Accurate predictor–corrector skip entry guidance for low lift-to-drag ratio spacecraft

Abstract

This paper develops numerical predictorcorrector skip entry guidance for vehicles with low lift-to-drag L/D ratio during the skip entry phase of a Moon return mission. The guidance method is composed of two parts: trajectory planning before entry and closed-loop guidance during skip entry. The result of trajectory planning before entry is able to present an initial value for predictorcorrector algorithm in closed-loop guidance for fast convergence. The magnitude of bank angle, which is parameterized as a linear function of the range-to-go, is modulated to satisfy the downrange requirements. The sign of the bank angle is determined by the bank-reversal logic. The predictor-corrector algorithm repeatedly applied onboard in each guidance cycle to realize closed-loop guidance in the skip entry phase. The e¨ectivity of the proposed guidance is validated by simulations in nominal conditions, including skip entry, loft entry, and direct entry, as well as simulations in dispersion conditions considering the combination disturbance of the entry interface, the aerodynamic coe©cients, the air density, and the mass of the vehicle.

Multi-Process Integrated Planning and Guidance for Return of Reusable Aircraft Under Time Constraint

“…A feasible trajectory can be quickly generated, and then the linear quadratic regulator (LQR) was used to track trajectory. With the advance in processor performance, many scholars have studies the guidance algorithm based on predictor-corrector method [11][12][13][14][15][16]. Brunner and Lu [17] conducted a large number of simulations and found that the predictive-correction reentry guidance exhibited a good robustness even under aerodynamic deviation.…”