Orbit-Injection Strategy and Trajectory-Planning Method of the Launch Vehicle under Power Failure Conditions

Aiming at the problem of autonomous decision making and trajectory planning (ADMTP) for launch vehicles under power failure conditions, the target degradation order strategy (TDOS) and the trajectory online planning method were studied in this paper. Firstly, the influence of power failure on the or...

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Bibliographic Details
Published inAerospace Vol. 9; no. 4; p. 199
Main Authors Diao, Yin, Pu, Jialun, Xu, Hechuan, Mu, Rongjun
Format Journal Article
LanguageEnglish
Published Basel MDPI AG 01.04.2022
Subjects
Accuracy
Convex analysis
Decision making
Decision theory
Failure
Failure analysis
Failure modes
Injection
launch vehicle
Methods
Neural networks
Numerical analysis
online trajectory planning
Optimization algorithms
orbit-injection strategy
Power
power failure
Satellite communications
Simulation analysis
Strategy
target degradation
Trajectory planning
Vehicles
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Summary:Aiming at the problem of autonomous decision making and trajectory planning (ADMTP) for launch vehicles under power failure conditions, the target degradation order strategy (TDOS) and the trajectory online planning method were studied in this paper. Firstly, the influence of power failure on the orbit-injection process was analyzed. Secondly, the TDOS was proposed according to the mission attribute, failure mode, and multi-payload combination. Then, an online planning method based on the adaptive target update iterative guidance method (ATU-IGM) and radial basis neural network (RBFNN) was proposed, where the ATU-IGM adopted the basic TDOS criterion for generating optimal orbit-injection samples and online guidance instructions, and the RBFNN was used for orbit-injection samples training and online generation of orbital missions. Finally, the comparative simulation analysis was performed under multi-failure conditions. The results showed that the TDOS proposed in this paper could meet the requirements of the mission decision making under different failures, target orbit types, orbit-injection methods, and payload compositions. The online trajectory-planning capability deviation was less than 5%, and the mission decision-making and trajectory-planning time were less than 10 ms. This study provides theoretical support for autonomous decision making and planning of space launch missions.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace9040199