An internal moving mass actuator control system is proposed for angle-of-attack and sideslip-based Mars precision entry guidance. Internal moving mass actuators provide vehicle control moments without direct interaction with the external flowfield. This enables trajectory control without destabilization concerns associated with aerodynamic flap ablation and flowfield interaction for both flap and thruster control systems. Angle-of-attack and sideslip control is proposed as an alternative to bank angle guidance for decoupling range and crossrange control for improved precision entry guidance. A new variant of the Apollo Earth return terminal guidance algorithm is presented and used to provide closed-loop attitude commands. A linear-quadratic controller with integral error action is synthesized and tuned for a Mars Phoenix-sized entry vehicle with two internal moving mass actuators for guidance command tracking. Nonlinear simulation of the controller for the eight-degree-of-freedom system demonstrates precision guidance to the nominal trajectory and final target for offnominal initial entry conditions for the flight-path angle, range, cross range, speed, and attitude. Presented as Paper 14-385 at the 24th AAS/AIAA Space Flight Mechanics Meeting, Santa Fe, New Mexico, 26-30 January 2014
Internal Moving Mass Actuator Control for Mars Entry Guidance
Journal of spacecraft and rockets ; 52 , 5
2015
Aufsatz (Zeitschrift)
Englisch
British Library Conference Proceedings | 2014
|Mars Science Laboratory Entry Guidance
NTRS | 2011
|Mars Science Laboratory Entry Guidance
NTIS | 2011
|