Enhanced predictor–corrector Mars entry guidance approach with atmospheric uncertainties
Due to the long-range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations ensuring high precision landing in future Mars missions. Based on the analysis of multiple disturbances, this study demonstrates an enhanced...
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| Published in | IET control theory & applications Vol. 13; no. 11; pp. 1612 - 1618 |
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| Main Authors | , , , |
| Format | Journal Article |
| Language | English |
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The Institution of Engineering and Technology
23.07.2019
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| Abstract | Due to the long-range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations ensuring high precision landing in future Mars missions. Based on the analysis of multiple disturbances, this study demonstrates an enhanced predictor–corrector guidance method to deal with the effect of atmospheric uncertainties during the entry phase of the Mars landing. In the proposed method, the predictor–corrector guidance algorithm is designed to autonomously drive the Mars lander to the parachute deployment. Meanwhile, the disturbance observer is designed to onboard estimate the effect of fiercely varying atmospheric uncertainties resulting from rapidly height decreasing. Then, with the estimation of atmospheric uncertainties compensated in the feed-forward channel, the composite guidance method is put forward such that both anti-disturbance and autonomous performance of the Mars lander guidance system are improved. Convergence of the proposed composite method is analysed. Simulations for a Mars lander entry guidance system demonstrates that the proposed method outperforms the baseline method in consideration of the atmospheric uncertainties. |
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| AbstractList | Due to the long-range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations ensuring high precision landing in future Mars missions. Based on the analysis of multiple disturbances, this study demonstrates an enhanced predictor–corrector guidance method to deal with the effect of atmospheric uncertainties during the entry phase of the Mars landing. In the proposed method, the predictor–corrector guidance algorithm is designed to autonomously drive the Mars lander to the parachute deployment. Meanwhile, the disturbance observer is designed to onboard estimate the effect of fiercely varying atmospheric uncertainties resulting from rapidly height decreasing. Then, with the estimation of atmospheric uncertainties compensated in the feed-forward channel, the composite guidance method is put forward such that both anti-disturbance and autonomous performance of the Mars lander guidance system are improved. Convergence of the proposed composite method is analysed. Simulations for a Mars lander entry guidance system demonstrates that the proposed method outperforms the baseline method in consideration of the atmospheric uncertainties. |
| Author | Lei, Guo Jianwei, Xu Wenhua, Chen Jianzhong, Qiao |
| Author_xml | – sequence: 1 givenname: Xu surname: Jianwei fullname: Jianwei, Xu organization: 1School of Automation Science and Electrical Engineering, Beihang University, No. 37, Xueyuan Road, Haidian District, Beijing, People's Republic of China – sequence: 2 givenname: Qiao surname: Jianzhong fullname: Jianzhong, Qiao organization: 2Beijing Advanced Innovation Center for Big Data-based Precision Medicine, Beihang University, No. 37, Xueyuan Road, Haidian District, Beijing, People's Republic of China – sequence: 3 givenname: Guo surname: Lei fullname: Lei, Guo email: lguo@buaa.edu.cn organization: 2Beijing Advanced Innovation Center for Big Data-based Precision Medicine, Beihang University, No. 37, Xueyuan Road, Haidian District, Beijing, People's Republic of China – sequence: 4 givenname: Chen surname: Wenhua fullname: Wenhua, Chen organization: 3Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, LE11 3TU, UK |
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| CitedBy_id | crossref_primary_10_1016_j_ast_2024_109368 crossref_primary_10_3390_aerospace9080427 crossref_primary_10_1007_s11431_022_2241_6 crossref_primary_10_1016_j_ast_2022_107364 crossref_primary_10_1109_TCYB_2020_3024997 crossref_primary_10_1002_asjc_2575 crossref_primary_10_1016_j_ast_2020_106361 crossref_primary_10_1515_ijnsns_2019_0290 crossref_primary_10_1109_TIE_2022_3152012 |
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| Copyright | The Institution of Engineering and Technology 2021 The Authors. IET Control Theory & Applications published by John Wiley & Sons, Ltd. on behalf of The Institution of Engineering and Technology |
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| Keywords | long-range data communication Mars lander guidance system entry, descent and landing (spacecraft) composite guidance method high precision landing aerospace control space vehicles atmospheric uncertainties predictor–corrector guidance algorithm enhanced predictor–corrector guidance method enhanced predictor–corrector Mars entry guidance approach Mars complex Mars environment future Mars missions Mars lander entry guidance system Mars landing predictor-corrector methods |
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| Snippet | Due to the long-range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations... Due to the long‐range data communication and complex Mars environment, the Mars lander needs to promote the ability to autonomously adapt uncertain situations... |
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| SubjectTerms | aerospace control atmospheric uncertainties complex Mars environment composite guidance method enhanced predictor–corrector guidance method enhanced predictor–corrector Mars entry guidance approach entry, descent and landing (spacecraft) future Mars missions high precision landing long‐range data communication Mars Mars lander entry guidance system Mars lander guidance system Mars landing predictor‐corrector methods predictor–corrector guidance algorithm Research Article space vehicles |
| Title | Enhanced predictor–corrector Mars entry guidance approach with atmospheric uncertainties |
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