Accession Number : ADA019802
Title : Angle-of-Attack Control of Drag for Slender Reentry Vehicle Recovery.
Descriptive Note : Interim rept.,
Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF AEROPHYSICS LAB
Personal Author(s) : Platus,Daniel H.
Report Date : 16 DEC 1975
Pagination or Media Count : 42
Abstract : A method is described in which drag increase due to angle of attack is used to decelerate a slender, high-ballistic-coefficient reentry vehicle for recovery. The angle of attack and drag increase are produced by the application of a controlled wind-fixed yaw moment, which causes dynamic undamping of the angle of attack. A small yaw moment can induce large circular coning motion for which the drag is predictable. It is shown that sufficient deceleration for recovery can be obtained after the vehicle has experienced high stagnation pressures for nosetip and heat-shield testing. Practical implementation of the recovery system is discussed.
Descriptors : *Slender bodies, *Test vehicles, *Hypersonic characteristics, *Atmosphere entry, Recovery, Deceleration, Angle of attack, Drag, Reentry vehicles, Ablation, Nose cones, Instrumentation, Equations of motion, Systems engineering, Mathematical analysis
Subject Categories : Guided Missiles
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE