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  • Inorganic Chemistry  (2.205)
  • Temperatur
  • Aircraft Stability and Control
  • Limnology
  • 2005-2009  (185)
  • 1950-1954  (1.685)
  • 1945-1949  (671)
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  • 1
    Publikationsdatum: 2009
    Beschreibung: Auswirkungen rezenter Klimaveränderungen im Meckenheimer Obstbaugebiet mit Hilfe 50-jähriger meteorologischer Aufzeichnungen auf die phänologischen Stadien Blüte, Ernte und Laubfall bei Apfel und Birne KATASTER-BESCHREIBUNG: Beginn des rezenten Klimawandels ab 1988: 1. Abschnitt von 1958–1987 (Periode I) nur geringe Temperaturänderung (0,42°C kühler) gegenüber dem langjährigen, 50-jährigen Mittel von 9,4°C auf, 2. Abschnitt von 1988–2007 (Periode II) mit Temperaturerhöhung (0,66°C wärmer), hier Beeinflussung der phänologischen Entwicklung bei Kernobst KATASTER-DETAIL: Tmit (Periode II), hier Blühdauer in den letzten 10 Jahren um etwa 4 Tage kürzer; Rückgang der Blühdauer von 12–15 auf 8–10 Tage und Verlängerung frostfreiee Periode um ca. 6 Tage und Änderung der Vegetationszeit (pomologische Vegetationszeit“ von Blühbeginn bis Laubfallbeginn) bei Apfel um 0–10 Tage bzw. bei Birne um 8 Tage in den Frühling – aber nicht in den Herbst – verlängerte
    Schlagwort(e): Klein-Altendorf, Nordrhein-Westfalen ; 1958-2007 ; Apfel ; Phänologie ; Temperatur ; Vegetationsperiode ; Birne
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  • 2
    Publikationsdatum: 2009
    Beschreibung: Einschätzungen der Reaktion der Wälder auf Klimawandel aus 11 Bundesländern mittels Fragebogen; biotische Schäden, abiotische Faktoren, Anfälligkeit von Baumarten gegenüber Einflüssen des Klimawandels KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Buche ; Eiche ; Fichte ; Forst ; Kiefer ; Klima ; Phänologie ; Temperatur ; Vegetationsperiode ; Waldwachstum ; Wassermangel ; Witterungsextreme
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  • 3
    facet.materialart.
    Unbekannt
    In:  Dissertationsschrift im Fach Geographie an der Mathematisch-Naturwissenschaftlichen Fakultät II der Humboldt-Universität zu Berlin
    Publikationsdatum: 2009
    Beschreibung: Mortalität in Perioden starker thermischer Belastung (1993, 1994 und 1997 sowie 2003 und 2006) im Zusammenhang mit dem Grad der Versiegelung und dem Anteil über-65-Jähriger KATASTER-BESCHREIBUNG: während thermisch stark belasteter Perioden der Jahre 1993, 1994 und 1997 sowie 2003 und 2006 sind bei unter-50-Jährigen Männer stärker als Frauen gefährdet, dieses Verhältnis kehrt sich in der Altersklasse über 50 um, hoher Versiegelungsgrad als Risikofaktor, bei weniger belastenden Situationen stehen Senioren dagegen gerade in Räumen mit geringer Versiegelung stärker unter Risiko (K. Gabriel, gekürzt) KATASTER-DETAIL: Delta T+: Tmax 〉 30°C und Andauer 〉 10d (1993, 1994, 1996, 2003, 2006) stärkere Mortalität von Männern 〈 50 Jahre
    Schlagwort(e): Berlin, Brandenburg ; 1990-2006 ; Umweltmedizin ; Temperatur
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  • 4
    Publikationsdatum: 2019-07-27
    Beschreibung: F-15 IFCS project goals are: a) Demonstrate Control Approaches that can Efficiently Optimize Aircraft Performance in both Normal and Failure Conditions [A] & [B] failures. b) Advance Neural Network-Based Flight Control Technology for New Aerospace Systems Designs with a Pilot in the Loop. Gen II objectives include; a) Implement and Fly a Direct Adaptive Neural Network Based Flight Controller; b) Demonstrate the Ability of the System to Adapt to Simulated System Failures: 1) Suppress Transients Associated with Failure; 2) Re-Establish Sufficient Control and Handling of Vehicle for Safe Recovery. c) Provide Flight Experience for Development of Verification and Validation Processes for Flight Critical Neural Network Software.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-956
    Format: application/pdf
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  • 5
    Publikationsdatum: 2019-07-13
    Beschreibung: The Next Generation (NextGen) transport aircraft configurations being investigated as part of the NASA Aeronautics Subsonic Fixed Wing Project have more control surfaces, or control effectors, than existing transport aircraft configurations. Conventional flight control is achieved through two symmetric elevators, two antisymmetric ailerons, and a rudder. The five effectors, reduced to three command variables, produce moments along the three main axes of the aircraft and enable the pilot to control the attitude and flight path of the aircraft. The NextGen aircraft will have additional redundant control effectors to control the three moments, creating a situation where the aircraft is over-actuated and where a simple relationship does not exist anymore between the required effector deflections and the desired moments. NextGen flight controllers will incorporate control allocation algorithms to determine the optimal effector commands and attain the desired moments, taking into account the effector limits. Approaches to solving the problem using linear programming and quadratic programming algorithms have been proposed and tested. It is of great interest to understand their relative advantages and disadvantages and how design parameters may affect their properties. In this paper, we investigate the sensitivity of the effector commands with respect to the desired moments and show on some examples that the solutions provided using the l2 norm of quadratic programming are less sensitive than those using the l1 norm of linear programming.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN-369 , AIAA Infotech@Aerospace Conference and Exhibit; Apr 06, 2009 - Apr 09, 2009; Seattle, WA; United States
    Format: application/pdf
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  • 6
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-07-19
    Beschreibung: In recent flight tests of F-15 Intelligent Flight Control System (IFCS), software simulated aircraft control surface failures were inserted to evaluate the IFCS adaptive systems. The failure commanded the left stabilator to a fixed position. The adaptive system uses a neural network that is designed to change control law gains, in the event of damage (real or simulated), that allows the aircraft to fly as it had before the damage. The performance of the adaptive system was assessed in terms of its ability to re-establish good onboard model tracking and its ability to decouple roll and pitch response.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC:873 , AIAA Infotech at Aerospace Conference and Exhibit; Apr 06, 2009 - Apr 09, 2009; Washington; United States
    Format: text
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  • 7
    Publikationsdatum: 2019-07-12
    Beschreibung: The primary purpose of the Quiet Spike(TradeMark) flight research program was to analyze the aerodynamic, structural, and mechanical proof-of-concept of a large multi-stage telescoping nose spike installed on the National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California) F-15B airplane. This report describes the preflight stability and control analysis performed to assess the effect of the spike on the stability, controllability, and handling qualities of the airplane; and to develop an envelope expansion approach to maintain safety of flight. The overall flight test objective was to collect flight data to validate the spike structural dynamics and loads model up to Mach 1.8. Other objectives included validating the mechanical feasibility of a morphing fuselage at operational conditions and determining the near-field shock wave characterization. The two main issues relevant to the stability and control objectives were the effects of the spike-influenced aerodynamics on the F-15B airplane flight dynamics, and the air data and angle-of-attack sensors. The analysis covered the sensitivity of the stability margins, and the handling qualities due to aerodynamic variation and the maneuvering limitations of the F-15B Quiet Spike configuration. The results of the analysis and the implications for the flight test program are also presented.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2009-214651 , H-2956 , DFRC-654
    Format: application/pdf
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  • 8
    Publikationsdatum: 2019-08-13
    Beschreibung: Adaptive control should be integrated with a baseline controller and only used when necessary (5 responses). Implementation as an emergency system. Immediately re-stabilize and return to controlled flight. Forced perturbation (excitation) for fine-tuning system a) Check margins; b) Develop requirements for amplitude of excitation. Adaptive system can improve performance by eating into margin constraints imposed on the non-adaptive system. Nonlinear effects due to multi-string voting.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-1050 , NASA RFI Workshop on Adaptive Control Validation; Aug 09, 2009; Chicago, IL; United States
    Format: application/pdf
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  • 9
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-07-12
    Beschreibung: This video presentation reviews the F-15 Intelligent Flight Control System and contains clips of flight tests and aircraft performance in the areas of target tracking, takeoff and differential stabilators. Video of the APG milestone flight 1g formation is included.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-992
    Format: text
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  • 10
    Publikationsdatum: 2019-07-12
    Beschreibung: The National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California) is conducting ongoing flight research using adaptive controller algorithms. A highly modified McDonnell-Douglas NF-15B airplane called the F-15 Intelligent Flight Control System (IFCS) is used to test and develop these algorithms. Modifications to this airplane include adding canards and changing the flight control systems to interface a single-string research controller processor for neural network algorithms. Research goals include demonstration of revolutionary control approaches that can efficiently optimize aircraft performance in both normal and failure conditions and advancement of neural-network-based flight control technology for new aerospace system designs. This report presents an overview of the processes utilized to develop adaptive controller algorithms during a flight-test program, including a description of initial adaptive controller concepts and a discussion of modeling formulation and performance testing. Design finalization led to integration with the system interfaces, verification of the software, validation of the hardware to the requirements, design of failure detection, development of safety limiters to minimize the effect of erroneous neural network commands, and creation of flight test control room displays to maximize human situational awareness; these are also discussed.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2009-214648 , H-2973 , DFRC-989
    Format: application/pdf
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  • 11
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-12
    Beschreibung: We propose a new framework called Evolving Systems to describe the self-assembly, or autonomous assembly, of actively controlled dynamical subsystems into an Evolved System with a higher purpose. An introduction to Evolving Systems and exploration of the essential topics of the control and stability properties of Evolving Systems is provided. This chapter defines a framework for Evolving Systems, develops theory and control solutions for fundamental characteristics of Evolving Systems, and provides illustrative examples of Evolving Systems and their control with adaptive key component controllers.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN820
    Format: application/pdf
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  • 12
    Publikationsdatum: 2019-07-12
    Beschreibung: This viewgraph presentation reviews the F-15 Intelligent Flight Control System and Aeronautics including Autonomous Aerial Refueling Demonstrations, X-48B Blended Wing Body, F-15 Quiet Spike, and NF-15 Intelligent Flight Controls.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-992
    Format: application/pdf
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  • 13
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper addresses the problem of verifying adaptive control techniques for enabling safe flight in the presence of adverse conditions. Since the adaptive systems are non-linear by design, the existing control verification metrics are not applicable to adaptive controllers. Moreover, these systems are in general highly uncertain. Hence, the system's characteristics cannot be evaluated by relying on the available dynamical models. This necessitates the development of control verification metrics based on the system's input-output information. For this point of view, a set of metrics is introduced that compares the uncertain aircraft's input-output behavior under the action of an adaptive controller to that of a closed-loop linear reference model to be followed by the aircraft. This reference model is constructed for each specific maneuver using the exact aerodynamic and mass properties of the aircraft to meet the stability and performance requirements commonly accepted in flight control. The proposed metrics are unified in the sense that they are model independent and not restricted to any specific adaptive control methods. As an example, we present simulation results for a wing damaged generic transport aircraft with several existing adaptive controllers.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN803 , AIAA Guidance, Navigation and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
    Format: application/pdf
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  • 14
