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  • Aircraft Stability and Control
  • GENERAL
  • Inorganic Chemistry
  • 1995-1999  (4)
  • 1955-1959
  • 1999  (4)
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Keywords
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  • 1995-1999  (4)
  • 1955-1959
Year
  • 1
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    Determination of Stability and Control Derivatives using Computational Fluid Dynamics and Automatic Differentiation (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: With the recent interest in novel control effectors there is a need to determine the stability and control derivatives of new aircraft configurations early in the design process. These derivatives are central to most control law design methods and would allow the determination of closed-loop control performance of the vehicle. Early determination of the static and dynamic behavior of an aircraft may permit significant improvement in configuration weight, cost, stealth, and performance through multidisciplinary design. The classical method of determining static stability and control derivatives - constructing and testing wind tunnel models - is expensive and requires a long lead time for the resultant data. Wind tunnel tests are also limited to the preselected control effectors of the model. To overcome these shortcomings, computational fluid dynamics (CFD) solvers are augmented via automatic differentiation, to directly calculate the stability and control derivatives. The CFD forces and moments are differentiated with respect to angle of attack, angle of sideslip, and aircraft shape parameters to form these derivatives. A subset of static stability and control derivatives of a tailless aircraft concept have been computed by two differentiated inviscid CFD codes and verified for accuracy with central finite-difference approximations and favorable comparisons to a simulation database.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 99-3136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High Reynolds Number Effects on HSCT Stability and Control Characteristics (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Two wind tunnel tests during 1995 in the National Transonic Facility (NTF 070 and 073) served to define Reynolds number effects on longitudinal and lateral-directional stability and control. Testing was completed at both high lift and transonic conditions. The effect of Reynolds number on the total airplane configuration, horizontal and vertical tail effectiveness, forebody chine performance, rudder control and model aeroelastics was investigated. This paper will present pertinent stability and control results from these two test entries. Note that while model aeroelastic effects are examined in this presentation, no corrections for these effects have been made to the data.
    Keywords: Aircraft Stability and Control
    Type: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop; Part 3; 1253-1284; NASA/CP-1999-209690/PT3
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Critical Stability and Control Issues in High-Speed Aerodynamics for the HSCT (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The stability and control issues in high speed aerodynamics of most significance for the development of a viable HSCT are identified, and the status of the Ref. H configuration with respect to these issues is discussed. The interdependence between aerodynamic requirements and assumptions about airplane system functions such as Envelope Protection and Integrated Flight/Propulsion Control is highlighted. The conclusions presented draw on results from the Ref. H Assessment and Alternate Control Concepts Assessment performed under Configuration Aerodynamics Subtask 5 during 1995.
    Keywords: Aircraft Stability and Control
    Type: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop; Part 3; 1215-1231; NASA/CP-1999-209690/PT3
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Reference H Piloted Assessment (LaRC.1) Pilot Briefing Guide (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This document describes the purpose of and method by which an assessment of the Boeing Reference H High-Speed Civil Transport design was evaluated in the NASA Langley Research Center's Visual/Motion Simulator in January 1997. Six pilots were invited to perform approximately 60 different Mission Task Elements that represent most normal and emergency flight operations of concern to the High Speed Research program. The Reference H design represents a candidate configuration for a High-Speed Civil Transport, a second generation supersonic civilian transport aircraft. The High-Speed Civil Transport is intended to be economically sound and environmentally safe while carrying passengers and cargo at supersonic speeds with a trans-Pacific range. This simulation study was designated "LaRC. 1" for the purposes of planning, scheduling and reporting within the Guidance and Flight Controls super-element of the High-Speed Research program. The study was based upon Cycle 3 release of the Reference H simulation model.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-1999-209533 , L-17903 , NAS 1.15:209533
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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