Guidance in the main deceleration section during a lunar landing of a spacecraft with an integrated propulsion system
- Авторлар: Zhukov B.1, Likhachev V.1, Sikharulidze Y.1, Tuchin A.1, Tuchin D.1, Fedotov V.1
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Мекемелер:
- Institute of Applied Mathematics
- Шығарылым: Том 55, № 2 (2016)
- Беттер: 260-270
- Бөлім: Control Systems of Moving Objects
- URL: https://journals.rcsi.science/1064-2307/article/view/219592
- DOI: https://doi.org/10.1134/S1064230716010111
- ID: 219592
Дәйексөз келтіру
Аннотация
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.
Негізгі сөздер
Авторлар туралы
B. Zhukov
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Ресей, Moscow
V. Likhachev
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Ресей, Moscow
Yu. Sikharulidze
Institute of Applied Mathematics
Хат алмасуға жауапты Автор.
Email: sikh@kiam1.rssi.ru
Ресей, Moscow
A. Tuchin
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Ресей, Moscow
D. Tuchin
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Ресей, Moscow
V. Fedotov
Institute of Applied Mathematics
Email: sikh@kiam1.rssi.ru
Ресей, Moscow