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper addresses the problem of controlling a nonlinear plant with a slow actuator using singular perturbation method. For the known plant-actuator cascaded system the proposed scheme achieves tracking of a given reference model with considerably less control demand than would otherwise result when using conventional design techniques. This is the consequence of excluding the small parameter from the actuator dynamics via time scale separation. The resulting tracking error is within the order of this small parameter. For the unknown system the adaptive counterpart is developed based on the prediction model, which is driven towards the reference model by the control design. It is proven that the prediction model tracks the reference model with an error proportional to the small parameter, while the prediction error converges to zero. The resulting closed-loop system with all prediction models and adaptive laws remains stable. The benefits of the approach are demonstrated in simulation studies and compared to conventional control approaches.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN802 , AIAA Guidance, Navigation and Control Conference (GN&C) 2009; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
    Format: application/pdf
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  • 15
    Publikationsdatum: 2019-07-13
    Beschreibung: The objective of this work is to assess the strengths, weaknesses, and robustness characteristics of several MRAC (Model-Reference Adaptive Control) based adaptive control technologies garnering interest from the community as a whole. To facilitate this, a control study using piloted and unpiloted simulations to evaluate sensitivities and handling qualities was conducted. The adaptive control technologies under consideration were ALR (Adaptive Loop Recovery), BLS (Bounded Linear Stability), Hybrid Adaptive Control, L1, OCM (Optimal Control Modification), PMRAC (Predictor-based MRAC), and traditional MRAC
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN956 , NASA Aviation Safety Conference; Nov 17, 2009 - Nov 19, 2009; McLean, VA; United States
    Format: application/pdf
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  • 16
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: Next generation aircraft with a large number of actuators will require advanced control allocation methods to compute the actuator commands needed to follow desired trajectories while respecting system constraints. Previously, algorithms were proposed to minimize the l1 or l2 norms of the tracking error and of the actuator deflections. The paper discusses the alternative choice of the l(infinity) norm, or sup norm. Minimization of the control effort translates into the minimization of the maximum actuator deflection (min-max optimization). The paper shows how the problem can be solved effectively by converting it into a linear program and solving it using a simplex algorithm. Properties of the algorithm are also investigated through examples. In particular, the min-max criterion results in a type of load balancing, where the load is th desired command and the algorithm balances this load among various actuators. The solution using the l(infinity) norm also results in better robustness to failures and to lower sensitivity to nonlinearities in illustrative examples.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN656 , AIAA Guidance, Navigation, and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
    Format: application/pdf
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  • 17
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents the application of Bounded Linear Stability Analysis (BLSA) method for metrics driven adaptive control. The bounded linear stability analysis method is used for analyzing stability of adaptive control models, without linearizing the adaptive laws. Metrics-driven adaptive control introduces a notion that adaptation should be driven by some stability metrics to achieve robustness. By the application of bounded linear stability analysis method the adaptive gain is adjusted during the adaptation in order to meet certain phase margin requirements. Analysis of metrics-driven adaptive control is evaluated for a linear damaged twin-engine generic transport model of aircraft. The analysis shows that the system with the adjusted adaptive gain becomes more robust to unmodeled dynamics or time delay.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN528 , AIAA Infotech Aerospace Conference; Jun 04, 2009; Seattle, WA; United States
    Format: application/pdf
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  • 18
    Publikationsdatum: 2019-07-13
    Beschreibung: Active control methodologies were applied to a full-scale active flap rotor obtained during a joint Boeing/ DARPA/NASA/Army test in the Air Force National Full-Scale Aerodynamic Complex 40- by 80-foot anechoic wind tunnel. The active flap rotor is a full-scale MD 900 helicopter main rotor with each of its five blades modified to include an on-blade piezoelectric actuator-driven flap with a span of 18% of radius, 25% of chord, and located at 83% radius. Vibration control demonstrated the potential of active flaps for effective control of vibratory loads, especially normal force loads. Active control of normal force vibratory loads using active flaps and a continuous-time higher harmonic control algorithm was very effective, reducing harmonic (1-5P) normal force vibratory loads by 95% in both cruise and approach conditions. Control of vibratory roll and pitch moments was also demonstrated, although moment control was less effective than normal force control. Finally, active control was used to precisely control blade flap position for correlation with pretest predictions of rotor aeroacoustics. Flap displacements were commanded to follow specific harmonic profiles of 2 deg or more in amplitude, and the flap deflection errors obtained were less than 0.2 deg r.m.s.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN590 , American Helicopter Society 65th Annual Forum and Technology Display; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
    Format: text
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  • 19
    Publikationsdatum: 2019-07-13
    Beschreibung: A cooperative study was performed to investigate the handling quality effects from reduced flight control system stability margins, and the trade-offs with higher disturbance rejection bandwidth (DRB). The piloted simulation study, perform on the NASA-Ames Vertical Motion Simulator, included three classes of rotorcraft in four configurations: a utility-class helicopter; a medium-lift helicopter evaluated with and without an external slung load; and a large (heavy-lift) civil tiltrotor aircraft. This large aircraft also allowed an initial assessment of ADS-33 handling quality requirements for an aircraft of this size. Ten experimental test pilots representing the U.S. Army, Marine Corps, NASA, rotorcraft industry, and the German Aerospace Center (DLR), evaluated the four aircraft configurations, for a range of flight control stability-margins and turbulence levels, while primarily performing the ADS-33 Hover and Lateral Reposition MTEs. Pilot comments and aircraft-task performance data were analyzed. The preliminary stability margin results suggest higher DRB and less phase margin cases are preferred as the aircraft increases in size. Extra care will need to be taken to assess the influence of variability when nominal flight control gains start with reduced margins. Phase margins as low as 20-23 degrees resulted in low disturbance-response damping ratios, objectionable oscillations, PIO tendencies, and a perception of an incipient handling qualities cliff. Pilot comments on the disturbance response of the aircraft correlated well to the DRB guidelines provided in the ADS-33 Test Guide. The A D-3S3 mid-term response-to-control damping ratio metrics can be measured and applied to the disturbance-response damping ratio. An initial assessment of LCTR yaw bandwidth shows the current Level 1 boundary needs to be relaxed to help account for a large pilot off-set from the c.g. Future efforts should continue to investigate the applicability/refinement of the current ADS-33 requirements to large vehicles, like an LCTR.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN523 , American Helicopter Society 65th Annual Forum Handling Qualities Session; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
    Format: application/pdf
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  • 20
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: In the presence of large uncertainties, a control system needs to be able to adapt rapidly to regain performance. Fast adaptation is referred to the implementation of adaptive control with a large adaptive gain to reduce the tracking error rapidly. However, a large adaptive gain can lead to high-frequency oscillations which can adversely affect robustness of an adaptive control law. A new adaptive control modification is presented that can achieve robust adaptation with a large adaptive gain without incurring high-frequency oscillations as with the standard model-reference adaptive control. The modification is based on the minimization of the Y2 norm of the tracking error, which is formulated as an optimal control problem. The optimality condition is used to derive the modification using the gradient method. The optimal control modification results in a stable adaptation and allows a large adaptive gain to be used for better tracking while providing sufficient stability robustness. Simulations were conducted for a damaged generic transport aircraft with both standard adaptive control and the adaptive optimal control modification technique. The results demonstrate the effectiveness of the proposed modification in tracking a reference model while maintaining a sufficient time delay margin.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN536 , AIAA Infotech@Aerospace; Apr 06, 2009 - Apr 09, 2009; Seattle, WA; United States
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  • 21
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper expands on the hybrid control architecture developed at the NASA Ames Research Center by addressing issues related to indirect adaptation using the recursive least squares (RLS) algorithm. Specifically, the hybrid control architecture is an adaptive flight controller that features both direct and indirect adaptation techniques. This paper will focus almost exclusively on the modifications necessary to achieve quality indirect adaptive control. Additionally this paper will present results that, using a full non -linear aircraft model, demonstrate the effectiveness of the hybrid control architecture given drastic changes in an aircraft s dynamics. Throughout the development of this topic, a thorough discussion of the RLS algorithm as a system identification technique will be provided along with results from seven well-known modifications to the popular RLS algorithm.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN521 , AIAA Infotech@aerospace; Apr 06, 2009 - Apr 09, 2009; Seattle, WA; United States
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  • 22
    Publikationsdatum: 2019-07-13
    Beschreibung: Trajectory-based operations with self-separation involve the aircraft taking the primary role in the management of its own trajectory in the presence of other traffic. In this role, the flight crew assumes the responsibility for ensuring that the aircraft remains separated from all other aircraft by at least a minimum separation standard. These operations are enabled by cooperative airborne surveillance and by airborne automation systems that provide essential monitoring and decision support functions for the flight crew. An airborne automation system developed and used by NASA for research investigations of required functionality is the Autonomous Operations Planner. It supports the flight crew in managing their trajectory when responsible for self-separation by providing monitoring and decision support functions for both strategic and tactical flight modes. The paper focuses on the latter of these modes by describing a capability for tactical intent-based conflict resolution and its role in a comprehensive suite of automation functions supporting trajectory-based operations with self-separation.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8424 , 9th AIAA Aviation Technology, Integration, and Operations Conference; Sep 21, 2009 - Sep 24, 2009; Hilton Head, SC; United States
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  • 23
    Publikationsdatum: 2019-07-13
    Beschreibung: Objective: Provide validation of adaptive control law concepts through full scale flight evaluation. Technical Approach: a) Engage failure mode - destabilizing or frozen surface. b) Perform formation flight and air-to-air tracking tasks. Evaluate adaptive algorithm: a) Stability metrics. b) Model following metrics. Full scale flight testing provides an ability to validate different adaptive flight control approaches. Full scale flight testing adds credence to NASA's research efforts. A sustained research effort is required to remove the road blocks and provide adaptive control as a viable design solution for increased aircraft resilience.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-1045 , NESC GN&C Face-to-face Meeting; Aug 09, 2009; Chicago, IL; United States
    Format: application/pdf
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  • 24
    Publikationsdatum: 2019-07-13
    Beschreibung: Next generation aviation flight control concepts require autonomous and intelligent control system architectures that close control loops directly around payload sensors in manner more integrated and cohesive that in traditional autopilot designs. Research into payload directed flight control at NASA Ames Research Center is investigating new and novel architectures that can satisfy the requirements for next generation control and automation concepts for aviation. Tighter integration between sensor and machine requires definition of specific sensor-directed control modes to tie the sensor data directly into a vehicle control structures throughout the entire control architecture, from low-level stability- and control loops, to higher level mission planning and scheduling reasoning systems. Payload directed flight systems can thus provide guidance, navigation, and control for vehicle platforms hosting a suite of onboard payload sensors. This paper outlines related research into the field of payload directed flight; and outlines requirements and operating concepts for payload directed flight systems based on identified needs from the scientific literature.'
