A solar wing layout structure of a high-precision spacecraft

Abstract

The invention discloses a solar wing layout structure of a high-precision spacecraft. A top solar wing main plate and top solar wing side plates form a top solar wing which is fixedly installed on a platform top plate through bolts; an included angle between the top solar wing main plate and each top solar wing side plate is 120 degrees; the section of a spacecraft platform is in the shape of a regular hexagon, the top solar wing main plate is rectangular, each top solar wing side plate is triangular, and a bottom solar wing is installed at the bottom of a platform bottom plate; top solar wing honeycomb sandwich embedded parts are pre-embedded in the top solar wing main plate and the top solar wing side plates, and platform top plate honeycomb sandwich embedded parts are pre-embedded in the platform top plate; and a top solar wing pressing rod is installed among the top solar wing main plate, the top solar wing side plates and a payload. The solar wing layout structure disclosed by the invention can effectively improve the connection stiffness between the solar wing and the spacecraft platform so as to reduce the micro-vibration of the solar wing and improve the attitude stability of the spacecraft platform, and has the advantages of simple configuration, convenient connection and obvious effect.

Description

technical field [0001] The invention relates to the field of spacecraft, in particular to a solar wing layout structure of a high-precision spacecraft, which can be applied to spacecraft with relatively high attitude stability. Background technique [0002] With the development of my country's spacecraft in the direction of high precision and high stability, the payloads carried by it have higher and higher requirements for the attitude stability of the platform. It is necessary to minimize the micro-vibration of the spacecraft platform to improve the attitude stability of the platform. [0003] One of the main sources of spacecraft microvibration is solar wing flexural vibration. The current spacecraft platform basically uses movable solar wings, and the connection stiffness with the platform is low. When the spacecraft performs orbit transfer or attitude adjustment, it will produce micro-vibration, thereby reducing the attitude stability of the platform. In addition, in o...

AI Technical Summary

Problems solved by technology

The current spacecraft platform basically uses movable solar wings, and the connection stiffness with the platform is low. When the spacecraft performs orbit transfer or attitude adjustment, it will produce micro-vibration, thereby reducing the attitude stability of the platform.

In addition, in order to minimize the weight of the spacecraft, the solar wing basically uses lightweight materials such as honeycomb sandwich panels, which further aggravates the micro-vibration

Seriously, when the solar wing enters and exits the shadow of the sun, due to the drastic change of the external heat flow, it may cause thermal flutter of the solar wing, which seriously reduces the attitude stability of the spacecraft platform

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