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  • 1
    Electronic Resource
    Electronic Resource
    Dominance and the social behavior of adult female bonnet macaques (Macaca radiata) (1981)
    Springer
    Primates 22 (1981), S. 368-378 
    Details
    ISSN: 0032-8332
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology
    Notes: Abstract Female bonnet macaques are ranked according to naturally occurring dyadic aggressive interactions. Several possible correlates of these ranks are examined. Maternal rank and early life history are found to be highly correlated with rank. In addition, a number of social relationships (female/female presentations, female/female mounts, contact among females and aggression) are found to be related to rank. The meaning of rank outside of head to head encounters is discussed.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF02381577
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Effect of aeroelastic-propulsive interactions on flight dynamics of a hypersonic vehicle (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The desire to achieve orbit-on-demand access to space with rapid turn-around capability and aircraft-like processing operations has given rise to numerous hypersonic aerospace plane design concepts which would take off horizontally from a conventional runway and employ air-breathing scramjet propulsion systems for acceleration to orbital speeds. Most of these air-breathing hypersonic vehicle concepts incorporate an elongated fuselage forebody to act as the aerodynamic compression surface for a scramjet combustor module. This type of airframe-integrated scramjet propulsion system tends to be highly sensitive to inlet conditions and angle-of-attack perturbations. Furthermore, the basic configuration of the fuselage, with its elongated and tapered forebody, produces relatively low frequency elastic modes which will cause perturbations in the combustor inlet conditions due to the oscillation of the forebody compression surface. The flexibility of the forebody compression surface, together with sensitivity of scramjet propulsion systems to inlet conditions, creates the potential for an unprecedented form of aeroelastic-propulsive interaction in which deflections of the vehicle fuselage give rise to propulsion transients, producing force and moment variations that may adversely impact the longitudinal flight dynamics and/or excite the elastic modes. These propulsive force and moment variations may have an appreciable impact on the performance, guidance, and control of a hypersonic aerospace plane. The objectives of this research are to quantify the magnitudes of propulsive force and moment perturbations resulting from elastic deformation of a representative hypersonic vehicle, and to assess the potential impact of these perturbations on the vehicle's longitudinal flight dynamics.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA LaRC Workshop on Guidance, Navigation, Controls, and Dynamics for Atmospheric Flight, 1993; p 459-472
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of piloting aids for manual control of hypersonic maneuvers (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of piloting aids designed to provide precise maneuver control for an air-breathing hypersonic vehicle is described. Stringent constraints and nonintuitive high-speed flight effects associated with maneuvering in the hypersonic regime raise the question of whether manual control of such a vehicle should even be considered. The objectives of this research were to determine the extent of manual control that is desirable for a vehicle maneuvering in this regime and to identify the form of aids that must be supplied to the pilot to make such control feasible. A piloted real-time motion-based simulation of a hypersonic vehicle concept was used for this study, and the investigation focused on a single representative cruise turn maneuver. Piloting aids, which consisted of an auto throttle, throttle director, autopilot, flight director, and two head-up display configurations, were developed and evaluated. Two longitudinal control response types consisting of a rate-command/attitude-hold system and a load factor-rate/load-factor-hold system were also compared. The complete set of piloting aids, which consisted of the autothrottle, throttle director, and flight director, improved the average Cooper-Harper flying qualities ratings from 8 to 2.6, even though identical inner-loop stability and control augmentation was provided in all cases. The flight director was determined to be the most critical of these aids, and the cruise turn maneuver was unachievable to adequate performance specifications in the absence of this flight director.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-3525 , NAS 1.60:3525 , L-17446
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Control integration concept for hypersonic cruise-turn maneuvers (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Piloting difficulties associated with conducting aircraft maneuvers in hypersonic flight are caused in part by the nonintuitive nature of the aircraft response and the stringent constraints anticipated on allowable angle of attack and dynamic pressure variations. An approach is documented that provides precise, coordinated maneuver control during excursions from a hypersonic cruise flight path and the necessary flight condition constraints. The approach is to achieve specified guidance commands by resolving altitude and cross range errors into a load factor and bank angle command by using a coordinate transformation that acts as an interface between outer and inner loop flight controls. This interface, referred to as a 'resolver', applies constraints on angle of attack and dynamic pressure perturbations while prioritizing altitude regulation over cross range. An unpiloted test simulation, in which the resolver was used to drive inner loop flight controls, produced time histories of responses to guidance commands and atmospheric disturbances at Mach numbers of 6, 10, 15, and 20. Angle of attack and throttle perturbation constraints, combined with high speed flight effects and the desire to maintain constant dynamic pressure, significantly impact the maneuver envelope for a hypersonic vehicle.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-3136 , L-16928 , NAS 1.60:3136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Control concept for maneuvering in hypersonic flight (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This research investigates an approach to provide precise, coordinated maneuver control during excursions from a hypersonic cruise flight path while observing the necessary flight condition constraints. The approach achieves specified guidance commands by resolving altitude and cross-range errors into a load factor and bank angle command through a coordinate transformation which acts as an interface between outer loop guidance controls and inner loop flight controls. This interface, referred to as a 'resolver', applies constraints on angle-of-attack and dynamic pressure perturbations while prioritizing altitude regulation over crossrange. An unpiloted test simulation, in which the resolver was used to drive inner-loop flight controls, produced time histories of responses to guidance commands at Mach numbers of 6, 10, 15, and 20. It is shown that angle-of-attack and throttle perturbation constraints, combined with high-speed flight effects and the desire to maintain constant dynamic pressure, significantly impact the maneuver envelope for a hypersonic vehicle. Turn rate, climb rate, and descent rate limits are expressed in terms of these constraints.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-5055
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Research Activities within NASA's Morphing Program (2000)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: In the last decade, smart technologies have become important enabling technologies that cut across traditional boundaries in science and engineering. Here smart is defined as the ability to respond to a stimulus in a predictable and reproducible manner. While multiple successes have been achieved in the laboratory, we have yet to see the general applicability of smart technologies to actual aircraft and spacecraft. The NASA Morphing program is an attempt to couple research across a wide range of disciplines to integrate smart technologies into high payoff applications on aircraft and spacecraft. The program bridges research in several technical disciplines and combines the effort into applications that include active aerodynamic control, active aeroelastic control, and vehicle performance improvement. System studies are used to assess the highest-payoff program objectives, and specific research activities are defined to address the technologies required for development of smart aircraft and spacecraft. This paper will discuss the overall goals of NASA's Morphing program, highlight some of the recent research efforts and discuss the multidisciplinary studies that support that research and some of the challenges associated with bringing the smart technologies to real applications on flight vehicles.