    Schlagwort(e): Aircraft Stability and Control
    Materialart: IEEEAC-paper-1410 , ARC-E-DAA-TN-342 , 2009 IEEE Aerospace Conference; Mar 07, 2009 - Mar 10, 2009; Big Sky, MT; United States
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  • 25
    Publikationsdatum: 2019-07-13
    Beschreibung: In this paper we present a new L(sub 1) adaptive control architecture that directly compensates for matched as well as unmatched system uncertainty. To evaluate the L(sub 1) adaptive controller, we take advantage of the flexible research environment with rapid prototyping and testing of control laws in the Airborne Subscale Transport Aircraft Research system at the NASA Langley Research Center. We apply the L(sub 1) adaptive control laws to the subscale turbine powered Generic Transport Model. The presented results are from a full nonlinear simulation of the Generic Transport Model and some preliminary pilot evaluations of the L(sub 1) adaptive control law.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8378 , AIAA Guidance, Navigation, and Control Conference (GNC) 2009; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 26
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper is devoted to robust, Predictor-based Model Reference Adaptive Control (PMRAC) design. The proposed adaptive system is compared with the now-classical Model Reference Adaptive Control (MRAC) architecture. Simulation examples are presented. Numerical evidence indicates that the proposed PMRAC tracking architecture has better than MRAC transient characteristics. In this paper, we presented a state-predictor based direct adaptive tracking design methodology for multi-input dynamical systems, with partially known dynamics. Efficiency of the design was demonstrated using short period dynamics of an aircraft. Formal proof of the reported PMRAC benefits constitute future research and will be reported elsewhere.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8365 , AIAA Guidance, Navigation, and Control Conference (GNC) 2009; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 27
    Publikationsdatum: 2019-07-13
    Beschreibung: The problem of controlling a system in the presence of unknown actuator and sensor faults is addressed. The system is assumed to have groups of actuators, and groups of sensors, with each group consisting of multiple redundant similar actuators or sensors. The types of actuator faults considered consist of unknown actuators stuck in unknown positions, as well as reduced actuator effectiveness. The sensor faults considered include unknown biases and outages. The approach employed for fault detection and estimation consists of a bank of Kalman filters based on multiple models, and subsequent control reconfiguration to mitigate the effect of biases caused by failed components as well as to obtain stability and satisfactory performance using the remaining actuators and sensors. Conditions for fault identifiability are presented, and the adaptive scheme is applied to an aircraft flight control example in the presence of actuator failures. Simulation results demonstrate that the method can rapidly and accurately detect faults and estimate the fault values, thus enabling safe operation and acceptable performance in spite of failures.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8359 , AIAA Guidance, Navigation, and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 28
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents the application of Bounded Linear Stability Analysis (BLSA) method for metrics-driven adaptive control. The bounded linear stability analysis method is used for analyzing stability of adaptive control models, without linearizing the adaptive laws. Metrics-driven adaptive control introduces a notion that adaptation should be driven by some stability metrics to achieve robustness. By the application of bounded linear stability analysis method the adaptive gain is adjusted during the adaptation in order to meet certain phase margin requirements. Analysis of metrics-driven adaptive control is evaluated for a second order system that represents a pitch attitude control of a generic transport aircraft. The analysis shows that the system with the metrics-conforming variable adaptive gain becomes more robust to unmodeled dynamics or time delay. The effect of analysis time-window for BLSA is also evaluated in order to meet the stability margin criteria.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN-289 , AIAA Aerospace Sciences Meeting; Jan 05, 2009 - Jan 08, 2009; Orlando, FL; United States
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  • 29
    Publikationsdatum: 2019-07-13
    Beschreibung: Suitably placed discrete roughness elements are known to delay or hasten the onset of transition, depending on requirements. In this paper, 2D eigenvalue analysis is used to study the effects of surface roughness in the context of transition delay over subsonic and supersonic swept wing configurations, as well as boundarylayer tripping on the forebody of a hypersonic air breathing vehicle.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8181 , IUTAM 2009 Symposium on Laminar-Turbulent Transition; Jun 23, 2009 - Jun 26, 2009; Stockholm; Sweden
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  • 30
    Publikationsdatum: 2019-07-13
    Beschreibung: The Rapidly Deployable Stable Platform (RDSP) is a novel vessel designed to be a reconfigurable, stable at-sea platform. It consists of a detachable catamaran and spar, performing missions with the spar extending vertically below the catamaran and hoisting it completely out of the water. Multiple thrusters located along the spar allow it to be actively controlled in this configuration. A controller is presented in this work that uses an adaptive feedback algorithm in conjunction with Direct Adaptive Disturbance Rejection (DADR) to mitigate persistent, vortex-induced disturbances. Given the frequency of a disturbance, the nominal DADR scheme adaptively compensates for its unknown amplitude and phase. This algorithm is extended to adapt to a disturbance frequency that is only coarsely known by including a Phase Locked Loop (PLL). The PLL improves the frequency estimate on-line, allowing the modified controller to reduce vortex-induced motions by more than 95% using achievable thrust inputs.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: OMAE2009-79492 , M09-0360 , International Conference on Ocean, Offshore and Arctic Engineering; May 31, 2009 - Jun 05, 2009; Honolulu, HI; United States
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  • 31
    Publikationsdatum: 2019-07-13
    Beschreibung: The development of flight control systems to enhance aircraft safety during periods of vehicle impairment or degraded operations has been the focus of extensive work in recent years. Conditions adversely affecting aircraft flight operations and safety may result from a number of causes, including environmental disturbances, degraded flight operations, and aerodynamic upsets. To enhance the effectiveness of adaptive and envelope limiting controls systems, it is desirable to examine methods for identifying the occurrence of anomalous conditions and for assessing the impact of these conditions on the aircraft operational limits. This paper describes initial work performed toward this end, examining the use of fault detection methods applied to the aircraft for aerodynamic performance degradation identification and model-based methods for envelope prediction. Results are presented in which a model-based fault detection filter is applied to the identification of aircraft control surface and stall departure failures/upsets. This application is supported by a distributed loading aerodynamics formulation for the flight dynamics system reference model. Extensions for estimating the flight envelope due to generalized aerodynamic performance degradation are also described.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-9220 , AIAA Guidance, Navigation, and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 32
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper considers the problem of direct model reference adaptive control when the plant-model matching conditions are violated due to abnormal changes in the plant or incorrect knowledge of the plant's mathematical structure. The approach consists of direct adaptation of state feedback gains for state tracking, and simultaneous estimation of the plant-model mismatch. Because of the mismatch, the plant can no longer track the state of the original reference model, but may be able to track a new reference model that still provides satisfactory performance. The reference model is updated if the estimated plant-model mismatch exceeds a bound that is determined via robust stability and/or performance criteria. The resulting controller is a hybrid direct-indirect adaptive controller that offers asymptotic state tracking in the presence of plant-model mismatch as well as parameter deviations.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-8350 , AIAA Guidance, Navigation, and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 33
    Publikationsdatum: 2019-07-12
    Beschreibung: The NASA F/A-18 tail number (TN) 853 full-scale Integrated Resilient Aircraft Control (IRAC) testbed has been designed with a full array of capabilities in support of the Aviation Safety Program. Highlights of the system's capabilities include: 1) a quad-redundant research flight control system for safely interfacing controls experiments to the aircraft's control surfaces; 2) a dual-redundant airborne research test system for hosting multi-disciplinary state-of-the-art adaptive control experiments; 3) a robust reversionary configuration for recovery from unusual attitudes and configurations; 4) significant research instrumentation, particularly in the area of static loads; 5) extensive facilities for experiment simulation, data logging, real-time monitoring and post-flight analysis capabilities; and 6) significant growth capability in terms of interfaces and processing power.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-IRAC-CAP-002 , DFRC-972
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  • 34
    Publikationsdatum: 2019-07-19
    Beschreibung: If normal aircraft flight controls are lost, emergency flight control may be attempted using only the thrust of engines. Collective thrust is used to control flightpath, and differential thrust is used to control bank angle. One issue is whether a total loss of hydraulics (TLOH) leaves an airplane in a recoverable condition. Recoverability is a function of airspeed, altitude, flight phase, and configuration. If the airplane can be recovered, flight test and simulation results on several transport-class airplanes have shown that throttles-only control (TOC) is usually adequate to maintain up-and-away flight, but executing a safe landing is very difficult. There are favorable aircraft configurations, and also techniques that will improve recoverability and control and increase the chances of a survivable landing. The DHS and NASA have recently conducted a flight and simulator study to determine the effectivity of manual throttles-only control as a way to recover and safely land a range of transport airplanes. This paper discusses TLOH recoverability as a function of conditions, and TOC landability results for a range of transport airplanes, and some key techniques for flying with throttles and making a survivable landing. Airplanes evaluated include the B-747, B-767, B-777, B-757, A320, and B-737 airplanes.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-953 , 9th AIAA Aviation Technology, Integration, and Operations Conference; Sep 21, 2009 - Sep 23, 2009; Hilton Head, SC; United States
    Format: text
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  • 35
    Publikationsdatum: 2019-07-13
    Beschreibung: The National Aeronautics and Space Administration (NASA) at the Dryden Flight Research Center (DFRC) has been conducting flight-test research using an F-15 aircraft (figure 1). This aircraft has been specially modified to interface a neural net (NN) controller as part of a single-string Airborne Research Test System (ARTS) computer with the existing quad-redundant flight control system (FCC) shown in figure 2. The NN commands are passed to FCC channels 2 and 4 and are cross channel data linked (CCDL) to the other computers as shown. Numerous types of fault-detection monitors exist in the FCC when the NN mode is engaged; these monitors would cause an automatic disengagement of the NN in the event of a triggering fault. Unfortunately, these monitors still may not prevent a possible NN hard-over command from coming through to the control laws. Therefore, an additional and unique safety monitor was designed for a single-string source that allows authority at maximum actuator rates but protects the pilot and structural loads against excessive g-limits in the case of a NN hard-over command input. This additional monitor resides in the FCCs and is executed before the control laws are computed. This presentation describes a "floating limiter" (FL) concept that was developed and successfully test-flown for this program (figure 3). The FL computes the rate of change of the NN commands that are input to the FCC from the ARTS. A window is created with upper and lower boundaries, which is constantly "floating" and trying to stay centered as the NN command rates are changing. The limiter works by only allowing the window to move at a much slower rate than those of the NN commands. Anywhere within the window, however, full rates are allowed. If a rate persists in one direction, it will eventually "hit" the boundary and be rate-limited to the floating limiter rate. When this happens, a persistent counter begins and after a limit is reached, a NN disengage command is generated. The tunable metrics for the FL are (1) window size, (2) drift rate, and (3) persistence counter. Ultimate range limits are also included in case the NN command should drift slowly to a limit value that would cause the FL to be defeated. The FL has proven to work as intended. Both high-g transients and excessive structural loads are controlled with NN hard-over commands. This presentation discusses the FL design features and presents test cases. Simulation runs are included to illustrate the dramatic improvement made to the control of NN hard-over effects. A mission control room display from a flight playback is presented to illustrate the neural net fault display representation. The FL is very adaptable to various requirements and is independent of flight condition. It should be considered as a cost-effective safety monitor to control single-string inputs in general.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-970 , AIAA Infotech@Aerospace Conference and Exhibit; Apr 06, 2009 - Apr 09, 2009; Seattle, WA; United States
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  • 36
    Publikationsdatum: 2019-07-13
    Beschreibung: Program Objectives: I. Assess stability & control characteristics of a BWB class vehicle in free-flight conditions: a) Assess dynamic interaction of control surfaces; b) Assess control requirements to accommodate asymmetric thrust; and c) Assess stability and controllability about each axis at a range of flight conditions. II. Assess flight control algorithms designed to provide desired flight characteristics: a) Assess control surface allocation and blending; b) Assess edge of envelope protection schemes; c) Assess takeoff and landing characteristics; and d) Test experimental control laws and control design methods III. Evaluate prediction and test methods for BWB class vehicles: a) Correlate flight measurements with ground-based predictions and measurements.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-993 , International Test and Evaluation Association (ITEA) 2009 Test Instrumentation Workshop; May 12, 2009 - May 14, 2009; Ridgecrest, CA; United States
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  • 37
    Publikationsdatum: 2019-07-13
    Beschreibung: The NASA AirSTAR system has been designed to address the challenges associated with safe and efficient subscale flight testing of research control laws in adverse flight conditions. In this paper, software elements of this system are described, with an emphasis on components which allow for rapid prototyping and deployment of aircraft control laws. Through model-based design and automatic coding a common code-base is used for desktop analysis, piloted simulation and real-time flight control. The flight control system provides the ability to rapidly integrate and test multiple research control laws and to emulate component or sensor failures. Integrated integrity monitoring systems provide aircraft structural load protection, isolate the system from control algorithm failures, and monitor the health of telemetry streams. Finally, issues associated with software configuration management and code modularity are briefly discussed.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-7618 , AIAA Infotech at Aerospace Conference and Exhibit; Apr 06, 2009 - Apr 09, 2009; Washington; United States
