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.
Status of the Validation of High-Angle-Of-Attack Nose-Down Pitch Control Margin Design Guidelines
1992-01-01
Miscellaneous
No indication
English
Status of the Validation of High-Angle-of-Attack Nose-Down Pitch Control Margin Design Guidelines
British Library Conference Proceedings | 1993
|British Library Conference Proceedings | 1994
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