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Double-motor rope-type solar wing auxiliary turning mechanism

A flipping mechanism and dual-motor technology, applied in aerospace equipment, simulators of space navigation conditions, transportation and packaging, etc., can solve the problems of insufficient repeatability and stability of the solar wing deployment mechanism, and achieve strong applicability, The structure is simple and the effect of meeting the requirements of the design

Active Publication Date: 2015-10-28
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem of insufficient repeatability and stability of the existing solar wing deployment mechanism for ground tests, the present invention further proposes a double-motor rope-type solar wing auxiliary turning mechanism

Method used

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  • Double-motor rope-type solar wing auxiliary turning mechanism
  • Double-motor rope-type solar wing auxiliary turning mechanism
  • Double-motor rope-type solar wing auxiliary turning mechanism

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Experimental program
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specific Embodiment approach 1

[0007] Specific implementation mode 1: Combination Figure 1 to Figure 3 To explain this embodiment, the dual-motor rope-type solar wing auxiliary turning mechanism in this embodiment includes a hanger 1, a left wire retracting mechanism 2, a right wire retracting mechanism 3, and a spring assembly 4. The hanger 1 is made of a hanger column. The inverted T-shaped hanger 1 composed of 1-1 and the hanger bottom plate 1-2, the left wire retracting mechanism 2 is installed on the left side of the lower surface of the hanger bottom plate 1-2, and the right wire retracting mechanism 3 is installed on the hanger bottom plate 1-2 On the right side of the lower surface, the left steel wire retracting mechanism 2 and the right steel wire retracting mechanism 3 are connected to the solar wing 5 through the spring assembly 4.

[0008] In this embodiment, the left wire retracting mechanism 2 and the right wire retracting mechanism 3 are fixed at the lower part of the hanger bottom plate 1-2, ...

specific Embodiment approach 2

[0009] Specific implementation manner two: combination Image 6 To illustrate this embodiment, the spring assembly 4 of the dual-motor rope-type solar wing auxiliary turning mechanism in this embodiment includes a left spring 4-1, a right spring 4-2, a connecting ring 4-3 and a pull rod 4-4, and a left spring 4 One end of -1 and one end of the right spring 4-2 are both connected to one end of the tie rod 4-4 through the connecting ring 4-3, and the other end of the tie rod 4-4 is provided with a through hole 4-4-1 connected to the sun wing 5 . The other components and connection relationships are the same as in the first embodiment.

specific Embodiment approach 3

[0010] Specific implementation mode three: combination Figure 4 To illustrate this embodiment, the left wire retracting mechanism 2 of the dual-motor rope-type solar wing auxiliary turning mechanism in this embodiment includes a left motor 2-1, a left reducer 2-2, a left sheave 2-3, and a left wire 2 -4. The left coupling 2-5 and the left protective cover 2-6, the left motor 2-1 is connected to the left reducer 2-2 through the left protective cover 2-6, and the rotating shaft of the left motor 2-1 is connected to the left The shaft gear 2-5 is connected with the input shaft of the left reducer 2-2, and the left coupling 2-5 is located in the left protective cover 2-6, and the left sheave 2-3 is set on the output of the left reducer 2-2 On the shaft, one end of the left steel wire 2-4 is connected to the left sheave 2-3, and the other end of the left steel wire 2-4 is connected to the other end of the left spring 4-1. Other components and connection relationships are the same a...

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Abstract

The invention relates to a solar wing auxiliary turnover mechanism, in particular to a double-motor rope type solar wing auxiliary turnover mechanism. The double-motor rope type solar wing auxiliary turnover mechanism aims to solve the problems that an exiting solar wing unfolding mechanism for ground tests is poor in repeatability and stability. The double-motor rope type solar wing auxiliary turnover mechanism comprises a hanging bracket, a left steel wire reeling and unreeling mechanism, a right steel wire reeling and unreeling mechanism and a spring assembly, wherein the hanging bracket is an inverted-T-shaped hanging bracket formed by a hanging bracket stand column and a hanging bracket base plate, the left steel wire reeling and unreeling mechanism is mounted on the left side of the lower surface of the hanging bracket bottom plate, the right steel wire reeling and unreeling mechanism is mounted on the right side of the lower surface of the hanging bracket bottom plate, and the left steel wire reeling and unreeling mechanism and the right steel wire reeling and unreeling mechanism are connected with solar wings through the spring assembly. The double-motor rope type solar wing auxiliary turnover mechanism is used for solar wing unfolding tests.

Description

Technical field [0001] The invention relates to a solar wing auxiliary turning mechanism, in particular to a dual-motor rope type solar wing auxiliary turning mechanism. Background technique [0002] In the thermal balance experiment of the lander, the solar wing needs to be deployed and retracted many times in the space environment simulator. Since the solar wing drive mechanism does not have the ability to deploy and retract on the ground, it is necessary to develop a set of solar wing deployment mechanism for ground test, which can be reliably realized. The deployment angle of the solar wing is adjusted individually, and measures such as mechanical limit are adopted to ensure the safety of the detector system. Existing solar wing deployment mechanisms have problems with vacuum drive motors that are difficult to obtain, cannot achieve multiple deployments, the drive mechanism is too large, the connection relationship is difficult to achieve, it is easy to cause damage to the so...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00
Inventor 高海波邓宗全郑军强丁亮刘振李楠
Owner HARBIN INST OF TECH