CLC number:
On-line Access: 2025-01-21
Received: 2023-02-27
Revision Accepted: 2023-10-09
Crosschecked: 2025-01-21
Cited: 0
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Hui XU, Guangbin CAI, Chaoxu MU, Xin LI, Hao WEI. Segmented predictor-corrector reentry guidance based on an analytical profile[J]. Journal of Zhejiang University Science A, 2025, 26(1): 50-65.
@article{title="Segmented predictor-corrector reentry guidance based on an analytical profile",
author="Hui XU, Guangbin CAI, Chaoxu MU, Xin LI, Hao WEI",
journal="Journal of Zhejiang University Science A",
volume="26",
number="1",
pages="50-65",
year="2025",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2300102"
}
%0 Journal Article
%T Segmented predictor-corrector reentry guidance based on an analytical profile
%A Hui XU
%A Guangbin CAI
%A Chaoxu MU
%A Xin LI
%A Hao WEI
%J Journal of Zhejiang University SCIENCE A
%V 26
%N 1
%P 50-65
%@ 1673-565X
%D 2025
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2300102
TY - JOUR
T1 - Segmented predictor-corrector reentry guidance based on an analytical profile
A1 - Hui XU
A1 - Guangbin CAI
A1 - Chaoxu MU
A1 - Xin LI
A1 - Hao WEI
J0 - Journal of Zhejiang University Science A
VL - 26
IS - 1
SP - 50
EP - 65
%@ 1673-565X
Y1 - 2025
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2300102
Abstract: A segmented predictor-corrector method is proposed for hypersonic glide vehicles to address the issue of the slow computational speed of obtaining guidance commands using the traditional predictor-corrector guidance method. Firstly, an altitude-energy profile is designed, and the bank angle is derived analytically as the initial iteration value for the predictor-corrector method. The predictor-corrector guidance method has been improved by deriving an analytical form for predicting the range-to-go error, which greatly accelerates the iterative speed. Then, a segmented guidance algorithm is proposed. The above analytically predictor-corrector guidance method is adopted when the energy exceeds an energy threshold. When the energy is less than the threshold, the equidistant test method is used to calculate the bank angle command, which ensures guidance accuracy as well as computational efficiency. Additionally, an adaptive guidance cycle strategy is applied to reduce the computational time of the reentry guidance trajectory. Finally, the accuracy and robustness of the proposed method are verified through a series of simulations and Monte-Carlo experiments. Compared with the traditional integral method, the proposed method requires 75% less computation time on average and achieves a lower landing error.
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