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Design method for solar panel device of sun-synchronous orbit satellite and solar panel device designed by adopting method

A technology of sun-synchronous orbit and solar panels, applied in the field of satellite solar panels, can solve the problems of long development cycle, difficulty in adjusting the attitude of solar panels, and high production cost, and achieve the effects of short research cycle, simple structure and low cost.

Pending Publication Date: 2022-07-12
哈尔滨工大卫星技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problems of difficulty in attitude adjustment, high production cost and long development cycle of existing solar panels, and provide a solar panel device design method for sun-synchronous orbit satellites and a solar panel device designed by this method

Method used

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  • Design method for solar panel device of sun-synchronous orbit satellite and solar panel device designed by adopting method
  • Design method for solar panel device of sun-synchronous orbit satellite and solar panel device designed by adopting method

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Embodiment approach 1

[0029] Embodiment 1, such as figure 1 As shown, a method for designing a solar panel device for a sun-synchronous orbit satellite, the method includes:

[0030] establishing a satellite body coordinate system, the satellite body coordinate system coincides with the orbital coordinate system;

[0031] Specifically, the coordinate system is defined as follows: this coordinate system is based on a circular orbit, and the coordinate system of the satellite body is based on the diagram, that is, Xb points to the direction of the satellite's running speed, Zb points to the direction of the ground load at the bottom of the satellite, and Yb is determined by The right hand rule is given. Orbital coordinate system VVLH (Vehicle Velocity, Local Horizontal) X-axis points to the direction of orbital velocity, Z-axis points to the center of the earth, and Y-axis is perpendicular to the direction of the orbital surface by the right-hand rule.

[0032] Since the attitude of some satellites...

Embodiment approach 2

[0040] Embodiment 2. This embodiment is a further limitation of the method for designing a solar panel device for a solar synchronous orbit satellite described in Embodiment 1. In this embodiment, the angle β between the sun vector and the orbital plane is A further limitation is made, which specifically includes: the angle β between the sun vector and the orbital plane is the average value of the angle between the sun vector and the orbital plane corresponding to several time periods.

[0041] First calculate the beta angle of the sun-synchronous orbit, and based on the average beta angle to determine the angle between the windsurfing board and the axis of rotation.

[0042] Average beta angle calculation method:

[0043] First, enter the relationship between the beta angle and the moment in a period of time as:

[0044] β=f(t)

[0045] then the average beta angle for:

[0046]

[0047] where: t n is a time interval for a period of time, f(t n ) is the beta angle ...

Embodiment approach 3

[0051] Embodiment 3. A solar panel device using the solar panel device design method for a solar synchronous orbit satellite according to any one of Embodiments 1 and 2. The device includes: a solar panel, a solar sail Plate drive, connecting rod and angle locking device;

[0052] The connecting rod is on the same straight line with the rotation axis of the solar panel;

[0053]The angle locking device is used to connect the connecting rod and the solar panel, and the included angle between the straight line where the connecting rod is located and the normal line of the solar panel is α;

[0054] It should be noted that the rotation axis of the windsurfing board is not coplanar with the plane where the windsurfing board is located, that is, the axis intersects the windsurfing board surface, and the angle is equal to the angle between the sun vector and the orbital plane.

[0055] The other end of the connecting rod is connected with the solar panel driving device, and the sol...

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Abstract

The invention discloses a design method of a solar panel device of a sun-synchronous orbit satellite and the solar panel device designed by adopting the method, belongs to the technical field of satellite solar panels, and solves the problems of difficulty in attitude adjustment, high manufacturing cost and long development period of an existing solar panel. The method comprises the following steps: establishing a satellite body coordinate system, wherein the satellite body coordinate system coincides with an orbital coordinate system; the rotating shaft of the solar panel coincides with the rotating axis of the sun vector; calculating an included angle beta between the sun vector and the orbital plane; according to the included angle beta, the included angle alpha between the normal of the solar panel and the rotating shaft of the solar panel is obtained, and the included angle alpha and the included angle beta are complementary angles; and designing the solar panel device according to the included angle alpha. The method is suitable for the design of the solar panel device of the remote sensing satellite with the unchanged attitude.

Description

technical field [0001] The present application relates to the technical field of satellite solar panels, and in particular, to a method for designing a solar panel device for a solar synchronous orbit satellite and a solar panel device designed by using the method. Background technique [0002] The solar panel part of the existing sun-synchronous orbit satellite adopts a single-axis SADA (solar panel drive mechanism) and the SADA rotation axis is perpendicular to the solar panel method, and the attitude control system of the satellite can be used to achieve sun orientation. [0003] Existing solar panels need to use a solar panel servo system, so that the solar array always points to the sun, and the load points to the direction of the mission, so as to ensure sufficient energy for the satellite system under the condition of uninterrupted mission. Most of the existing single-axis windsurfing drive devices use motor servo systems, including stepper motors, reducers, and servo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64G1/44
CPCB64F5/00B64G1/443Y02E10/50
Inventor 马维良吴凡奚瑞辰董旭乐欣龙苏莹莹帅剑澜
Owner 哈尔滨工大卫星技术有限公司
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