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  • 1
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    Selected design issues of some high speed rotorcraft concepts (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study of vehicle concepts for High Speed Rotorcraft applications has been undertaken at Ames Research Center in cooperation with NASA Lewis and Langley Centers, with the objective of defining their technology needs. The design guidelines include a low downwash velocity in hover, good low speed maneuver capabilities and cruise speeds up to 450 knots. Four contractors and a systems analysis effort within NASA have defined promising configurations which may be capable of meeting these goals. This paper addresses challenging problems associated with some of the configurations in the areas of aerodynamics, propulsion, weights and aeroelastic stability.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-3297
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A mathematical model of a tilt-wing aircraft for piloted simulation (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model of a tilt-wing aircraft that was used in a piloted, six-degree-of-freedom flight simulation application is described. Two types of control systems developed for the math model are discussed: a conventional, programmed-flap wing-tilt control system and a geared-flap wing-tilt control system. The primary objective was to develop the capability to study tilt-wing aircraft. Experienced Tilt-wing pilots subjectively evaluated the model using programmed-flap control to assess the quality of the simulation. The math model was then applied to study geared-flap control to investigate the possibility of eliminating the need for auxilary pitch-control devices (such as the horizontal tail rotor or tail jet used in earlier tilt-wing designs). This investigation was performed in the moving-base simulation environment, and the vehicle responses with programmed-flap and geared-flap control were compared. The results of the evaluation of the math model are discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-103864 , A-91150 , NAS 1.15:103864
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Description of a tilt wing mathematical model for piloted simulation (1991)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: A tilt-wing mathematical model that was used in a piloted six-deg-of-freedom flight simulation application is presented. Two types of control systems developed for the model - a conventional programmed-flap wing-tilt control system and a geared-flap wing-tilt control system - are discussed. The objective of this effort was to develop the capability to study tilt-wing aircraft. Experienced tilt-wing pilots subjectively evaluated the model using programmed-flap control to assess the quality of the simulation. The objective was met and the model was then applied to study geared-flap control to investigate the possibility of eliminating the need for auxiliary pitch control devices. This was performed in the moving-base simulation environment, and the vehicle responses with programmed-flap and geared-flap control were compared.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Control of a human-powered helicopter in hover (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The study of a control system for the Da Vinci 2 human-powered helicopter in hovering flight is documented. This helicopter has two very large, slowly rotating rotor blades and is considered to be unstable in hover. The control system is designed to introduce stability in hover by maintaining level rotors through the use of rotor tip mounted control surfaces. A five degree of freedom kinematic model was developed to study this control system and is documented. Results of this study show that the unaugmented configuration is unstable due to the large Lock Number, and the augmented configuration is stable. The role of NASA in this study included the development and analysis of the kinematic model and control laws. Both analytical and numerical techniques were used.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-101029 , A-88280 , NAS 1.15:101029
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Evaluation of a Neural Adaptive Flight Controller (1997)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The objective of this paper is to present results from the evaluation of a direct adaptive tracking controller. The control architecture employs both pre-trained and an on-line neural networks to represent the non-linear aircraft dynamics in the model inversion portion of the controller. The aircraft model used for this evaluation is representative of the F-15 Advanced Control Technology for Integrated Vehicles (ACTIVE) aircraft. The controller was evaluated for three cases: (1) nominal conditions; (2) loss of control power; and (3) loss of control power in the presence of atmospheric turbulence. The results were compared with the existing F-15 ACTIVE conventional mode controller in all cases. The results indicate extremely desirable airframe stabilization characteristics for case (1) that do not degrade significantly for case (2) or (3) as does the conventional mode controller. It was concluded that this controller exhibits both stable and robust adaptive characteristics when subjected to mild and extreme loss of control power conditions. Integration of this neural adaptive flight controller into the full non-linear six degree-of-freedom F-15 ACTIVE simulation is recommended for evaluation in a real-time high fidelity piloted simulation environment.
    Keywords: Aircraft Stability and Control
    Type: AIAA Guidance, Navigation and Control Conference; Aug 11, 1997 - Aug 13, 1997; New Orleans, LA; United States
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    NASA TECHNICAL REPORTS
  • 6
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    The Utilization of Flight Simulation for Research and Development (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The objective of this paper is to review the conventional uses of flight simulation at NASA Ames Research Center for research and development, and to also consider the many new areas that have embraced flight simulation as an effective and economic research tool. Flight simulators have always been a very useful and economic research tool. Component technologies have evolved considerably to meet demands imposed by the aerospace community. In fact, the utilization of flight simulators for research and development has become so widely accepted that non-traditional uses have evolved. Whereas flight dynamics and control, guidance and navigation, vehicle design, mission assessment, and training have been, and perhaps always will be, the most popular research areas associated with simulation, many new areas under the broad categories of human factors and information science have realized significant benefits from the use of flight simulators for research and development. This paper will survey the simulation facilities at NASA Ames Research Center, and discuss selected topics associated with research programs, simulation experiments, and related technology development activities for the purpose of highlighting the expanding role of simulation in aerospace research and development. The information in this paper will in no way provide foreign companies with a competitive advantage over U. S. industry.
