Posture and path coupling control method for deep space exploration soft landing process

Abstract

The invention relates to a posture and path coupling control method for the deep space exploration soft landing process. In the deep space celestial body soft landing process, a thrust-variable swing engine is used for conducting posture control, and therefore a landing path is disturbed. Important measures for reducing posture control and path control coupling of the thrust-variable swing engine includes that a part, used for eliminating centroid skewing, in a swing angle of the thrust-variable swing engine is estimated on line, and flight postures are amended. According to the posture and path coupling control method, the swing angle of the thrust-variable swing engine is required to be estimated on line firstly, and stable components of the swing angle are extracted; then the target flight postures are amended through the stable components of the swing angle, the amended thrust direction is coincident with the thrust direction expected in a guidance law, and influences of posture control swing of the thrust-variable swing engine on guidance are initiatively eliminated. By means of the posture and path coupling control method, disturbance to the guidance is reduced to the maximum degree while the posture control is carried out, and even though the guidance has no three-direction position control capacity, it can be guaranteed that the flight path is coincident with an ideal path as far as possible.

Description

technical field [0001] The invention relates to an attitude-orbit coupling control method in the soft landing process of deep space exploration, belonging to the field of autonomous control of deep space exploration. Background technique [0002] Landing detection is an important means of deep space exploration. For a large lander or a probe that lands on a large celestial body, in order to reduce the landing speed and offset the gravitational force of the target celestial body, the thrust of the landing engine must be very large. If a large landing engine is used, due to factors such as engine manufacturing, installation, and unbalanced propellant discharge during the descent process, the thrust direction of the landing engine will not just pass through the center of mass, which will generate a large attitude disturbance moment, which is unfavorable to attitude control. influences. There are two ways to solve it. One method is to install a larger attitude control engine ...

AI Technical Summary

Problems solved by technology

[0004] The technology of the present invention solves the problem: to overcome the problem that the existing deep space exploration soft landing swing engine control technology will produce lateral interference force that will adversely affect the guidance, and proposes an attitude-orbit coupling control method for the deep space exploration soft landing process , the method online ide

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