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Sun-facing orientation control method for single-degree-of-freedom solar panel of inclined orbit satellite

A solar panel and directional control technology, which is applied in attitude control, space navigation vehicle guidance device, space vehicle power supply system, etc., can solve the problems of satellite attitude disturbance and high requirements of satellite attitude control system, and achieves the reduction of energy consumption, The effect of improving attitude control accuracy and excellent comprehensive performance

Active Publication Date: 2020-05-19
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

Although the real-time yaw maneuver control improves the accuracy of the sailboard to the sun, it also brings a certain disturbance to the satellite attitude, which has higher requirements on the satellite attitude control system

Method used

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  • Sun-facing orientation control method for single-degree-of-freedom solar panel of inclined orbit satellite
  • Sun-facing orientation control method for single-degree-of-freedom solar panel of inclined orbit satellite

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Embodiment Construction

[0036] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with specific embodiments of the present invention and corresponding drawings. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts fall within the protection scope of the present invention.

[0037] The technical solutions provided by the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0038] An embodiment of the present invention provides a sun-oriented control method for a single-degree-of-freedom solar panel on an inclined-orbit satellite, the method comprising:

[0039] Acco...

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Abstract

The invention discloses a sun-facing orientation control method for a single-degree-of-freedom solar panel of an inclined orbit satellite. The method comprises the steps: a solar panel sun-facing control mode is selected according to a satellite sun altitude angle beta; when the absolute value of beta is smaller than or equal to 15 degrees, the satellite does not yaw, and a solar panel driving mechanism drives the solar panel to turn over. When the absolute value of beta is larger than or equal 15 degrees and smaller than or equal to 45 degrees, the satellite yaws at a fixed angle, and the solar panel driving mechanism drives the solar panel to turn over. When the absolute value of beta is larger than 45 degrees, the satellite yaws in real time, and the solar panel driving mechanism drivesthe solar panel to turn over. The invention discloses the sun-facing orientation control method for the single-degree-of-freedom solar panel of the inclined orbit satellite, the relation between thesolar energy obtaining efficiency and the attitude control precision is comprehensively considered, on the premise that the good sun-facing performance of the solar panel is guaranteed, energy consumption and the design difficulty of an attitude and orbit control system can be reduced, the satellite attitude control precision is improved, and a satellite can achieve the better comprehensive performance.

Description

technical field [0001] The invention relates to the technical field of space-borne equipment, in particular to a sun-oriented control method for a single-degree-of-freedom solar panel of an inclined-orbit satellite. Background technique [0002] Inclined-orbit satellites refer to satellites with an inclination angle > 0 between the orbit of an artificial satellite orbiting the earth’s circular motion and the equator. This kind of satellite can conduct fixed-point reconnaissance of a place, and can also conduct meteorological observations at different latitudes. For a satellite with a single-degree-of-freedom solar panel, due to the change of the right ascension of the ascending node and the revolution of the earth, the angle between the sun vector and the orbital plane of the satellite changes at a large angle, resulting in a large loss of solar energy. [0003] In the prior art, the real-time yaw movement is generally performed by satellites, and the driving mechanism of...

Claims

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Application Information

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IPC IPC(8): G05D1/08B64G1/24B64G1/44
CPCB64G1/44B64G1/24Y02E10/50
Inventor 绳涛熊亚洲赵勇陈利虎杨磊白玉铸宋新杨园华
Owner NAT UNIV OF DEFENSE TECH
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