A Hybrid Aerocapture Guidance Algorithm

Abstract

Abstract. Numerical predictor-corrector guidance algorithms are widely used in aerocapture missions. However, the overload can be quite large and even exceed the entry corridor. A hybrid guidance algorithm for Aerocapture is developed in this paper to solve this problem. First, the entry corridor and a reference trajectory for Earth aerocapture in the drag acceleration profile are obtained. Then, a three-phase hybrid guidance law combined with constant bank angle profile algorithm, feedback linearization tracking algorithm and numerical predictor-corrector algorithm is proposed. The simulation results under nominal and off-nominal conditions demonstrate that the proposed method reaches the target orbit accurately and relieves the overload efficiently.