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Design of Adaptive Iterative Guidance Scheme for Mars Ascent Vehicle Orbiting Phase
- SONG Chun1, GUO Yanning2, GUO Minwen3, LI Kun2
Author information
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1. Science and Technology on Space Physics Laboratory, Beijing 100076, China;
2. Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China;
3. Beijing Institute of Control Engineering, Beijing 100094, China
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History
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Received |
Revised |
Published |
01 Nov 2013 |
30 Dec 2013 |
26 Mar 2024 |
Issue Date |
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26 Mar 2024 |
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Abstract
An adaptive iterative guidance strategy was designed for the guidance of Mars ascent vehicle in the orbiting phase. To reduce the effects of initial state deviation and the uncertainty of the Martian environment, the remaining flight time was calculated iteratively in the guidance coordinate system in each cycle, and the optimal control angle satisfying the constraints of the target point position and velocity vector was solved under the fixed thrust of the ascender, so as to correct the flight trajectory in real time. The simulation results show that compared with the traditional open-loop guidance scheme, the proposed scheme significantly improves guidance accuracy, in which the altitude error is reduced by three orders of magnitude, the maximum velocity error is reduced to one-third of that of the original open-loop guidance, the orbital inclination and eccentricity errors at the entry point satisfy the basic engineering requirements, and it can be used as a reliable scheme for the future guidance of the Mars ascent vehicle in the orbiting phase.
Keywords
Mars ascent vehicle /
orbiting phase /
iterative guidance /
optimal control
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SONG Chun, GUO Yanning, GUO Minwen, LI Kun.
Design of Adaptive Iterative Guidance Scheme for Mars Ascent Vehicle Orbiting Phase. Journal of Deep Space Exploration, 2024, 11(1): 31‒39 https://doi.org/10.15982/j.issn.2096-9287.2024.20230055
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