Guidance and control of reentry vehicle based on dynamic inversion approach

In this paper, simultaneous implementation of an online guidance with the dynamic-inversionbased attitude control is discussed for a hypersonic reentry vehicle. For this purpose, a six-degree-offreedom model is developed considering the oblate rotating Earth. Dynamic Inversion cancels the inherent dynamics of a nonlinear system and replaces it with a specified desired linear one. This approach is applied to the design of reentry vehicle attitude controller assuming timescale separation between attitude and attitude rates. Attitude control is responsible for tracking guidance commands. PPN guidance features make it an appropriate guidance law for evaluating the performance of the attitude control; thus, it is selected as the online guidance law. Effects of disturbances, uncertainties and actuator delay are studied. Simulations verify the performance of the whole guidance and control system in the presence of external disturbances, model uncertainties and input constraints. The approach robustness is verified by Monte Carlo simulation.

Keywords:

Reentry Vehicle , Dynamic Inversion , Guidance , Attitude control