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  • 1
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    Development of high-angle-of-attack nose-down pitch control margin design guidelines for combat aircraft (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A broad research program to identify maneuvering requirements for advanced fighters and the corresponding design criteria to aid in making critical design tradeoffs is being conducted under the NASA High-Angle-of-Attack Technology Program (HATP). As part of this activity, NASA and the U.S. Navy are conducting cooperative research to develop high-angle-of-attack control margin requirements. This paper will summarize the status of this program. Following some background information, the simulation study conducted to develop a set of preliminary guidelines for nose-down pitch control is reviewed, and the results of some very limited flight tests are described.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA LaRC Workshop on Guidance, Navigation, Controls, and Dynamics for Atmospheric Flight, 1993; p 293-322
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Flight validation of ground-based assessment for control power requirements at high angles of attack (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A review is presented in viewgraph format of an ongoing NASA/U.S. Navy study to determine control power requirements at high angles of attack for the next generation high-performance aircraft. This paper focuses on recent flight test activities using the NASA High Alpha Research Vehicle (HARV), which are intended to validate results of previous ground-based simulation studies. The purpose of this study is discussed, and the overall program structure, approach, and objectives are described. Results from two areas of investigation are presented: (1) nose-down control power requirements and (2) lateral-directional control power requirements. Selected results which illustrate issues and challenges that are being addressed in the study are discussed including test methodology, comparisons between simulation and flight, and general lessons learned.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Center, Fourth High Alpha Conference, Volume 2; 20 p
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    NASA TECHNICAL REPORTS
  • 3
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    Application of piloted simulation to high-angle-of-attack flight-dynamics research for fighter aircraft (1992)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The use of piloted simulation at Langley Research Center as part of the NASA High-Angle-of-Attack Technology Program (HATP), which was created to provide concepts and methods for the design of advanced fighter aircraft, is reviewed. A major research activity within this program is the development of the design processes required to take advantage of the benefits of advanced control concepts for high angle of attack agility. Fundamental methodologies associated with the effective use of piloted simulation for this research are described, particularly those relating to the test techniques, validation of the test results, and design guideline/criteria development.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD, Piloted Simulation Effectiveness; 16 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Use of Piloted Simulation for High-Angle-of-Attack Agility Research and Design Criteria Development (1991)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The use of piloted simulation at Langley Research Center as part of the NASA High-Angle-of-Attack Technology Program (HATP) to provide methods and concepts for the design of advanced fighter aircraft is discussed. A major focus is to develop the design process required to fully exploit the benefits from advanced control concepts for high-angle-of attack agility.
    Keywords: Spacecraft Instrumentation and Astrionics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Status of the Validation of High-Angle-Of-Attack Nose-Down Pitch Control Margin Design Guidelines (1992)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: This paper presents a summary of results obtained to date in an ongoing cooperative research program between NASA and the U.S. Navy to develop design criteria for high-angle-of-attack nose- down pitch control for combat aircraft. A fundamental design consideration for aircraft incorporating relaxed static stability in pitch is the level of stability which achieves a proper balance between high- speed performance considerations and low-speed requirements for maneuvering at high angles of attack. A comprehensive data base of piloted simulation results was generated for parametric variations of critical parameters affecting nose-down control capability. The results showed a strong correlation of pilot rating to the short-term pitch response for nose-down commands applied at high- angle-of-attack conditions. Using these data, candidate design guidelines and flight demonstration requirements were defined. Full- scale flight testing to validate the research methodology and proposed guidelines is in progress, some preliminary results of which are reviewed.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Status of the validation of high-angle-of-attack nose-down pitch control margin design guidelines (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a summary of results obtained to date in an ongoing cooperative research program between NASA and the U.S. Navy to develop design criteria for high-angle-of-attack nose-down pitch control for combat aircraft. A fundamental design consideration for aircraft incorporating relaxed static stability in pitch is the level of stability which achieves a proper balance between high-speed performance considerations and low-speed requirements for maneuvering at high angles of attack. A comprehensive data base of piloted simulation results was generated for parametric variations of critical parameters affecting nose-down control capability. The results showed a strong correlation of pilot rating to the short-term pitch response for nose-down commands applied at high-angle-of-attack conditions. Using these data, candidate design guidelines and flight demonstration requirements were defined. Full-scale flight testing to validate the research methodology and proposed guidelines is in progress, some preliminary results of which are reviewed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 93-3623 , In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08); p. 60-75.
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Controls for agility research in the NASA High-Alpha Technology Program (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The research process being used to develop control law design methodologies and guidelines in the NASA High-Alpha Technology Program are discussed. This step-by-step process consists of four basic elements: (1) control law architecture definition and linear synthesis, (2) nonlinear batch simulation, (3) piloted simulation evaluation, and (4) flight test validation. This paper discusses the research tools being used in this effort and provides a status report on design methodologies and guidelines being developed for each of these elements.
    Keywords: Aircraft Stability and Control
    Type: SAE PAPER 912148 , SAE, Aerospace Technology Conference and Exposition; Sept. 23-26, 1991; Long Beach, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Development of a preliminary high-angle-of-attack nose-down pitch control requirement for high-performance aircraft (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The requirements for high-angle-of-attack nose-down pitch control for advanced high-performance aircraft are discussed. Background information on fundamental factors that influence and, to a large extent, determine the high angle-of-attack nose-down control requirement is briefly reviewed. Guidelines currently proposed by other sources which attempt to define these requirements are discussed. A requirement based on NASA analysis of the characteristics of existing relaxed static stability (RSS) aircraft is presented. This analysis could provide the basis for a preliminary design guide.
    Keywords: AERODYNAMICS
    Type: NASA-TM-101684 , NAS 1.15:101684
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Investigation of High-alpha Lateral-directional Control Power Requirements for High-performance Aircraft (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Designers of the next-generation fighter and attack airplanes are faced with the requirements of good high-angle-of-attack maneuverability as well as efficient high speed cruise capability with low radar cross section (RCS) characteristics. As a result, they are challenged with the task of making critical design trades to achieve the desired levels of maneuverability and performance. This task has highlighted the need for comprehensive, flight-validated lateral-directional control power design guidelines for high angles of attack. A joint NASA/U.S. Navy study has been initiated to address this need and to investigate the complex flight dynamics characteristics and controls requirements for high-angle-of-attack lateral-directional maneuvering. A multi-year research program is underway which includes ground-based piloted simulation and flight validation. This paper will give a status update of this program that will include a program overview, description of test methodology and preliminary results.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 93-3647 , AIAA Atmospheric Flight Mechanics Conference; Aug 09, 1993 - Aug 11, 1993; Monterey, CA; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Use of piloted simulation for high-angle-of-attack agility research and design criteria development (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The application of piloted simulations in the development of advanced fighter aircraft is reviewed in the context of the NASA High-Angle-of-Attack Technology Program (HATP). The HATP combines wind-tunnel experiments, computational aerodynamics, piloted simulations, and flight tests on a modified F-18 testbed aircraft and utilizes the experience and facilities of several NASA centers. Consideration is given to the role of simulation in the overall research process, simulation capabilities and software requirements, simulation flexibility and fidelity, evaluation maneuvers, the role of simulator pilots in evaluations, the analysis of simulation results, flight validation of maneuvers and rating approaches, and the use of simulations to define design criteria. Extensive diagrams, graphs, and flow charts are included.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-2954 , AIAA Flight Simulation Technologies Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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