Design of Uncertain Attitude Control Method for Deep Space Probe Based on Fuzzy Control

In space exploration missions, attitude control is the basis to ensure the completion of various tasks, especially in the take-off and landing stage plays a key role. Although the landing control technology of the spacecraft is becoming more and more mature, the attitude control of the extraterrestrial take-off stage is still less studied. In this paper, a fuzzy controller is designed for the launch of a deep space probe in the alien uncertain environment. Firstly, the detector model used in this paper is summarized, and the attitude description method and corresponding kinematic equation are given. Then, according to the fuzzy control principle, the fuzzy control rules which map the attitude Angle and angular velocity to the output torque are established. Finally, the fuzzy attitude Angle and angular velocity are taken as the input, and the corresponding fuzzy output is obtained according to the fuzzy rule, and the switch state output of the controller engine is obtained by deblurring, so as to realize the fast and effective control of the detector attitude. Then, numerical simulation was used to test the control effect of the controller and its robustness when there is a deviation between the initial attitude and the engine installation. Finally, physical simulation of the probe take-off process was carried out in ADAMS environment combined with Simulink module. According to the above analysis and simulation, the results show that compared with the control divergence caused by the classical PD control method when the actual model is different from the ideal model, the controller has stronger robustness under parameter uncertainty, and meets the demand for attitude control during the autonomous take-off of deep space probes. This study provides an effective fuzzy control scheme for extraterrestrial liftoff, which provides a theoretical and methodological basis for further research.