    Keywords: Aeronautics (General)
    Type: Structural Aspects of Flexible Aircraft Control; 13-1 - 13-10; RTO-MP-36
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Lateral stability analysis for X-29A drop model using system identification methodology (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 22-percent dynamically scaled replica of the X-29A forward-swept-wing airplane has been flown in radio-controlled drop tests at the NASA Langley Research Center. A system identification study of the recorded data was undertaken to examine the stability and control derivatives that influence the lateral behavior of this vehicle with particular emphasis on an observed wing rock phenomenon. All major lateral stability derivatives and the damping-in-roll derivative were identified for angles of attack from 5 to 80 degrees by using a data-partitioning methodology and a modified stepwise regression algorithm.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-4108 , L-16471 , NAS 1.15:4108
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Impact of aeroelasticity on propulsion and longitudinal flight dynamics of an air-breathing hypersonic vehicle (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Many air-breathing hypersonic aerospacecraft design concepts incorporate an elongated fuselage forebody acting as the aerodynamic compression surface for a hypersonic combustion module, or scram jet. This highly integrated design approach creates the potential for an unprecedented form of aero-propulsive-elastic interaction in which deflections of the vehicle fuselage give rise to propulsion transients, producing force and moment variations that may adversely impact the rigid body flight dynamics and/or further excite the fuselage bending modes. To investigate the potential for such interactions, a math model was developed which included the longitudinal flight dynamics, propulsion system, and first seven elastic modes of a hypersonic air-breathing vehicle. Perturbation time histories from a simulation incorporating this math model are presented that quantify the propulsive force and moment variations resulting from aeroelastic vehicle deflections. Root locus plots are presented to illustrate the effect of feeding the propulsive perturbations back into the aeroelastic model. A concluding section summarizes the implications of the observed effects for highly integrated hypersonic air-breathing vehicle concepts.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 93-1367 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1; p. 628-637.
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis of lateral stability of X-29 drop model using system identification methodology (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A 22-percent dynamically scaled replica of the X-29 forward-swept-wing aircraft is currently being flown in radio-controlled drop tests at NASA Langley's Plumtree Test Site. Flight data were recorded from early flights in the test program, which consisted mainly of large amplitude maneuvers over wide angle-of-attack ranges with several uncontrolled wing rock episodes. A system identification study of the recorded data was undertaken to examine the stability and control derivatives which influence the lateral behavior of this vehicle with particular emphasis on the wing rock phenomenon. All major lateral stability derivatives and the damping-in-roll derivative were identified for 5-80 deg angle-of-attack by using a data partitioning methodology and a modified stepwise regression algorithm. No control effectiveness derivatives could be identified from the flights conducted so far.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2625
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Wind Tunnel Test of an RPV with Shape-Change Control Effector and Sensor Arrays (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A variety of novel control effector concepts have recently emerged that may enable new approaches to flight control. In particular, the potential exists to shift the composition of the typical aircraft control effector suite from a small number of high authority, specialized devices (rudder, aileron, elevator, flaps), toward larger numbers of smaller, less specialized, distributed device arrays. The concept envisions effector and sensor networks composed of relatively small high-bandwidth devices able to simultaneously perform a variety of control functions using feedback from disparate data sources. To investigate this concept, a remotely piloted flight vehicle has been equipped with an array of 24 trailing edge shape-change effectors and associated pressure measurements. The vehicle, called the Multifunctional Effector and Sensor Array (MESA) testbed, was recently tested in NASA Langley's 12-ft Low Speed wind tunnel to characterize its stability properties, control authorities, and distributed pressure sensitivities for use in a dynamic simulation prior to flight testing. Another objective was to implement and evaluate a scheme for actively controlling the spanwise pressure distribution using the shape-change array. This report describes the MESA testbed, design of the pressure distribution controller, and results of the wind tunnel test.
    Keywords: Aerodynamics
    Type: AIAA Paper 2004-5114 , AIAA Guidance, Navigation and Control Conference; Aug 16, 2004 - Aug 19, 2004; Providence, RI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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