Solar sail spacecraft three-axis attitude control and execution mechanism

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 complex structure, etc., and achieve relief. The quality of the spacecraft and the effect of avoiding the risk of air leakage

Active Publication Date: 2017-02-22
NANJING UNIV OF SCI & TECH
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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 sm

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  • Solar sail spacecraft three-axis attitude control and execution mechanism
  • Solar sail spacecraft three-axis attitude control and execution mechanism
  • Solar sail spacecraft three-axis attitude control and execution mechanism

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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 th

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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

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Claims

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Application Information

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Owner NANJING UNIV OF SCI & TECH
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