Reentry-Vehicle Dispersion from Entry Angular Misalignment.
AEROSPACE CORP EL SEGUNDO CALIF IVAN A GETTING LABS
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An approximate solution is obtained for the dispersion of a reentry vehicle caused by an initial angular misalignment between the vehicle axis of symmetry and the velocity vector at entry into the atmosphere. The dispersion depends on the exoatmospheric motion, which determines the precession mode of the lift vector during angle-of-attack convergence. Maximum dispersion results from an initial angular misalignment in absence of exoatmospheric coning motion. The trajectory deflection for this case occurs in a plane that leads the plane of initial angular misalignment by approximately 90 deg. The dispersion is approximately proportional to roll rate, in contrast to dispersion from body-fixed asymmetries, which varies inversely with roll rate. Author
- Guided Missile Dynamics, Configurations and Control Surfaces
- Guided Missile Reentry Vehicles