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  • 38
    Publikationsdatum: 2019-07-13
    Beschreibung: The National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California) is conducting ongoing flight research using adaptive controller algorithms. A highly modified McDonnell-Douglas NF-15B airplane called the F-15 Intelligent Flight Control System (IFCS) was used for these algorithms. This airplane has been modified by the addition of canards and by changing the flight control systems to interface a single-string research controller processor for neural network algorithms. Research goals included demonstration of revolutionary control approaches that can efficiently optimize aircraft performance for both normal and failure conditions, and to advance neural-network-based flight control technology for new aerospace systems designs. Before the NF-15B IFCS airplane was certified for flight test, however, certain processes needed to be completed. This paper presents an overview of these processes, including a description of the initial adaptive controller concepts followed by a discussion of modeling formulation and performance testing. Upon design finalization, the next steps are: integration with the system interfaces, verification of the software, validation of the hardware to the requirements, design of failure detection, development of safety limiters to minimize the effect of erroneous neural network commands, and creation of flight test control room displays to maximize human situational awareness.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC #874 , AIAA Infotech@ Aerospace Conference and Exhibit; Apr 06, 2009 - Apr 09, 2009; Seattle, WA; United States
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  • 39
    Publikationsdatum: 2019-07-13
    Beschreibung: The paper presents an adaptive control technique for a damaged large transport aircraft subject to unknown atmospheric disturbances such as wind gust or turbulence. It is assumed that the damage results in vertical tail loss with no rudder authority, which is replaced with a differential thrust input. The proposed technique uses the adaptive prediction based control design in conjunction with the time scale separation principle, based on the singular perturbation theory. The application of later is necessitated by the fact that the engine response to a throttle command is substantially slow that the angular rate dynamics of the aircraft. It is shown that this control technique guarantees the stability of the closed-loop system and the tracking of a given reference model. The simulation example shows the benefits of the approach.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN806 , AIAA Guidance, Navigation and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 40
    Publikationsdatum: 2019-07-13
    Beschreibung: Recently a new optimal control modification has been introduced that can achieve robust adaptation with a large adaptive gain without incurring high-frequency oscillations as with the standard model-reference adaptive control. This modification is based on an optimal control formulation to minimize the L2 norm of the tracking error. The optimal control modification adaptive law results in a stable adaptation in the presence of a large adaptive gain. This study examines the optimal control modification adaptive law in the context of a system with a time scale separation resulting from a fast plant with a slow actuator. A singular perturbation analysis is performed to derive a modification to the adaptive law by transforming the original system into a reduced-order system in slow time. The model matching conditions in the transformed time coordinate results in increase in the feedback gain and modification of the adaptive law.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN781 , 2009 AIAA Guidance, Navigation, and Control Conference; Aug 10, 2009 - Aug 13, 2009; Chicago, IL; United States
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  • 41
    Publikationsdatum: 2021-05-19
    Beschreibung: La presente tesis respondió preguntas importantes para el conocimiento del embalse de Rincón del Bonete (EdRB) y para la obtención de los puntos de referencia para la determinación de estrés ecológico en el mismo. Los objetivos específicos comprendieron la determinación de los aspectos limnológicos más relevantes, la caracterización del embalse según su estado trófico, así como el conocimiento del estado de explotación de la especie íctica mas relevante desde el punto de vista comercial. Se determinaron indicadores que permitieron aportar información de base para cuantificar el grado de perturbación del embalse a fin de adoptar estrategias de conservación y manejo, así como definir las zonas más sensibles de impacto ambiental. Se evaluó la variabilidad espacio-temporal de los componentes bióticos y abióticos que pudieran emplearse como indicadores de estrés y se realizó un diagnóstico del EdRB empleando métodos holísticos (índices y modelos morfoedáficos), empíricos (técnicas hidroacústicas) y modelos analíticos basados en una descripción más detallada del stock (análisis virtual de poblaciones). Se encontró un gradiente marcado desde la represa hacia la entrada del río al embalse, fundamentalmente en cuanto a la transparencia del agua, concentración de fosfatos, conductividad y densidad de organismos fitoplanctónicos y zooplanctónicos. Los indicadores basados en organismos zooplanctónicos lo clasificarían como un ambiente mesotrófico. Los resultados obtenidos con técnicas hidroacústicas y pesca experimental, sugieren un patrón de distribución espacio-temporal, caracterizado por desplazamientos de los peces entre el cuerpo central del embalse y los brazos, asociado a la época del año o al régimen hidrológico. Se propuso un indicador del estado de estrés (IR) basado en las técnicas hidroacústicas, que relaciona la ictiomasa potencialmente reclutable a la pesquería con la ictiomasa total. El IR mostró variaciones espaciales que evidenciaron áreas de cría de peces y al comparar para un mismo ambiente las variaciones anuales, se obtuvo un indicador de estrés. El análisis de largo plazo (1991-1999) mostró que la tararira (Hoplias malabaricus malabaricus) está siendo sometida a un fuerte estrés debido a la presión de pesca realizada en el EdRB. Las diferentes aproximaciones metodológicas y variables empleadas para evaluar el estado de situación del EdRB, muestran efectos antropogénicos en el sistema y en la comunidad ictícola asociada. A efectos de proveer las bases ambientales para un manejo integrado, se propone la continuación del monitoreo, considerando variables físico-químicas sensibles y componentes de la trama trófica, en especial fito y zooplancton, y biomasa íctica. Se sugieren pautas de manejo adicionales, tales como la creación de áreas protegidas y la implementación de vedas espaciales a la actividad pesquera.
    Beschreibung: This thesis answered important questions for the knowledge of the Rincon del Bonete (EdRB) reservoir and to obtain points of reference for the determination of ecologic stress in it, by means of a long-term study. The specific objectives included the determination of the main limnological aspects, the characterisation of the reservoir according to its trophyc status, the estimation of the composition and structure of the ichthyic community, as well as the status of exploitation of the main species. Finally, signs that provided information to quantify the grade of disturbance of the reservoir, aimed at the taking of management and protection strategies, as well as at defining the most sensible zones of environmental impact. The space-temporal variability of the biotic components suitable of being used as stress indicators was evaluated and the possible application of the determination of ichthyic biomass and of other fishing-biological parameters as of possible ecological stress estimators. A diagnostic of the reservoir was carried out performing different studies based on holistic (morphoedaphic index and morphoedaphic models), empirical (hydroacoustic techniques and experimental fishing) and analytical methods (virtual population analysis). The EdRB was classified as a mesotrophic environment according with the zooplankton composition and with the nutrients concentrations. The results obtained with hydroacoustic techniques and experimental fishing outlined a space-temporal pattern of the fish distribution according with the season of the year and hydrological conditions. A stress indicator index (IR) was proposed based in hydroacoustic techniques. Space variations of this index pointed out breeding areas while temporal variations were considered as a stress condition. The long-term virtual population analysis (1991-1999) showed anthropogenic stress of tararira (Hoplias malabaricus malabaricus) as a result of over fishing. The different approaches carried out in order to evaluate the situation of the EdRB, pointed out anthropogenic effects on the system and the ichthyic community. A continuous monitory of the most sensible physical-chemicals variables as well as the web chain components (phytoplankton, zooplankton and ichthyic biomass particularly) was suggested in order to obtain the environmental basis of an integrated management of the reservoir. Recommendations on creating protected areas and implementing fishing restriction are presented.
    Beschreibung: Programa de Desarrollo de las Ciencias Básicas (PEDECIBA) - Facultad de Ciencias - Universidad de la República
    Beschreibung: Tesis de Doctorado en Biología, Opción Zoología
    Schlagwort(e): M40 ; Limnology ; Environmental monitoring ; Biomass ; Artificial lakes ; Resource conservation ; Ecological balance ; Limnology ; Environmental monitoring ; Artificial lakes ; Resource conservation ; Ecological balance ; Indicators ; Echo surveys ; Freshwater lakes ; Experimental fishing ; Biomass
    Repository-Name: AquaDocs
    Materialart: Theses and Dissertations
    Format: 166
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  • 42
    Publikationsdatum: 2021-05-19
    Beschreibung: Topics on Lake Victoria limnology, benthic fauna, stock assessment, catch assessment survey, gear selectivity, fisheries ecology, fish parasites and marketing economics are covered. Management and conservation of the lake's fisheries and other aquatic resources are discussed. Dialogue between fishermen, scientists and administrators is stressed, measures to be undertaken are addressed and further research is recommended.
    Beschreibung: Kenya Marine and Fisheries Research Institute and the European Economic Community
    Beschreibung: pp.1-9 only in uploaded file
    Beschreibung: Published
    Schlagwort(e): Fishery management ; Lake fisheries ; Limnology ; Stock assessment ; Inland fisheries ; Resource management ; Zoobenthos ; Fishery management ; Freshwater fish ; Inland fisheries ; Lake fisheries ; Limnology ; Resource management ; Stock assessment ; Zoobenthos
    Repository-Name: AquaDocs
    Materialart: Book
    Format: 197pp.
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  • 43
    Publikationsdatum: 2008
    Beschreibung: Nadelschäden, Überlebensrate, Höhenwachstum 1-jähriger Kiefern im Laborexperiment unter verschiedenen Frösten. Bei genereller Zunahme der mittleren Jahrestemperatur nimmt die Empfindlichkeit gegenüber Frösten zu KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Kiefer ; Klima ; Temperatur ; Witterungsextreme
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  • 44
    facet.materialart.
    Unbekannt
    In:  Gatower Gespräche 2007: Waldbau und Forstökonomie im Zeichen des Klimawandels
    Publikationsdatum: 2008
    Beschreibung: hauptsächlich Stress und Schäden durch zukünftigen Klimawandel KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Stressindikator ; Forst ; Kiefer ; Temperatur ; Trockenheit ; Wassermangel ; Witterungsextreme
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  • 45
    facet.materialart.
    Unbekannt
    In:  In: Gostomzyk, J.G.; Enke, M. (Hrsg.): Globaler Klimawandel und Gesundheit. Schriftenreihe der Landeszentrale für Gesundheit in Bayern, Band 19, München, 2008, 105-111
    Publikationsdatum: 2008
    Beschreibung: Auswirkung der Hitzewelle 2003 auf die Sterblichkeit in Bayern KATASTER-BESCHREIBUNG: Annahme des „harvesting“-Effekts KATASTER-DETAIL:
    Schlagwort(e): Bayern ; 2000-2003 ; Umweltmedizin ; Temperatur
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  • 46
    facet.materialart.
    Unbekannt
    In:  In: Lozán, J.L.; Graßl, H.; Jendritzky, G.; Karbe, L.; Reise, K. (Hrsg.) Warnsignal Klima: Gesundheitsrisiken. Gefahren für Pflanzen, Tiere und Menschen.Wissenschaftliche Auswertungen, Hamburg, 108-114
    Publikationsdatum: 2008
    Schlagwort(e): Umweltmedizin ; Temperatur ; Luftverunreinigungen
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  • 47
    facet.materialart.
    Unbekannt
    In:  Masterarbeit in der Klimatologie des Geographischen Instituts an der Mathematisch-Naturwissenschaftlichen Fakultät II der Humboldt-Universität zu Berlin
    Publikationsdatum: 2008
    Beschreibung: Vergleich der Sommerperioden 2003 und 2006 im Untersuchungszeitraum für Patientenaufnahmen bei über 45-Jähringen mit Atmungssystemerkrankungen KATASTER-BESCHREIBUNG: für Sommer 2006 positive signifikante Zusammenhänge zwischen Patientenaufnahmen mit Herz-Kreislauf- und Atmungssystemerkrankungen und ansteigender Luftfeuchte sowie Sonnenscheindauer bei Lufttemperaturen ab 25°C KATASTER-DETAIL: Delta T+, Delta Relf +, Delta Sonn+: Tmit 〉 25°C (2003 und 2006), dann signifikante Zunahme von Herzkreislauf-Erkrankungen und Atemwegssystemerkrankungen
    Schlagwort(e): Berlin ; 2002-2006 ; Umweltmedizin ; Temperatur
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  • 48
    Publikationsdatum: 2019-07-19
    Beschreibung: NASA Aeronautics Subsonic Fixed Wing Project is focused on mitigating the environmental and operation impacts expected as aviation operations triple by 2025. The approach is to extend technological capabilities and explore novel civil transport configurations that reduce noise, emissions, fuel consumption and field length. Two Next Generation (NextGen) aircraft have been identified to meet the Subsonic Fixed Wing Project goals - these are the Hybrid Wing-Body (HWB) and Cruise Efficient Short Take-Off and Landing (CESTOL) aircraft. The technologies and concepts developed for these aircraft complicate the vehicle s design and operation. In this paper, flight control challenges for NextGen aircraft are described. The objective of this paper is to examine the potential of state-of-the-art control architectures and algorithms to meet the challenges and needed performance metrics for NextGen flight control. A broad range of conventional and intelligent control approaches are considered, including dynamic inversion control, integrated flight-propulsion control, control allocation, adaptive dynamic inversion control, data-based predictive control and reinforcement learning control.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN121 , International Powered Lift Conference; Jul 22, 2008 - Jul 24, 2008; London; United Kingdom
    Format: text
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  • 49
    Publikationsdatum: 2019-08-26
    Beschreibung: Improved miniature trailing edge effectors for aerodynamic control are provided. Three types of devices having aerodynamic housings integrated to the trailing edge of an aerodynamic shape are presented, which vary in details of how the control surface can move. A bucket type device has a control surface which is the back part of a C-shaped member having two arms connected by the back section. The C-shaped section is attached to a housing at the ends of the arms, and is rotatable about an axis parallel to the wing trailing edge to provide up, down and neutral states. A flip-up type device has a control surface which rotates about an axis parallel to the wing trailing edge to provide up, down, neutral and brake states. A rotating type device has a control surface which rotates about an axis parallel to the chord line to provide up, down and neutral states.
