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Lander attitude simulation platform device

A technology for simulating platforms and landers, applied in the aerospace field, can solve problems such as difficulty in simulating tests and high cost of landers, and achieve the effect of solving high simulation costs and low costs

Active Publication Date: 2016-03-30
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the cost of the lander is very high, and it is difficult to be used for simulation tests. Therefore, there is a need for a low-cost simulation device that can realize various landing attitude control functions

Method used

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  • Lander attitude simulation platform device

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Embodiment Construction

[0036] The technical solutions in the embodiments of the present invention will be clearly and completely described and discussed below in conjunction with the accompanying drawings of the present invention. Obviously, what is described here is only a part of the examples of the present invention, not all examples. Based on the present invention All other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0037] In order to facilitate the understanding of the embodiments of the present invention, specific embodiments will be taken as examples for further explanation below in conjunction with the accompanying drawings, and each embodiment does not constitute a limitation to the embodiments of the present invention.

[0038] Such as figure 1 As shown, a lander attitude simulation platform device provided by the present invention includes: a top plate 1, a frame 2, an attitude angle si...

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Abstract

The invention discloses an attitude simulation platform device for a lander. The attitude simulation platform device comprises a top plate, a rack, an attitude angle simulation module and a movable subsystem interface. The attitude angle simulation module is connected between the top plate and the rack, the attitude angle simulation module, the top plate and the rack rotate in a homocentric three-bearing mode, and by the adoption of three freedom degrees, a needed inclination direction, a pointing direction and an inclination angle are obtained. The subsystem interface is connected to the top surface of the top plate and used for locking / releasing a movable subsystem. The attitude angle simulation module comprises an upper wedge plate and a lower wedge plate, the wedge face of the upper wedge plate is connected with the wedge face of the lower wedge plate in a rotatable mode, the bottom surface of the upper wedge plate is connected with the top plate in a rotatable mode, and the bottom surface of the lower wedge plate is connected with the rack in a rotatable mode. The three freedom degrees include the situations that rotation of the lower wedge plate relative to the rack is used for controlling inclination direction of the top plate, rotation of the top plate relative to the upper wedge plate is used for controlling the pointing direction of the top plate, and relative rotation of the upper wedge plate and the lower wedge plate is used for controlling the inclination angle of the top plate.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a device for simulating the working state of a lander. Background technique [0002] In the process of planetary exploration in space, the rover (for the entire landing system, also called the mobile subsystem) is currently the most ideal device. When the rover reaches the surface of the target planet, the rover is separated from the lander after the landing is completed by the lander, so that it can successfully set foot on the surface of the planet. Just like the Yutu arrived on the moon, it also completed the landing on the moon through the lander. [0003] The mobile performance of the rover on the lander is an important prerequisite for the rover to transfer to the surface of the planet. It is usually necessary to test its maximum moving speed, attitude angle adaptability, static holding ability, braking ability, and traction ability in order to know its Performance ind...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00
Inventor 罗小桃肖杰詹涵菁姬鸣张晓伟刘殿富
Owner SHANGHAI AEROSPACE SYST ENG INST