    Keywords: Computer Programming and Software
    Type: AEROTECH 1994; Oct 03, 1994 - Oct 06, 1994; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Aerodynamic Analysis of the Truss-Braced Wing Aircraft Using Vortex-Lattice Superposition Approach (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The SUGAR Truss-BracedWing (TBW) aircraft concept is a Boeing-developed N+3 aircraft configuration funded by NASA ARMD FixedWing Project. This future generation transport aircraft concept is designed to be aerodynamically efficient by employing a high aspect ratio wing design. The aspect ratio of the TBW is on the order of 14 which is significantly greater than those of current generation transport aircraft. This paper presents a recent aerodynamic analysis of the TBW aircraft using a conceptual vortex-lattice aerodynamic tool VORLAX and an aerodynamic superposition approach. Based on the underlying linear potential flow theory, the principle of aerodynamic superposition is leveraged to deal with the complex aerodynamic configuration of the TBW. By decomposing the full configuration of the TBW into individual aerodynamic lifting components, the total aerodynamic characteristics of the full configuration can be estimated from the contributions of the individual components. The aerodynamic superposition approach shows excellent agreement with CFD results computed by FUN3D, USM3D, and STAR-CCM+.
    Keywords: Aerodynamics; Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN15815 , Aviation 2014; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    An Integrated Vehicle Modeling Environment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes an Integrated Vehicle Modeling Environment for estimating aircraft geometric, inertial, and aerodynamic characteristics, and for interfacing with a high fidelity, workstation based flight simulation architecture. The goals in developing this environment are to aid in the design of next generation intelligent fight control technologies, conduct research in advanced vehicle interface concepts for autonomous and semi-autonomous applications, and provide a value-added capability to the conceptual design and aircraft synthesis process. Results are presented for three aircraft by comparing estimates generated by the Integrated Vehicle Modeling Environment with known characteristics of each vehicle under consideration. The three aircraft are a modified F-15 with moveable canards attached to the airframe, a mid-sized, twin-engine commercial transport concept, and a small, single-engine, uninhabited aerial vehicle. Estimated physical properties and dynamic characteristics are correlated with those known for each aircraft over a large portion of the flight envelope of interest. These results represent the completion of a critical step toward meeting the stated goals for developing this modeling environment.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 99-4106 , AIAA Atmospheric Flight Mechanics Conference; Aug 09, 1999 - Aug 11, 1999; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Rotor and control system loads analysis of the XV-15 with the advanced technology blades (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis of the rotor and control system loads of the XV-15 with the Advanced Technology Blades (XV-15/ATB) was conducted to study the effects of modifications designed to alleviate high collective actuator loads encountered during initial flight tests. Rotor loads predictions were correlated with flight data to establish accuracies of the methodology used in the analysis. Control system loads predictions were then examined and were also correlated with flight data. The results showed a significant reduction in 3/rev collective actuator loads of the XV-15/ATB when the control system stiffness was increased and the rotor blade chord balance and tip twist were modified.
    Keywords: AERODYNAMICS
    Type: NASA-TM-102876 , A-90316 , NAS 1.15:102876 , American Helicopter Society National Technical Specialists'' Meeting on Innovations in Rotorcraft Test Technologies for the 90''s; Oct 01, 1990; Scottsdale, AZ; United States
    Format: application/pdf
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  • 10
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    Rotor and control system loads analysis of the XV-15 with the advanced technology blades (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An analysis of the rotor and control system loads of the XV-15 with the Advanced Technology Blades (XV-15/ATB) was conducted to investigate the effects of modifications designed to alleviate high collective actuator loads encountered during initial flight tests. Rotor loads predictions were correlated with flight data to establish accuracies of the methodology used in the analysis. Control system loads predictions were then examined and were also correlated with flight data. The results showed a significant reduction in 3/rev collective actuator loads of the XV-15/ATB when the control system stiffness was increased and the rotor blade chord balance and tip twist were modified.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AHS National Technical Specialists'' Meeting; Oct 08, 1990 - Oct 12, 1990; Scottsdale, AZ; United States
    Format: text
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    NASA TECHNICAL REPORTS
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