    Schlagwort(e): Aircraft Stability and Control
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  • 50
    Publikationsdatum: 2019-07-12
    Beschreibung: The Dynamic Multi-track Airways (DMA) Concept for Air Traffic Management (ATM) proposes a network of high-altitude airways constructed of multiple, closely spaced, parallel tracks designed to increase en-route capacity in high-demand airspace corridors. Segregated from non-airway operations, these multi-track airways establish high-priority traffic flow corridors along optimal routes between major terminal areas throughout the National Airspace System (NAS). Air traffic controllers transition aircraft equipped for DMA operations to DMA entry points, the aircraft use autonomous control of airspeed to fly the continuous-airspace airway and achieve an economic benefit, and controllers then transition the aircraft from the DMA exit to the terminal area. Aircraft authority within the DMA includes responsibility for spacing and/or separation from other DMA aircraft. The DMA controller is responsible for coordinating the entry and exit of traffic to and from the DMA and for traffic flow management (TFM), including adjusting DMA routing on a daily basis to account for predicted weather and wind patterns and re-routing DMAs in real time to accommodate unpredicted weather changes. However, the DMA controller is not responsible for monitoring the DMA for traffic separation. This report defines the mature state concept, explores its feasibility and performance, and identifies potential benefits. The report also discusses (a) an analysis of a single DMA, which was modeled within the NAS to assess capacity and determine the impact of a single DMA on regional sector loads and conflict potential; (b) a demand analysis, which was conducted to determine likely city-pair candidates for a nationwide DMA network and to determine the expected demand fraction; (c) two track configurations, which were modeled and analyzed for their operational characteristic; (d) software-prototype airborne capabilities developed for DMA operations research; (e) a feasibility analysis of key attributes in the concept design; (f) a near-term, transitional application of the DMA concept as a proving ground for new airborne technologies; and (g) conclusions. The analysis indicates that the operational feasibility of a national DMA network faces significant challenges, especially for interactions between DMAs and between DMA and non-DMA traffic. Provided these issues are resolved, sectors near DMAs could experience significant local capacity benefits.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TP-2008-215323 , L-19462
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  • 51
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-12
    Beschreibung: The first air launch attempt of an X-43A stack, consisting of the booster, adapter and Hyper-X research vehicle, ended in failure shortly after the successful drop from the National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California) B-52B airplane and ignition of the booster. The stack was observed to begin rolling and yawing violently upon reaching transonic speeds, and the grossly oscillating fins of the booster separated shortly thereafter. The flight then had to be terminated with the stack out of control. Very careful linear flutter and aeroservoelastic analyses were subsequently performed as reported herein to numerically duplicate the observed instability. These analyses properly identified the instability mechanism and demonstrated the importance of including the flight control laws, rigid-body modes, structural flexible modes and control surface flexible modes. In spite of these efforts, however, the predicted instability speed remained more than 25 percent higher than that observed in flight. It is concluded that transonic shock phenomena, which linear analyses cannot take into account, are also important for accurate prediction of this mishap instability.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2008-214635 , H-2837
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  • 52
    Publikationsdatum: 2019-08-13
    Beschreibung: This poster presents the current adaptive control research being conducted at NASA ARC and LaRC in support of the Integrated Resilient Aircraft Control (IRAC) project. The technique "Approximate Stability Margin Analysis of Hybrid Direct-Indirect Adaptive Control" has been developed at NASA ARC to address the needs for stability margin metrics for adaptive control that potentially enables future V&V of adaptive systems. The technique "Direct Adaptive Control With Unknown Actuator Failures" is developed at NASA LaRC to deal with unknown actuator failures. The technique "Adaptive Control with Adaptive Pilot Element" is being researched at NASA LaRC to investigate the effects of pilot interactions with adaptive flight control that can have implications of stability and performance.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN-219 , NASA Aviation Safety Technical Conference; Oct 21, 2008; Denver, CO; United States
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  • 53
    Publikationsdatum: 2019-07-13
    Beschreibung: Icing alters the shape and surface characteristics of aircraft components, which results in altered aerodynamic forces and moments caused by air flow over those iced components. The typical effects of icing are increased drag, reduced stall angle of attack, and reduced maximum lift. In addition to the performance changes, icing can also affect control surface effectiveness, hinge moments, and damping. These effects result in altered aircraft stability and control and flying qualities. Over the past 80 years, methods have been developed to understand how icing affects performance, stability and control. Emphasis has been on wind tunnel testing of two-dimensional subscale airfoils with various ice shapes to understand their effect on the flow field and ultimately the aerodynamics. This research has led to wind tunnel testing of subscale complete aircraft models to identify the integrated effects of icing on the aircraft system in terms of performance, stability, and control. Data sets of this nature enable pilot in the loop simulations to be performed for pilot training, or engineering evaluation of system failure impacts or control system design.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2008-215453 , AIAA-Paper-2008-6204 , E-16643 , Atmospheric Flight Mechanics Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 54
    Publikationsdatum: 2019-07-13
    Beschreibung: This study investigated two concepts: (1) whether speeding a human-in-the-loop simulation (or the subject's "world") scales time stress in such a way as to cause primary task performance to reveal workload differences between experimental conditions and (2) whether using natural hand motions to control the attitude of an aircraft makes controlling the aircraft easier and more intuitive. This was accomplished by having pilots and non-pilots make altitude and heading changes using three different control inceptors at three simulation speeds. Results indicate that simulation speed does affect workload and controllability. The bank and pitch angle error was affected by simulation speed but not by a simulation speed by controller type interaction; this may have been due to the relatively easy flying task. Results also indicate that pilots could control the bank and pitch angle of an aircraft about equally as well with the glove as with the sidestick. Non-pilots approached the pilots ability to control the bank and pitch angle of an aircraft using the positional glove - where the hand angle is directly proportional to the commanded aircraft angle. Therefore, (1) changing the simulation speed lends itself to objectively indexing a subject s workload and may also aid in differentiating among interface concepts based upon performance if the task being studied is sufficiently challenging and (2) using natural body movements to mimic the movement of an airplane for attitude control is feasible.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: HFES 2008: Human Factors and Ergonomics Society 52nd Annual Meeting; Sep 22, 2008 - Sep 26, 2008; New York City, NY; United States
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  • 55
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: This report presents the system description, methods, and sample results of the in-flight stability analysis for the X-48B, Blended Wing Body Low-Speed Vehicle. The X-48B vehicle is a dynamically scaled, remotely piloted vehicle developed to investigate the low-speed control characteristics of a full-scale blended wing body. Initial envelope clearance was conducted by analyzing the stability margin estimation resulting from the rigid aircraft response during flight and comparing it to simulation data. Short duration multisine signals were commanded onboard to simultaneously excite the primary rigid body axes. In-flight stability analysis has proven to be a critical component of the initial envelope expansion.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-775 , 46th AIAA Atmospheric Flight Mechanics Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 56
    Publikationsdatum: 2019-07-13
    Beschreibung: Adaptive flight control systems have the potential to be resilient to extreme changes in airplane behavior. Extreme changes could be a result of a system failure or of damage to the airplane. The goal for the adaptive system is to provide an increase in survivability in the event that these extreme changes occur. A direct adaptive neural-network-based flight control system was developed for the National Aeronautics and Space Administration NF-15B Intelligent Flight Control System airplane. The adaptive element was incorporated into a dynamic inversion controller with explicit reference model-following. As a test the system was subjected to an abrupt change in plant stability simulating a destabilizing failure. Flight evaluations were performed with and without neural network adaptation. The results of these flight tests are presented. Comparison with simulation predictions and analysis of the performance of the adaptation system are discussed. The performance of the adaptation system is assessed in terms of its ability to stabilize the vehicle and reestablish good onboard reference model-following. Flight evaluation with the simulated destabilizing failure and adaptation engaged showed improvement in the vehicle stability margins. The convergent properties of this initial system warrant additional improvement since continued maneuvering caused continued adaptation change. Compared to the non-adaptive system the adaptive system provided better closed-loop behavior with improved matching of the onboard reference model. A detailed discussion of the flight results is presented.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 57
    Publikationsdatum: 2019-07-13
    Beschreibung: Over the past decade, the goal of reducing the fatal accident rate of large transport aircraft has resulted in research aimed at the problem of aircraft loss-of-control. Starting in 1999, the NASA Aviation Safety Program initiated research that included vehicle dynamics modeling, system health monitoring, and reconfigurable control systems focused on flight regimes beyond the normal flight envelope. In recent years, there has been an increased emphasis on adaptive control technologies for recovery from control upsets or failures including damage scenarios. As part of these efforts, NASA has developed the Airborne Subscale Transport Aircraft Research (AirSTAR) flight facility to allow flight research and validation, and system testing for flight regimes that are considered too risky for full-scale manned transport airplane testing. The AirSTAR facility utilizes dynamically-scaled vehicles that enable the application of subscale flight test results to full scale vehicles. This paper describes the modeling and simulation approach used for AirSTAR vehicles that supports the goals of efficient, low-cost and safe flight research in abnormal flight conditions. Modeling of aerodynamics, controls, and propulsion will be discussed as well as the application of simulation to flight control system development, test planning, risk mitigation, and flight research.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Atmospheric Flight Mechanics Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 58
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: A general overview of the Ikhana Uninhabited Air System (UAS) is presented. The contents include: 1) Ikhana UAS; 2) Ikhana UAS / Ground Control Station (GCS); 3) Ikhana UAS / Antennas; 4) Western States Fire Mission 2007 Partners; 5) FAA Certificate of Authorization (COA); 6) Western States Fire Missions (WSFM) 2007; 7) WSFM 1-4 2007; 8) California Wildfire Emergency Response 2007; 9) WSFM 5-8 Emergency Response 2007; 10) WSFM Achievements; and 11) WSFM Challenges.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: EAA AirVenture 2008 (Oshkosh); Jul 28, 2008 - Aug 03, 2008; Oshkosh, WI; United States
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  • 59
    Publikationsdatum: 2019-07-13
    Beschreibung: A flight control system architecture for the NASA AirSTAR infrastructure has been designed to address the challenges associated with safe and efficient flight testing of research control laws in adverse flight conditions. The AirSTAR flight control system provides a flexible framework that enables NASA Aviation Safety Program research objectives, and includes the ability to rapidly integrate and test research control laws, emulate component or sensor failures, inject automated control surface perturbations, and provide a baseline control law for comparison to research control laws and to increase operational efficiency. The current baseline control law uses an angle of attack command augmentation system for the pitch axis and simple stability augmentation for the roll and yaw axes.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 60
    Publikationsdatum: 2019-07-13
    Beschreibung: Formal robustness analysis of aircraft control upset prevention and recovery systems could play an important role in their validation and ultimate certification. As a part of the validation process, this paper describes an analysis method for determining a reliable flight regime in the flight envelope within which an integrated resilent control system can achieve the desired performance of tracking command signals and detecting additive faults in the presence of parameter uncertainty and unmodeled dynamics. To calculate a reliable flight regime, a structured singular value analysis method is applied to analyze the closed-loop system over the entire flight envelope. To use the structured singular value analysis method, a linear fractional transform (LFT) model of a transport aircraft longitudinal dynamics is developed over the flight envelope by using a preliminary LFT modeling software tool developed at the NASA Langley Research Center, which utilizes a matrix-based computational approach. The developed LFT model can capture original nonlinear dynamics over the flight envelope with the ! block which contains key varying parameters: angle of attack and velocity, and real parameter uncertainty: aerodynamic coefficient uncertainty and moment of inertia uncertainty. Using the developed LFT model and a formal robustness analysis method, a reliable flight regime is calculated for a transport aircraft closed-loop system.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 61
