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A three-axis attitude control actuator for solar sail spacecraft

A technology of three-axis attitude and actuators, which is applied in the direction of aerospace vehicle guidance devices, aerospace vehicle power supply systems, etc., can solve the problems of difficulty in controlling the deployment of small sails at the top, small rolling axis torque, and small adjustable range. Achieve the effect of reducing the mass of the spacecraft and avoiding the risk of air leakage

Active Publication Date: 2019-05-07
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • A three-axis attitude control actuator for solar sail spacecraft
  • A three-axis attitude control actuator for solar sail spacecraft
  • A three-axis attitude control actuator for solar sail spacecraft

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Embodiment

[0024] A novel solar sail attitude control actuator of the present invention includes a sliding mass-moving small sail (Sliding Masses-Moving Vanes, SMMV). The inventive device can generate the torque required for the three-axis attitude control of the solar sail, and fully utilizes sunlight for energy, has a relatively simple structure, and does not affect the deployment of the solar sail. In particular, the device can quickly provide the rolling shaft torque, and its amplitude can be adjusted in a large range.

[0025] combine figure 1 , the SMMV device is installed on the solar sail spacecraft, including a support rod 1, a slider 2, a small sail 3, a support frame 4 and a telescopic rod 6. The support rod 1 is arranged along the diagonal of the sail surface 7 of the square spacecraft, and the slider 2 slides along the support rod 1 . The small sail 3 is connected with the support frame 4 through the telescopic rod 6 . The bottom end of the support frame 4 is connected to...

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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 ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/44
CPCB64G1/24B64G1/44
Inventor 吴利平郭毓王璐吴益飞郭健陈庆伟
Owner NANJING UNIV OF SCI & TECH
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