A Novel IGC Scheme for RHV with the Capabilities of Online Aerodynamic Coefficient Estimation and Trajectory Generation

Abstract

A novel integrated guidance and control (IGC) scheme for a Re-entry Hypersonic Vehicle (RHV) is proposed with the capabilities of online aerodynamic coefficient estimation based on an Unscented Kalman Filter and online trajectory generation based on the Gaussian pseudospectral method. A linear quadratic regulator is adopted for trajectory tracking guidance and a second-layer sliding mode controller is designed for attitude control. The variation of lift and drag coefficients are modeled and estimated online, based on which a new trajectory can be generated. The commands of trajectory generation are set as moments of actuators and their extremums pose more constraints on the rate and acceleration of flow angles. Comprehensive simulations are conducted and comparable IGC performances with normal conditions are obtained under large aerodynamic coefficient errors according to online generated trajectory, which proves the effectiveness and advantages of the proposed IGC scheme.

Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control

“…(1) the estimation law of equation ( 21), in conjunction with the control law of equation (24), is insensitive to the sampling time step; (2) the output error can become small enough by sufficient reduction of the sampling time step;…”

“…and the proof of the second result of the theorem is completed here. Furthermore, to prove that the system has BIBO stability, one may rewrite equation (24) as follows…”

“…In this line, references can be made to the control of a skid-to-turn hypersonic missiles, 18 navigation with high automation, 19 3-D bank-to-turn maneuvering of a missile with a pulse angle, 20 control of a missile against an unrecognized maneuvering target despite uncertainties and control bounds, 21 increase of accuracy at the landing point of satellite carrier boosters, 22 and control of a flexible hypersonic vehicle. 23 Moreover, a robust adaptive IGC scheme relying on the model of the system is recently developed by Wang et al 24 for a re-entry hypersonic vehicle with online estimation of aerodynamic coefficients.…”