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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Veröffentlicht in:	IET control theory & applications Jg. 13; H. 11; S. 1612 - 1618
Hauptverfasser:	Jianwei, Xu, Jianzhong, Qiao, Lei, Guo, Wenhua, Chen
Format:	Journal Article
Sprache:	Englisch
Veröffentlicht:	The Institution of Engineering and Technology 23.07.2019
Schlagworte:	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 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
ISSN:	1751-8644, 1751-8652
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Zusammenfassung:	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.
ISSN:	1751-8644 1751-8652
DOI:	10.1049/iet-cta.2018.5782