Double-direction solar panel control method applicable to inclined orbit satellite

An inclined orbit, two-way control technology, applied in the direction of adaptive control, control using feedback, general control system, etc., can solve problems such as high cost, immature technology of two-dimensional drive mechanism, unfavorable satellite equipment, etc., to achieve positive and the effect of backdrive control

Active Publication Date: 2014-12-03
SHANGHAI XINYUE METER FACTORY
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Problems solved by technology

For two-dimensional motion, a two-dimensional driving mechanism must be used to drive the sailboard to achieve two-dimensional tracking motion, but the technology of the two-dimensional driving mechanism is not yet mature, and the cost is high, which is not conducive to the current satellite equipment

Method used

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  • Double-direction solar panel control method applicable to inclined orbit satellite
  • Double-direction solar panel control method applicable to inclined orbit satellite
  • Double-direction solar panel control method applicable to inclined orbit satellite

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Embodiment Construction

[0047] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0048] The invention discloses a sailboard two-way control method adapted to inclined orbit satellites. The purpose of the sailboard's directional control to the sun is to make the sailboard drive error meet the index requirements, that is, the angle between the sailboard normal and the sun vector meets the index requirements. Realize that the surface of the windsurfing battery faces the sun all the time. Based on the mathematical model (law of the sun's motion) and the requirements of control indicators, the design of the sun-oriented control law of the sailboard can be started.

[0049] like figure 1 As shown, the sailboard two-way control method adapted to inclined orbit satellites includes the following steps:

[0050] Step 1. Establish a mathematical model of the position relationship between the inclined orbit satellite and the sun, and ...

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Abstract

The invention discloses a double-direction solar panel control method applicable to an inclined orbit satellite. The double-direction solar panel control method comprises the steps that a mathematic model of the positional relation between the inclined orbit satellite and the sun is built and used for quantitative description of the motion law of the sun relative to the satellite; a solar panel driving error is defined according to the mathematic model and used as input of solar panel driving control; the law of solar panel capture control is determined, so that a solar panel is made to find the sun; the law of solar panel tracing control is determined, so that solar panel sun-targeted orientation is realized through sun tracing. According to the double-direction solar panel control method applicable to the inclined orbit satellite, the solar panel driving law and satellite yawing maneuvering are combined, and the problem that the inclined orbit satellite realizes sun-targeted orientation through a one-dimensional solar panel driving mechanism is solved; judgment and adjustment can be carried out autonomously according to the motion direction of the sun according to the forward flight and inverted flight of the satellite, and correct capture of the sun by the solar panel under different initial conditions is realized; forward driving control and inverted driving control of sun-targeted orientation of the solar panel are realized according to the forward flight and inverted flight of the satellite.

Description

technical field [0001] The invention relates to a driving control method for a satellite solar sail, in particular to a two-way control method for a sail adapting to satellites in inclined orbits. Background technique [0002] The sunlight irradiation situation for satellites in inclined orbits is more complicated. The sun will move continuously from one side of the orbital plane to the other side, and the angle between the sun’s light and the orbital plane (sun altitude angle β) will be between -90° and 90° change continuously. That is, the motion of sunlight relative to the satellite body is a two-dimensional motion, which includes both the rotational motion around the pitch axis due to orbital motion and the rotational motion around the yaw axis due to orbital precession. In order to ensure that satellites in inclined orbits can obtain solar energy, the sail must always be oriented toward the sun. For two-dimensional motion, a two-dimensional driving mechanism must be u...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D3/12G05B13/04
Inventor 丰保民朱虹叶立军万海音陈占胜徐峰修艳红冒海飞
Owner SHANGHAI XINYUE METER FACTORY
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