Guidance in the main deceleration section during a lunar landing of a spacecraft with an integrated propulsion system

B. I. Zhukov; V. N. Likhachev; Yu. G. Sikharulidze; A. G. Tuchin; D. A. Tuchin; V. P. Fedotov

doi:10.1134/S1064230716010111

Guidance in the main deceleration section during a lunar landing of a spacecraft with an integrated propulsion system

Authors: Zhukov B.I.¹, Likhachev V.N.¹, Sikharulidze Y.G.¹, Tuchin A.G.¹, Tuchin D.A.¹, Fedotov V.P.¹
Affiliations:
1. Institute of Applied Mathematics
Issue: Vol 55, No 2 (2016)
Pages: 260-270
Section: Control Systems of Moving Objects
URL: https://journals.rcsi.science/1064-2307/article/view/219592
DOI: https://doi.org/10.1134/S1064230716010111
ID: 219592

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Abstract

An algorithm is developed for terminal guidance during the main deceleration section of the lunar landing trajectory of a spacecraft with an integrated propulsion system, which has a main engine with variable thrust and four auxiliary nonthrottleable engines. A method of guidance adaptation to the actual motion conditions by measuring the thrust acceleration with jumps in time is proposed.