Control method for double-shaft solar wing driving mechanism of near-earth inclined orbit satellite

A technology of solar wing drive and inclined orbit, which is applied in the field of satellite control, can solve the problems of complex configuration, exceeding the satellite attitude control system, and the interference of the gravity gradient moment of the two wings of the solar wing, so as to achieve the effect of optimizing the configuration of the mechanism system and reducing the interference

Active Publication Date: 2021-06-11
航天科工空间工程发展有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The A-axis rotates 360° at a constant speed within one orbital period. This installation method generally requires two A-axis and B-axis, and the configuration is complicated. In addition, under certain lighti

Method used

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  • Control method for double-shaft solar wing driving mechanism of near-earth inclined orbit satellite
  • Control method for double-shaft solar wing driving mechanism of near-earth inclined orbit satellite
  • Control method for double-shaft solar wing driving mechanism of near-earth inclined orbit satellite

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no. 1 example

[0045] The satellite orbit height of the present embodiment is 1000km (the average radius of the earth is 6378.137km), and the orbital inclination angle is 80°

[0046] One embodiment of the present invention discloses a method for controlling a dual-axis solar wing drive mechanism of a low-earth inclined orbit satellite.

[0047] Said institutions include:

[0048] First axis mechanism, star body, second axis mechanism and solar wing;

[0049] The first shaft mechanism is installed on the star body, the second shaft mechanism is connected with the first shaft mechanism through a connecting rod, and the solar wing is connected with the second shaft mechanism.

[0050] In this embodiment, the first axis mechanism is figure 1 In the B-axis mechanism, the second axis mechanism is figure 1 The A-axis mechanism in.

[0051] Such as figure 2 As shown, the method includes:

[0052] S100. Set the maximum rotational angular velocity allowed by the first axis; the satellite att...

no. 2 example

[0067] Such as figure 1 As shown, an embodiment of the present invention also discloses a dual-axis solar wing drive mechanism for a low-earth inclined orbit satellite, said mechanism comprising:

[0068] First axis mechanism, star body, second axis mechanism and solar wing;

[0069] In this embodiment, the first axis mechanism is figure 1 In the B-axis mechanism, the second axis mechanism is figure 1 The A-axis mechanism in.

[0070] The B-axis mechanism is installed on the star body, the A-axis mechanism is connected with the B-axis mechanism through a connecting rod, and the solar wing is connected with the A-axis mechanism.

[0071] The invention provides a dual-axis solar wing driving mechanism for a near-earth inclined orbit satellite, which optimizes the configuration of the mechanism system and reduces the interference of the movement of the solar sail to the attitude of the whole satellite.

no. 3 example

[0073] Figure 5 A schematic structural diagram of a computer device provided by another embodiment of the present application is shown. Figure 5 The computer device 50 shown is only an example, and should not impose any limitation on the functions and scope of use of the embodiments of the present application. Such as Figure 5 As shown, computer device 50 takes the form of a general-purpose computing device. Components of computer device 50 may include, but are not limited to: one or more processors or processing units 500 , system memory 516 , bus 501 connecting various system components including system memory 516 and processing unit 500 .

[0074] Bus 501 represents one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor, or a local bus using any of a variety of bus structures. These architectures include, by way of example, but are not limited to Industry Standard Archite...

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Abstract

The embodiment of the invention discloses a control method for a double-shaft solar wing driving mechanism of a near-earth inclined orbit satellite. The mechanism comprises a first shaft mechanism, a satellite body, a second shaft mechanism and a solar wing, the first shaft mechanism is installed on a star body, the second shaft mechanism is connected with the first shaft mechanism through a connecting rod, and the solar wing is connected with the second shaft mechanism. According to the installation and control method for the double-shaft solar wing driving mechanism of the near-earth inclined orbit satellite, the configuration of a mechanism system is optimized, and the interference of the movement of a solar panel on the attitude of the whole satellite is reduced. Meanwhile, a control parameter calculation method and detailed steps of the solar wing driving mechanism under different illumination conditions are given, and the satellite can obtain solar energy to the maximum extent on the premise that the requirement of the whole satellite attitude control system is met.

Description

technical field [0001] The invention relates to the field of satellite control. More specifically, it relates to a method for controlling a dual-axis solar wing drive mechanism of a low-earth inclined orbit satellite, a drive mechanism, a computer device, and a computer-readable storage medium. Background technique [0002] Satellites in orbit are in the light period most of the time. Solar cells are semiconductor devices that convert light energy into electrical energy. Solar cell arrays use solar cells to convert light energy into electrical energy through physical changes. It is currently the first choice for satellites. power generation device. According to the structural classification, solar cell arrays can be divided into two types: body-mounted and deployable. The solar cell array installed on the surface of the star structure is called a body-mounted solar cell array, and the solar cell array installed outside the star and unfolded and locked by a mechanism is cal...

Claims

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Application Information

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IPC IPC(8): B64G1/44B64G1/24
CPCB64G1/443B64G1/244Y02E10/50
Inventor 雷亚珂向开恒王鹏飞张楠
Owner 航天科工空间工程发展有限公司
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