    Publikationsdatum: 2019-07-13
    Beschreibung: Results from a low Reynolds number wind tunnel experiment on a NACA 0015 airfoil with a 30% chord trailing edge flap tested at deflection angles of 0, 20, and 40 are presented and discussed. Zero net mass flux periodic excitation was applied at the ap shoulder to control flow separation for flap deflections larger than 0. The primary objective of the experiment was to compare force and moment data obtained from integrating surface pressures to data obtained from a 5-component strain-gage balance in preparation for additional three-dimensional testing of the model. To achieve this objective, active flow control is applied at an angle of attack of 6 where published results indicate that oscillatory momentum coefficients exceeding 1% are required to delay separation. Periodic excitation with an oscillatory momentum coefficient of 1.5% and a reduced frequency of 0.71 caused a significant delay of separation on the airfoil with a flap deflection of 20. Higher momentum coefficients at the same reduced frequency were required to achieve a similar level of flow attachment on the airfoil with a flap deflection of 40. There was a favorable comparison between the balance and integrated pressure force and moment results.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: 26th AIAA Applied Aerodynamics Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 62
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: This viewgraph presentation describes the adaptive and intelligent control methods used for aircraft survival. The contents include: 1) Motivation for Adaptive Control; 2) Integrated Resilient Aircraft Control Project; 3) Full-scale Flight Assets in Use for IRAC; 4) NASA NF-15B Tail Number 837; 5) Gen II Direct Adaptive Control Architecture; 6) Limited Authority System; and 7) 837 Flight Experiments. A simulated destabilization failure analysis along with experience and lessons learned are also presented.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NAVAIR Meeting; Feb 07, 2008; Edwards, CA; United States
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  • 63
    Publikationsdatum: 2019-07-13
    Beschreibung: In July 2005, Bell Helicopter won the U.S. Army's Armed Reconnaissance Helicopter competition to produce a replacement for the OH-58 Kiowa Warrior capable of performing the armed reconnaissance mission. To meet the U.S. Army requirement that the ARH-70A have Level 1 handling qualities for the scout rotorcraft mission task elements defined by ADS-33E-PRF, Bell equipped the aircraft with their generic automatic flight control system (AFCS). Under the constraints of the tight ARH-70A schedule, the development team used modem parameter identification and control law optimization techniques to optimize the AFCS gains to simultaneously meet multiple handling qualities design criteria. This paper will show how linear modeling, control law optimization, and simulation have been used to produce a Level 1 scout rotorcraft for the U.S. Army, while minimizing the amount of flight testing required for AFCS development and handling qualities evaluation of the ARH-70A.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: American Helicopter Society 63rd Annual Forum; May 01, 2007 - May 03, 2007; Virginia Beach, VA; United States
    Format: text
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  • 64
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: Full scale flight test forces designers to address real-world issues. Provides high-visibility demonstration. Adds credibility that adaptation technology can be a viable design option. Helps to separate the real from the imagined.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: Aviation Safety Conference; Oct 21, 2008; Denver, CO; United States
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  • 65
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: A broad overview of current adaptive flight control research efforts at NASA is presented, as well as some more detailed discussion of selected specific approaches. The stated objective of the Integrated Resilient Aircraft Control Project, one of NASA s Aviation Safety programs, is to advance the state-of-the-art of adaptive controls as a design option to provide enhanced stability and maneuverability margins for safe landing in the presence of adverse conditions such as actuator or sensor failures. Under this project, a number of adaptive control approaches are being pursued, including neural networks and multiple models. Validation of all the adaptive control approaches will use not only traditional methods such as simulation, wind tunnel testing and manned flight tests, but will be augmented with recently developed capabilities in unmanned flight testing.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: 14th Yale Workshop on Adaptive and Learning Systems; Jun 02, 2008 - Jun 05, 2008; New Haven, CT; United States
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  • 66
    Publikationsdatum: 2019-07-13
    Beschreibung: A maneuver design method that is particularly well-suited for determining the stability and control characteristics of hypersonic vehicles is described in detail. Analytical properties of the maneuver design are explained. The importance of these analytical properties for maximizing information content in flight data is discussed, along with practical implementation issues. Results from flight tests of the X-43A hypersonic research vehicle (also called Hyper-X) are used to demonstrate the excellent modeling results obtained using this maneuver design approach. A detailed design procedure for generating the maneuvers is given to allow application to other flight test programs.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: U.S. Air Force T&E Days; Feb 05, 2008 - Feb 07, 2008; Los Angeles, CA; United States
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  • 67
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper describes a combined control strategy designed to reduce sound radiation from stiffened aircraft-style panels. The control architecture uses robust active damping in addition to high-authority linear quadratic Gaussian (LQG) control. Active damping is achieved using direct velocity feedback with triangularly shaped anisotropic actuators and point velocity sensors. While active damping is simple and robust, stability is guaranteed at the expense of performance. Therefore the approach is often referred to as low-authority control. In contrast, LQG control strategies can achieve substantial reductions in sound radiation. Unfortunately, the unmodeled interaction between neighboring control units can destabilize decentralized control systems. Numerical simulations show that combining active damping and decentralized LQG control can be beneficial. In particular, augmenting the in-bandwidth damping supplements the performance of the LQG control strategy and reduces the destabilizing interaction between neighboring control units.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: Acoustics ''08 Paris Conference and Exhibition - 155th Acoustical Society of A; Jun 29, 2008 - Jul 04, 2008; Paris; France
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  • 68
    Publikationsdatum: 2019-07-13
    Beschreibung: The NASA Glenn Research Center (GRC) is developing an active damping at blade resonances using piezoelectric structure to reduce excessive vibratory stresses that lead to high cycle fatigue (HCF) failures in aircraft engine turbomachinery. Conventional passive damping work was shown first on a nonrotating beam made by Ti-6A1-4V with a pair of identical piezoelectric patches, and then active feedback control law was derived in terms of inductor, resister, and capacitor to control resonant frequency only. Passive electronic circuit components and adaptive feature could be easily programmable into control algorithm. Experimental active damping was demonstrated on two test specimens achieving significant damping on tip displacement and patch location. Also a multimode control technique was shown to control several modes.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2008-215212 , E-16486 , Paper no. 3124 , 2008 Propulsion-Safety and Affordable Readiness (P-SAR) Conference; Mar 18, 2008 - Mar 20, 2008; Myrtle Beach, SC; United States
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  • 69
    Publikationsdatum: 2019-07-13
    Beschreibung: Multivariable control allows controller designs that can provide decoupled command tracking and robust performance in the presence of modeling uncertainties. Although the last two decades have seen extensive development of multivariable control theory and example applications to complex systems in software/hardware simulations, there are no production flying systems aircraft or spacecraft, that use multivariable control. This is because of the tremendous challenges associated with implementation of such multivariable control designs. Unfortunately, the curriculum in schools does not provide sufficient time to be able to provide an exposure to the students in such implementation challenges. The objective of this paper is to share the lessons learned by a practitioner of multivariable control in the process of applying some of the modern control theory to the Integrated Flight Propulsion Control (IFPC) design for an advanced Short Take-Off Vertical Landing (STOVL) aircraft simulation.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2008-215027 , AIAA Paper-2007-6334 , E-16220 , Guidance, Navigation and Control Conference; Aug 20, 2007 - Aug 23, 2007; Hilton Head, SC; United States
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  • 70
    Publikationsdatum: 2019-07-12
    Beschreibung: A variable-structure control system designed to enable a fuselage-heavy airplane to recover from spin has been demonstrated in a hand-launched, instrumented model glider airplane. Variable-structure control is a high-speed switching feedback control technique that has been developed for control of nonlinear dynamic systems.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LAR-17106-1 , NASA Tech Briefs, July 2008; 21
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  • 71
    Publikationsdatum: 2019-07-13
    Beschreibung: In this paper we present an integrated approach to in-flight damage accommodation in flight control. The approach is based on Multiple Models, Switching and Tuning (MMST), and consists of three steps: In the first step the main objective is to acquire a realistic aircraft damage model. Modeling of in-flight damage is a highly complex problem since there is a large number of issues that need to be addressed. One of the most important one is that there is strong coupling between structural dynamics, aerodynamics, and flight control. These effects cannot be studied separately due to this coupling. Once a realistic damage model is available, in the second step a large number of models corresponding to different damage cases are generated. One possibility is to generate many linear models and interpolate between them to cover a large portion of the flight envelope. Once these models have been generated, we will implement a recently developed-Model Set Reduction (MSR) technique. The technique is based on parameterizing damage in terms of uncertain parameters, and uses concepts from robust control theory to arrive at a small number of "centered" models such that the controllers corresponding to these models assure desired stability and robustness properties over a subset in the parametric space. By devising a suitable model placement strategy, the entire parametric set is covered with a relatively small number of models and controllers. The third step consists of designing a Multiple Models, Switching and Tuning (MMST) strategy for estimating the current operating regime (damage case) of the aircraft, and switching to the corresponding controller to achieve effective damage accommodation and the desired performance. In the paper present a comprehensive approach to damage accommodation using Model Set Design,MMST, and Variable Structure compensation for coupling nonlinearities. The approach was evaluated on a model of F/A-18 aircraft dynamics under control effector damage, augmented by nonlinear cross-coupling terms and a structural dynamics model. The proposed approach achieved excellent performance under severe damage effects.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Paper 2008-6504 , LF99-7796 , AIAA Guidance, Navigation and Control Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 72
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents a stable discrete-time adaptive law that targets modeling errors in a direct adaptive control framework. The update law was developed in our previous work for the adaptive disturbance rejection application. The approach is based on the philosophy that without modeling errors, the original control design has been tuned to achieve the desired performance. The adaptive control should, therefore, work towards getting this performance even in the face of modeling uncertainties/errors. In this work, the baseline controller uses dynamic inversion with proportional-integral augmentation. Dynamic inversion is carried out using the assumed system model. On-line adaptation of this control law is achieved by providing a parameterized augmentation signal to the dynamic inversion block. The parameters of this augmentation signal are updated to achieve the nominal desired error dynamics. Contrary to the typical Lyapunov-based adaptive approaches that guarantee only stability, the current approach investigates conditions for stability as well as performance. A high-fidelity F-15 model is used to illustrate the overall approach.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN-171 , AlAA Guidance Navigation and Control Conference; Aug 18, 2008; Hawaii; United States
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  • 73
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-08-27
    Beschreibung: To control vortices originating at the tips of a rotor's blades rotating through the air at a revolution frequency f, separation control device(s) are actuated to periodically introduce perturbations into the airflow moving over the blades. The periodic introduction of perturbations is controlled in accordance with a periodic modulating frequency of introduction f.sub.0 while the frequency of the perturbations so-introduced is designated as f.sub.e. Vortex control is achieved when the periodic modulating frequency of introduction f.sub.0 satisfies the relationship nf.ltoreq.f.sub.0.ltoreq.f.sub.e where n is the number of blades.
