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

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 a...

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Bibliographic Details
Published in:Journal of computer & systems sciences international 2016-03, Vol.55 (2), p.260-270
Main Authors: Zhukov, B. I., Likhachev, V. N., Sikharulidze, Yu. G., Tuchin, A. G., Tuchin, D. A., Fedotov, V. P.
Format: Article
Language:English
Subjects:
Aerospace engines
Algorithms
Analysis
Control
Control Systems of Moving Objects
Deceleration
Energy consumption
Engineering
Engines
Lunar landing
Mechatronics
Navigation systems
Propulsion systems
Robotics
Satellites
Spacecraft
Studies
Terminal guidance
Thrust
Variable thrust
Velocity
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Description
Summary: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.
ISSN:1064-2307
1555-6530
DOI:10.1134/S1064230716010111