Non-Linear Dynamic Inversion-Based Guidance and Control for Atmospheric Entry
- Paper number
IAC-07-D2.3.09
- Author
Mr. Tiago Hormigo, Spin.Works, Portugal
- Coauthor
João Araújo, Portugal
- Coauthor
Francisco Camara, Portugal
- Year
2007
- Abstract
Non-linear trajectory and attitude control laws are developed and applied to a blunted sphere-cone model, in order to track a reference Mars atmospheric entry trajectory and demonstrate the capability for precision landing. For the guidance loop, a feedback linearization of the drag dynamics is used to control the drag acceleration (using bank angle modulation to control the orientation of the lift vector), and periodic trajectory updates to compensate any minor down-range deviations associated to transient drag errors. For the attitude control loop, the attitude dynamics equations are also feedback-linearized in order to stabilize the angles of attack and sideslip throughout the entire range of flight conditions, as well as for tracking the commanded bank angle. To verify the system performance and its robustness to uncertainties, a Monte-Carlo campaign is carried out on a high-fidelity 6DOF simulation tool using state-of-the-art environment models, considering uncertainties on the martian atmosphere, uncertainties on initial trajectory conditions, and several vehicle model uncertainties.
- Abstract document