Accession Number : ADA257418


Title :   Pitch Control Margin at High Angle of Attack-Quantitative Requirements (Flight Test Correlation with Simulation Predictions)


Corporate Author : NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD


Personal Author(s) : Lackey, J ; Hadfield, C


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a257418.pdf


Report Date : Jan 1992


Pagination or Media Count : 42


Abstract : Aircraft designs that employ relaxed static stability (RSS) have the following problem: reduced pitching moments associated with RSS at high angle of attack (AOA) require a minimum pitch recovery moment or margin to guarantee a safe return from high AOA maneuvers at the most aft center of gravity (CG) encountered during a mission. Recent incidents and mishaps on Class IV aircraft have demonstrated a need for establishing quantitative longitudinal high AOA pitch control margin design guidelines for future aircraft. The Naval Air Warfare Center - Aircraft Division (NAWC-AD) is currently supporting an effort in conjunction with NASA Langley Research Center (NASA LARC) to quantify such requirements. NASA LaRC has conducted a series of extensive simulation evaluations to define these design guidelines.


Descriptors :   *PITCH(MOTION) , *ANGLE OF ATTACK , CONTROL , REQUIREMENTS , SIMULATION , STABILITY , ATTACK , MISSIONS , GRAVITY , DIVISION , STATIC STABILITY , HIGH ANGLES , STATICS , MANEUVERS , PHOSGENE , GUARANTEES , MOMENTS , AIRCRAFT , CENTER OF GRAVITY , WARFARE , RECOVERY


Subject Categories : Flight Control and Instrumentation


Distribution Statement : APPROVED FOR PUBLIC RELEASE