Guidance in the main deceleration section during a lunar landing of a spacecraft with an integrated propulsion system
- Autores: Zhukov B.1, Likhachev V.1, Sikharulidze Y.1, Tuchin A.1, Tuchin D.1, Fedotov V.1
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Afiliações:
- Institute of Applied Mathematics
- Edição: Volume 55, Nº 2 (2016)
- Páginas: 260-270
- Seção: 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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Resumo
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.
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Sobre autores
B. Zhukov
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Rússia, Moscow
V. Likhachev
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Rússia, Moscow
Yu. Sikharulidze
Institute of Applied Mathematics
Autor responsável pela correspondência
Email: sikh@kiam1.rssi.ru
Rússia, Moscow
A. Tuchin
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Rússia, Moscow
D. Tuchin
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Rússia, Moscow
V. Fedotov
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Rússia, Moscow