A three-axis attitude control actuator for solar sail spacecraft

Abstract

The invention relates to a solar sail spacecraft three-axis attitude control and execution mechanism which is divided into a sliding mass block and a moving small sail. The solar sail spacecraft three-axis attitude control and execution mechanism comprises a support rod, the sliding bock, the small sail, a telescopic rod and a support frame. The support rod supports the spacecraft sail face, and the sliding block is embedded on the support rod and can slide along the support rod. One end of the telescopic rod is connected with the small sail, and the other end of the telescopic rod is fixedly connected to the support frame. The telescopic rod can telescope and rotate, the length of the telescopic rod is adjusted through linear telescoping, and the small sail is driven to rotate through rotation of the telescopic rod. The bottom end of the support frame is fixed to the geometric center of the spacecraft sail face, and the top end of the support frame is connected with a spacecraft load. According to the solar sail spacecraft three-axis attitude control and execution mechanism, torque needed by solar sail three-axis attitude control, sunlight is completely utilized for supplying energy, the structure is simple, and unfolding of the spacecraft sail face is not affected. By means of the solar sail spacecraft three-axis attitude control and execution mechanism, rolling shaft torque can be provided rapidly, and adjustable range of amplitude of the torque is large.

Description

technical field [0001] The invention relates to an attitude control actuator of a solar sail spacecraft, in particular to a three-axis attitude control actuator completely powered by sunlight. Background technique [0002] Solar sail spacecraft gain orbital propulsion by bouncing sunlight off their huge sails. Changing the attitude of the sun and adjusting the angle of sunlight reflection can adjust the amplitude and direction of the propulsion force, and then change the flight trajectory of the spacecraft. Therefore, the flight mission of the solar sail depends on its attitude control. Complex orbital missions correspond to various attitude maneuvers, and traditional spin stabilization cannot meet the requirements of changing attitudes. In order to serve solar sail orbit transfer and deep space flight missions, it is necessary to study an efficient and accurate three-axis attitude control system. [0003] To achieve three-axis attitude control, the solar sail spacecraft ...

AI Technical Summary

Problems solved by technology

However, the rolling axis stabilization bar and the method of flipping the sail surface are more complicated in structure, and the sail surface rotates during use, which affects orbital propulsion; the jet thruster consumes chemical energy and requires propellant to be carried, which is not suitable for deep space flight; the top controls the small sail itself Unfolding is more difficult, which also makes the sail unfolding mechanism more complicated; in addition, the rolling shaft torque provided by the above actuators is small, and the adjustable range is small. When the required rolling shaft control torque is large, it is difficult to quickly and effectively Output required torque

Images