    Schlagwort(e): Aircraft Stability and Control
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  • 74
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-19
    Beschreibung: This talk will present the motivation, research approach and status of intelligent control research for Next Generation Cruise Efficient Short Take Off and Landing (CESTOL) aircraft. An introduction to the challenges of CESTOL control will be given, leading into an assessment of potential control solutions. The approach of the control research will be discussed, including a brief overview of the technical aspects of the research.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: Fundamental Aeronautics Program Annual Meeting; Oct 08, 2008; Atlanta, GA; United States
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  • 75
    Publikationsdatum: 2019-07-13
    Beschreibung: The objective of this work is to leverage NASA resources to enable effective evaluation of resilient aircraft technologies through simulation. This includes examining strengths and weaknesses of adaptive controllers, emergency flight planning algorithms, and flight envelope determination algorithms both individually and as an integrated package.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN-213 , Aviation Safety Conference; Oct 21, 2008; Denver, CO; United States
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  • 76
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents a bounded linear stability analysis for a hybrid adaptive control that blends both direct and indirect adaptive control. Stability and convergence of nonlinear adaptive control are analyzed using an approximate linear equivalent system. A stability margin analysis shows that a large adaptive gain can lead to a reduced phase margin. This method can enable metrics-driven adaptive control whereby the adaptive gain is adjusted to meet stability margin requirements.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: ARC-E-DAA-TN119 , American Control Conference; Jun 11, 2008 - Jun 13, 2008; Seattle, WA; United States
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  • 77
    Publikationsdatum: 2019-07-13
    Beschreibung: The vortex hazard produced by large airliners and increasingly larger airliners entering service, combined with projected rapid increases in the demand for air transportation, is expected to act as a major impediment to increased air traffic capacity. Significant reduction in the vortex hazard is possible, however, by employing active vortex alleviation techniques that reduce the wake severity by dynamically modifying its vortex characteristics, providing that the techniques do not degrade performance or compromise safety and ride quality. With this as background, a series of experiments were performed, initially at NASA Langley Research Center and subsequently at the Berlin University of Technology in collaboration with the German Aerospace Center. The investigations demonstrated the basic mechanism for managing trailing vortices using retrofitted devices that are decoupled from conventional control surfaces. The basic premise for managing vortices advanced here is rooted in the erstwhile forgotten hypothesis of Albert Betz, as extended and verified ingeniously by Coleman duPont Donaldson and his collaborators. Using these devices, vortices may be perturbed at arbitrarily long wavelengths down to wavelengths less than a typical airliner wingspan and the oscillatory loads on the wings, and hence the vehicle, are small. Significant flexibility in the specific device has been demonstrated using local passive and active separation control as well as local circulation control via Gurney flaps. The method is now in a position to be tested in a wind tunnel with a longer test section on a scaled airliner configuration. Alternatively, the method can be tested directly in a towing tank, on a model aircraft, a light aircraft or a full-scale airliner. The authors believed that this method will have significant appeal from an industry perspective due to its retrofit potential with little to no impact on cruise (devices tucked away in the cove or retracted); low operating power requirements; small lift oscillations when deployed in a time-dependent manner; and significant flexibility with respect to the specific devices selected.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: LF99-7241 , 4th AIAA Flow Control Conference; Jun 23, 2008 - Jun 26, 2008; Seattle, WA; United States
    Format: application/pdf
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  • 78
    Publikationsdatum: 2019-07-13
    Beschreibung: Electronics for Distributed Turbine Engine Control and Space Exploration Missions are expected to encounter extreme temperatures and wide thermal swings. In particular, circuits deployed in a jet engine compartment are likely to be exposed to temperatures well exceeding 150 C. To meet this requirement, efforts exist at the NASA Glenn Research Center (GRC), in support of the Fundamental Aeronautics Program/Subsonic Fixed Wing Project, to develop temperature sensors geared for use in high temperature environments. The sensor and associated circuitry need to be located in the engine compartment under distributed control architecture to simplify system design, improve reliability, and ease signal multiplexing. Several circuits were designed using commercial-off-the-shelf as well as newly-developed components to perform temperature sensing at high temperatures. The temperature-sensing circuits will be described along with the results pertaining to their performance under extreme temperature.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: E-16795 , HiTEC 2008 High Temperature Electronics Conference/International Microelectronics and Packaging society (IMAPS); May 12, 2008 - May 15, 2008; Albuquerque, NM; United States
    Format: application/pdf
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  • 79
    facet.materialart.
    Unbekannt
    In:  Benutzerhandbuch fur @RISK Risikoanalysen- und Simulations- Add-InRisikoanalysen Add-In für Microsoft® Excel Version 5.7, September, 2010 Palisade Corporation 798 Cascadilla Street Ithaca, NY 14850 USA
    Publikationsdatum: 2007
    Beschreibung: Korrelationsanalyse zwischen Wettervariablen über mehrere Perioden und dem Zuckerrübenertrag an verschiedenen Standorten KATASTER-BESCHREIBUNG: Bildung von Wetterindexsummen über mehrere Monate im Vergleich zur Betrachtung einzelner Monate ergab keine höheren Korrelationen, höchste positive Korrelationskoeffizienten von 0,61 zwischen der Niederschlagssumme des Zeitraumes Juni bis August für den Standort Dedelow, in der Uckermark Brandesburgs. Einflusses der Temperatur auf den Zuckerertrag ergab negative Korrelationskoeffizienten, der höchste (negative) ermittelte Wert liegt bei -0,78 für die Periode Juli bis September, Dedelow. Positiven Einfluss hoher Temperaturen auf den Rübenertrag am Standort Kiel und Düse KATASTER-DETAIL:
    Schlagwort(e): Deutschland, teilw. einzelne Regionen ; 1958-2006 ; Zuckerrüben ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur
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  • 80
    Publikationsdatum: 2007
    Beschreibung: Studie zu einer prognostizierten Anzahl von Tagen mit Wärme- und mit Kältestress, basierend auf Klimaszenarien für den Zeitraum 2071 bis 2100 KATASTER-BESCHREIBUNG: Prognose: größere Zahl an Todesfällen durch Hitze im Süden gegenüber dem Norden Deutschlands und zugleich größerer Rückgang der Todesfälle durch Kälte im Norden, Anstieg der Todesopferzahl durch zunehmende Hitze insgesamt größer als Rückgang der Opferzahl durch weniger Kälte KATASTER-DETAIL:
    Schlagwort(e): Deutschland ; Umweltmedizin ; Temperatur
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  • 81
    facet.materialart.
    Unbekannt
    In:  2 -NAP 02-231 Bericht IV Interreg IIIA Literaturstudie alpine Kulturpflanzen Vs. 3.0 070425.
    Publikationsdatum: 2007
    Beschreibung: Sammlung historischer Informationen und Dokumentation des bäuerlichen Erfahrungswissens Kulturpflanzen von der Prähistorie - 20. Jahrhundert KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Schlagwort(e): Südtirol, Nordtirol und GraubündenSüdtirol, Nordtirol und Graubünden ; Kartoffeln ; Anbautermine ; Boden ; Ertrag ; Getreide ; Hafer ; Klima ; Landwirtschaft ; Mais ; Niederschlag ; Pflanzenkrankheit ; Pflanzenschädling ; Roggen ; Temperatur ; Trockenheit ; Vegetationsperiode ; Weizen ; Wetterbeobachtung ; Witterung ; Düngung ; Hackfrüchte
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  • 82
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2018-06-06
    Beschreibung: A guidance and control method was developed to detect and exploit thermals for energy gain. Latency in energy rate estimation degraded performance. The concept of a UAV harvesting energy from the atmosphere has been shown to be feasible with existing technology. Many UAVs have similar mission constraints to birds and sailplanes. a) Surveillance; b) Point to point flight with minimal energy; and c) Increased ground speed.
    Schlagwort(e): Aircraft Stability and Control
    Format: text
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  • 83
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2018-06-06
    Beschreibung: The primary objective of the UAVSAR Project is to develop a miniaturized polarimetric L-band synthetic aperture radar (SAR) for use on an unmanned aerial vehicle (UAV) or minimally piloted vehicle. This viewgraph presentation reviews NASA Dryden's role in the UAVSAR program. The G-III aircraft is described and shown, as well as a high level system architecture. The goals of the Platform Precision Autopilot (PPA) that it are shall fly the G-III within a 10 m (32.8 ft) diameter tube for at least 90% of each data take in conditions of calm to light atmospheric disturbances, as defined in MIL-STD-1797. That it minimize motion during data collection. It is critical to operate the UAVSAR System on a steady platform.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 84
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2018-06-06
    Beschreibung: This viewgraph presentation reviews the use of Intelligent Flight Control System (IFCS) for the F-15. The goals of the project are: (1) Demonstrate Revolutionary Control Approaches that can Efficiently Optimize Aircraft Performance in both Normal and Failure Conditions (2) Advance Neural Network-Based Flight Control Technology for New Aerospace Systems Designs. The motivation for the development are to reduce the chance and skill required for survival.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 85
    Publikationsdatum: 2018-06-06
    Beschreibung: A guidance and control method was developed to detect and exploit thermals for energy gain. Latency in energy rate estimation degraded performance. The concept of a UAV harvesting energy from the atmosphere has been shown to be feasible with existing technology. Many UAVs have similar mission constraints to birds and sailplanes. a) Surveillance; b) Point to point flight with minimal energy; and c) Increased ground speed.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 86
    Publikationsdatum: 2019-07-19
    Beschreibung: The Department of Homeland Security (DHS) created the PCAR (Propulsion-Controlled Aircraft Recovery) project in 2005 to mitigate the ManPADS (man-portable air defense systems) threat to the commercial aircraft fleet with near-term, low-cost proven technology. Such an attack could potentially cause a major FCS (flight control system) malfunction or other critical system failure onboard the aircraft, despite the extreme reliability of current systems. For the situations in which nominal flight controls are lost or degraded, engine thrust may be the only remaining means for emergency flight control [ref 1]. A computer-controlled thrust system, known as propulsion-controlled aircraft (PCA), was developed in the mid 1990s with NASA, McDonnell Douglas and Honeywell. PCA's major accomplishment was a demonstration of an automatic landing capability using only engine thrust [ref 11. Despite these promising results, no production aircraft have been equipped with a PCA system, due primarily to the modifications required for implementation. A minimally invasive option is TOC (throttles-only control), which uses the same control principles as PCA, but requires absolutely no hardware, software or other aircraft modifications. TOC is pure piloting technique, and has historically been utilized several times by flight crews, both military and civilian, in emergency situations stemming from a loss of conventional control. Since the 1990s, engineers at NASA Dryden Flight Research Center (DFRC) have studied TOC, in both simulation and flight, for emergency flight control with test pilots in numerous configurations. In general, it was shown that TOC was effective on certain aircraft for making a survivable landing. DHS sponsored both NASA Dryden Flight Research Center (Edwards, CA) and United Airlines (Denver, Colorado) to conduct a flight and simulation study of the TOC characteristics of a twin-jet commercial transport, and assess the ability of a crew to control an aircraft down to a survivable runway landing using TOC. The PCAR project objective was a set of pilot procedures for operation of a specific aircraft without hydraulics that (a) have been validated in both simulation and flight by relevant personnel, and (b) mesh well with existing commercial operations, maintenance, and training at a minimum cost. As a result of this study, a procedure has been developed to assist a crew in making a survivable landing using TOC. In a simulation environment, line pilots with little or no previous TOC experience performed survivable runway landings after a few practice TOC approaches. In-flight evaluations put line pilots in a simulated emergency situation where TOC was used to recover the aircraft, maneuver to a landing site, and perform an approach down to 200 feet AGL. The results of this research, including pilot observations, procedure comments, recommendations, future work and lessons learned, will he discussed. Flight data and video footage of TOC approaches may also be shown.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-650 , International Test and Evaluation Association; Nov 12, 2007 - Nov 15, 2007; Hawaii
    Format: text
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  • 87
    Publikationsdatum: 2019-07-19
    Beschreibung: The NASA Unmanned Aerial Vehicle Synthetic Aperture Radar (UAVSAR) program is developing a Synthetic Aperture Radar (SAR) for ground measurements. A key element for the success of this program is a Platform Precision Autopilot (PPA). An interim vehicle (NASA C-20AJGlll) was selected to carry the radar pod and develop the PPA. The PPA interfaces with the C- 20AIG Ill aircraft by imitating the output of an Instrument Landing System (ILS) approach. This technique retains the safeguards in the aircraft's autopilot. The PPA entered initial flight testing in early 2007. The PPA uses a Kalman filter to generate a real-time position solution with information from the C-20AIGIII and a real-time differential GPS unit designed by JPL. The real-time navigation solution is used to compute commands (Guidance and Control subsystems) which in turn drive two modified ILS testers. The ILS tester units produce modulated RF signals fed to the onboard navigation receiver. These correction signals allow the C-20NGIII autopilot to fly a simulated ILS approach that meets the PPA requirements for UAVSAR applications. The PPA requirement is to make repeat pass flights within a ten meter tube over a 200 kilometer course in conditions of cairn to light turbulence. Flight test results are expected to be available at the time of the NASA Science Technology Conference 2007
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-658 , 2007 NASA Science Technology Conference; Jun 19, 2007 - Jun 21, 2007; Adelphia, MD; United States
    Format: text
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  • 88
    Publikationsdatum: 2019-07-19
    Beschreibung: The primary objective of the Quiet Spike flight research program was the aerodynamic and structural proof-of-concept of a telescoping, 24 ft, sonic-boom suppressing nose boom on a F-15B aircraft. The program goal was to collect flight data for model validation up to 1.8 Mach. In the area of stability and controls the primary concern was to assess the effect of the spike on the stability, controllability and handling qualities of the aircraft. The primary goal of this test philosophy was maintaining safety of flight. Two main issues are discussed in this paper: the stability and controls approach and analysis in the presence of uncertain spike influenced aerodynamics on the F-15B aircraft flight dynamics; and the analysis of F-15B flight dynamics implications due to spike induced air flow in the vicinity of air data and angle-of-attack sensors. Also addressed are flight test implications based on the analysis
