Fast Deorbit Guidance Method Based on Virtual Reentry Angle

doi:10.12382/bgxb/2021.0710

Abstract

Abstract:

To meet the requirement of rapid deorbit of reentry vehicles, an online guidance algorithm for rapid deorbit based on virtual reentry angle is proposed. On the basis of analyzing the guidance mechanism of the pulse deorbit, the finite thrust method is used to gradually approach the terminal state so as to meet the shift requirements of the reentry angle and reentry speed. The convex optimization method is used to calculate the time-optimal trajectory that meets the multi-terminal constraints. Combined with the simulation results of the finite thrust guidance algorithm, the trajectory characteristics are analyzed, the concept of virtual reentry angle is proposed, and an online guidance algorithm for fast deorbit considering multi-terminal constraints is designed. The proposed method is compared with the existing methods from the aspects of computational efficiency and guidance accuracy, Monte-Carlo simulations are carried out under the condition of deviation of the thrust magnitude and direction of the engine. The simulation results show that compared to the existing algorithms, the proposed algorithm achieves the goal of rapidity in the deorbit stage and can meet the needs of online computing while ensuring the same control accuracy.

Key words: reentry vehicle, fast deorbit, virtual reentry angle, convex optimization

QUAN Shenming, WANG Zhu, CHAO Tao, YANG Ming. Fast Deorbit Guidance Method Based on Virtual Reentry Angle[J]. Acta Armamentarii, 2023, 44(3): 865-875.

Figures/Tables 10

Fig. 1 Schematic diagram of orbital transfer

Fig. 2 Deorbit trajectory of an elliptical orbit

Fig. 3 Schematic diagram of time-optimal deorbit

Fig. 4 Curve of the flight path angle with the improved method and the traditional method

Fig. 5 Flow chart of simulation of fast deorbit guidance

Fig. 6 Curves of time-optimal deorbit with multiple constraints

Fig. 7 Simulation results of the traditional deorbit guidance algorithm

Fig. 8 Simulation results of the fast deorbit guidance algorithm

Table 1 Parameter perturbations

偏差项	变化范围	分布类型
推力大小比例/%	[-5,5]	均匀分布
推力方向/(°)	[-0.1,0.1]	均匀分布
燃料质量/kg	[-20,20]	均匀分布

Fig. 9 Distribution of Monte Carlo simulation parameters

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