Solar cell array installation control strategy construction method and system
A technology of solar cell array and control strategy, which is applied in the power supply system, transportation and packaging of space navigation vehicle, space navigation equipment, etc., and can solve the problems of insufficient illumination efficiency and complicated on-orbit implementation.
Active Publication Date: 2020-11-06
SHANGHAI SATELLITE ENG INST
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[0003] Patent document CN106364702A discloses a solar cell array control strategy method adapted to inclined orbit yaw maneuvering satellites. It is mainly aimed at general inclined orbit design, which requires satellites to implement autonomous yaw attitude maneuver control, and the solar array illumination efficiency can only be guaranteed to be better than 0.71, there are problems of complex on-orbit implementation and insufficient lighting efficiency
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[0069] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.
[0070] like Figure 1-4 As shown, a solar cell array installation control strategy construction method provided according to the present invention includes:
[0071] Step S1: According to the parameters of the selected sun-synchronous orbit, analyze the satellite's on-orbit illumination conditions, and obtain the satellite's orbital illumination angle variation range information;
[0072] Step S2: According to the satellite layout constraints, determine the maximum deflection angle of the solar cell ar...
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The invention provides a solar cell array installation control strategy construction method and system, and the method comprises the steps: S1, analyzing the on-orbit illumination condition of a satellite according to the parameters of a selected sun synchronous orbit, and obtaining the orbit illumination angle change range information of the satellite; S2, determining a biased maximum angle of the solar cell array according to a satellite layout constraint condition, and obtaining biased maximum angle confirmation result information of the solar cell array; S3, according to the maximum valueand the minimum value of the on-orbit illumination angle of the satellite and the biased maximum angle of the solar cell array; S4, obtaining solar cell array installation strategy selection result information and worst illumination efficiency analysis result information of the sun synchronous orbit at any place; and S5, obtaining solar array installation control result information suitable for all-local-time solar synchronous orbit networking. The method is mainly oriented to satellite structure consistency in solar synchronous orbit networking, yaw attitude maneuver is not needed, and the illumination efficiency is better.
Description
technical field [0001] The present invention relates to the technical field of solar array installation control, in particular, to a solar cell array installation control strategy construction method and system, and in particular to a satellite solar cell array installation control strategy adapted to batch networking of sun-synchronous orbits in all places design method. Background technique [0002] Low Earth orbits can be divided into zero-inclination orbits, general-inclination orbits, and sun-synchronous orbits according to their inclination angles. Sun-synchronous orbits are often selected as remote sensing satellites, Orbits of communication satellites. Especially for remote sensing satellite missions, the sun-synchronous orbit in the morning, morning or afternoon is generally chosen at the place of the descending node, which can ensure relatively stable lighting conditions and energy supply on the star. With the increasingly urgent demands for earth-height revisit ...
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IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 樊炜陈锋李金亮曲耀斌曹岸杰仲惟超凌惠祥
Owner SHANGHAI SATELLITE ENG INST