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-654
    Format: text
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  • 89
    Publikationsdatum: 2019-07-19
    Beschreibung: This paper describes the performance of a simplified dynamic inversion controller with neural network supplementation. This 6 DOF (Degree-of-Freedom) simulation study focuses on the results with and without adaptation of neural networks using a simulation of the NASA modified F-15 which has canards. One area of interest is the performance of a simulated surface failure while attempting to minimize the inertial cross coupling effect of a [B] matrix failure (a control derivative anomaly associated with a jammed or missing control surface). Another area of interest and presented is simulated aerodynamic failures ([A] matrix) such as a canard failure. The controller uses explicit models to produce desired angular rate commands. The dynamic inversion calculates the necessary surface commands to achieve the desired rates. The simplified dynamic inversion uses approximate short period and roll axis dynamics. Initial results indicated that the transient response for a [B] matrix failure using a Neural Network (NN) improved the control behavior when compared to not using a neural network for a given failure, However, further evaluation of the controller was comparable, with objections io the cross coupling effects (after changes were made to the controller). This paper describes the methods employed to reduce the cross coupling effect and maintain adequate tracking errors. The IA] matrix failure results show that control of the aircraft without adaptation is more difficult [leas damped) than with active neural networks, Simulation results show Neural Network augmentation of the controller improves performance in terms of backing error and cross coupling reduction and improved performance with aerodynamic-type failures.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: DFRC-599 , AIAA Infotech@Aerospace 2007 Conference and Exhibit; May 07, 2007 - May 10, 2007; Rohnert Park, CA; United States
    Format: text
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  • 90
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-12
    Beschreibung: A piloted, fixed-base simulation was conducted in 2006 to determine optimum rudder pedal force/feel characteristics for transport aircraft. As part of this research, an evaluation of four metrics for assessing rudder pedal characteristics previously presented in the literature was conducted. This evaluation was based upon the numerical handling qualities ratings assigned to a variety of pedal force/feel systems used in the simulation study. It is shown that, with the inclusion of a fifth metric, most of the rudder pedal force/feel system designs that were rated poorly by the evaluation pilots could be identified. It is suggested that these metrics form the basis of a certification requirement for transport aircraft.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 91
    Publikationsdatum: 2019-08-13
    Beschreibung: A method and system for data modeling that incorporates the advantages of both traditional response surface methodology (RSM) and neural networks is disclosed. The invention partitions the parameters into a first set of s simple parameters, where observable data are expressible as low order polynomials, and c complex parameters that reflect more complicated variation of the observed data. Variation of the data with the simple parameters is modeled using polynomials; and variation of the data with the complex parameters at each vertex is analyzed using a neural network. Variations with the simple parameters and with the complex parameters are expressed using a first sequence of shape functions and a second sequence of neural network functions. The first and second sequences are multiplicatively combined to form a composite response surface, dependent upon the parameter values, that can be used to identify an accurate mode
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 92
    Publikationsdatum: 2019-07-13
    Beschreibung: This viewgraph presentation reviews NASA Dryden's role in the UAVSAR Program. The primary objective of the UAVSAR Project is to develop a miniaturized polarimetric L-band synthetic aperture radar (SAR) for use on an unmanned aerial vehicle (UAV) or minimally piloted vehicle. Dryden's work in developing the Platform Precision Autopilot (PPA) capability is described in this presentation. The goal for the development is that the PPA shall fly the G-III within a 10 m (32.8 ft) diameter tube for at least 90% of each data take in conditions of calm to light atmospheric disturbances, as defined. The G-III aircraft is descrbed, the test plan is outlined, and the initial test results are reviewed.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NSTC 2007 - 1st Annual NASA Science Technology Conference; Jun 19, 2007 - Jun 23, 2007; Adelphi, MD; United States
    Format: text
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  • 93
    Publikationsdatum: 2019-07-13
    Beschreibung: We compared two possible implementations of local linear models for control: one approach is based on a self-organizing map (SOM) to cluster the dynamics followed by a set of linear models operating at each cluster. Therefore the gating function is hard (a single local model will represent the regional dynamics). This simplifies the controller design since there is a one to one mapping between controllers and local models. The second approach uses a soft gate using a probabilistic framework based on a Gaussian Mixture Model (also called a dynamic mixture of experts). In this approach several models may be active at a given time, we can expect a smaller number of models, but the controller design is more involved, with potentially better noise rejection characteristics. Our experiments showed that the SOM provides overall best performance in high SNRs, but the performance degrades faster than with the GMM for the same noise conditions. The SOM approach required about an order of magnitude more models than the GMM, so in terms of implementation cost, the GMM is preferable. The design of the SOM is straight forward, while the design of the GMM controllers, although still reasonable, is more involved and needs more care in the selection of the parameters. Either one of these locally linear approaches outperform global nonlinear controllers based on neural networks, such as the time delay neural network (TDNN). Therefore, in essence the local model approach warrants practical implementations. In order to call the attention of the control community for this design methodology we extended successfully the multiple model approach to PID controllers (still today the most widely used control scheme in the industry), and wrote a paper on this subject. The echo state network (ESN) is a recurrent neural network with the special characteristics that only the output parameters are trained. The recurrent connections are preset according to the problem domain and are fixed. In a nutshell, the states of the reservoir of recurrent processing elements implement a projection space, where the desired response is optimally projected. This architecture trades training efficiency by a large increase in the dimension of the recurrent layer. However, the power of the recurrent neural networks can be brought to bear on practical difficult problems. Our goal was to implement an adaptive critic architecture implementing Bellman s approach to optimal control. However, we could only characterize the ESN performance as a critic in value function evaluation, which is just one of the pieces of the overall adaptive critic controller. The results were very convincing, and the simplicity of the implementation was unparalleled.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 94
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-07-13
    Beschreibung: The effect of individual blade control (IBC) on the full-scale, low airspeed, level flight UH-60A oscillatory fixed system 4P hub loads and the rotating system blade bending moments is studied. The effect of a single 3P IBC input has been considered in this analytical study. At the low speed under consideration, it has been found that convergence of the comprehensive analysis is important for obtaining good predictions. Good correlation has been obtained with the measured full-scale wind tunnel data for the shapes of the fixed system 4P hub loads variations with the 3P IBC input phase, and also for the "best" phase of the 3P input (for minimum hub loads). The blade bending moment comparison shows mixed results. The 3P lead lag and the 4P flap bending moment trends with the 3P IBC input phase are reasonably predicted, whereas the 5P lead lag bending moment trend is not predicted well. Finally, the prediction of the baseline (no IBC) bending moments needs further study.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: American Helicopter Society 63rd Annual Forum; May 01, 2007 - May 03, 2007; Virginia Beach, VA; United States
    Format: text
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  • 95
    Publikationsdatum: 2019-07-13
    Beschreibung: Adaptive flight control systems have the potential to be more resilient to extreme changes in airplane behavior. Extreme changes could be a result of a system failure or of damage to the airplane. A direct adaptive neural-network-based flight control system was developed for the National Aeronautics and Space Administration NF-15B Intelligent Flight Control System airplane and subjected to an inflight simulation of a failed (frozen) (unmovable) stabilator. Formation flight handling qualities evaluations were performed with and without neural network adaptation. The results of these flight tests are presented. Comparison with simulation predictions and analysis of the performance of the adaptation system are discussed. The performance of the adaptation system is assessed in terms of its ability to decouple the roll and pitch response and reestablish good onboard model tracking. Flight evaluation with the simulated stabilator failure and adaptation engaged showed that there was generally improvement in the pitch response; however, a tendency for roll pilot-induced oscillation was experienced. A detailed discussion of the cause of the mixed results is presented.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2007-214629 , H-2751 , AIAA-2007-2818 , AIAA 2007 Conference and Exhibit; May 07, 2007 - May 10, 2007; Rohnert Park, CA; United States
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  • 96
    Publikationsdatum: 2019-07-13
    Beschreibung: The Pegasus wing-glove flight experiment was designed to provide crossflow transition data at high Mach numbers, specifically to help validate stability based predictions for transition onset in a flight environment. This paper provides an analysis of the flight experiment, with emphasis on computational results for crossflow disturbances and the correlation of disturbance growth factors with in-flight transition locations via the e(sup N) method. Implications of the flight data for attachment line stability are also examined. Analysis of the thermocouple data reveals that transition (from turbulent to laminar flow) was first detected during the ascending flight of the rocket when the free stream Mach number exceeded about 4. Therefore, computations have been performed for flight Mach numbers of 4.13, 4.35, 4.56 and 4.99. Due to continually decreasing unit Reynolds number at higher altitudes, the entire wing-glove boundary layer became laminar at the highest flight Mach number computed above. In contrast, the boundary layer flow over the inboard tile region remained transitional up to and somewhat beyond the time of laminarization over the instrumented glove region. Linear stability predictions confirmed that the tile boundary layer is indeed more unstable to crossflow disturbances than the much colder stainless steel glove boundary layer. The transition locations based on thermocouple data from both the glove and the tile regions are found to correlate with stationary-crossflow N-factors within the range of 7 to 12.4 and with traveling mode N-factors between 7.6 and 14.1. Data from the thermocouples and hot film sensors indicates that transition from turbulent to laminar flow (i.e., laminarization) at a fixed point over the glove is generally completed within a flight time interval of 3 seconds. However, the times at which transition begins and ends as inferred from the hot film sensors are found to differ by about 2 seconds from the corresponding estimates based on the thermocouple data.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Paper-2007-4487 , 37th AIAA Fluid Dynamics Conference and Exhibit; Jun 25, 2007 - Jun 28, 2007; Miami, FL; United States
    Format: application/pdf
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  • 97
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: A viewgraph presentation on the satus of NASA Dryden's aircraft guidance and control is shown. The topics include: 1) Autonomous Airborne Refueling Demonstration (AARD); 2) Ikhana Project Update; 3) Quiet Spike; 4) F-15 Intelligent Flight Control System; 5) C-20A Precision Autopilot Development; and 6) X-48 Blended Wing Body.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: SAE Aerospace Control and Guidance Sub-committee System Conference; Feb 28, 2007 - Mar 02, 2007; Williamsburg, VA; United States
    Format: application/pdf
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  • 98
    Publikationsdatum: 2019-07-13
    Beschreibung: The angle measurement system (AMS) developed at NASA Langley Research Center (LaRC) is a system for many uses. It was originally developed to check taper fits in the wind tunnel model support system. The system was further developed to measure simultaneous pitch and roll angles using 3 orthogonally mounted accelerometers (3-axis). This 3-axis arrangement is used as a transfer standard from the calibration standard to the wind tunnel facility. It is generally used to establish model pitch and roll zero and performs the in-situ calibration on model attitude devices. The AMS originally used a laptop computer running DOS based software but has recently been upgraded to operate in a windows environment. Other improvements have also been made to the software to enhance its accuracy and add features. This paper will discuss the accuracy and calibration methodologies used in this system and some of the features that have contributed to its popularity.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: AIAA Paper 2007-1162 , 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
    Format: application/pdf
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  • 99
    Publikationsdatum: 2019-07-12
    Beschreibung: A method transmitting a message over at least one of a plurality of radio frequency (RF) channels of an RF communications network is provided. The method comprises the steps of detecting a presence of jamming pulses in the at least one of the plurality of RF channels. The characteristics of the jamming pulses in the at least one of the plurality of RF channels is determined wherein the determined characteristics define at least interstices between the jamming pulses. The message is transmitted over the at least one of the plurality of RF channels wherein the message is transmitted within the interstices of the jamming pulse determined from the step of determining characteristics of the jamming pulses.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
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  • 100
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-12
    Beschreibung: Thermals caused by convection in the lower atmosphere are commonly used by birds and glider pilots to extend flight duration, increase cross-country speed, improve range, or simply to conserve energy. Uninhabited Aerial Vehicles (UAVs) can also increase performance and reduce energy consumption by exploiting atmospheric convection. An autonomous soaring research project was conducted at the NASA Dryden Flight Research Center to evaluate the concept through flight test of an electric-powered motorglider with a wingspan of 4.27 m (14 ft). The UAV's commercial autopilot software was modified to include outer-loop soaring guidance and control. The aircraft total energy state was used to detect and soar within thermals. Estimated thermal size and position were used to calculate guidance commands for soaring flight. Results from a total of 23 thermal encounters show good performance of the guidance and control algorithms to autonomously detect and exploit thermals. The UAV had an average climb of 172 m (567 ft) during these encounters.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA/TM-2007-214611/REV1 , H-2714
    Format: application/pdf
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