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Ball bearing assembly for satellite deployment mechanism

A technology for deploying mechanisms and spherical bearings, applied to bearing components, shafts and bearings, sliding contact bearings, etc., can solve problems such as no explanation or report, no data collected, etc., and achieve the effect of improving functional reliability

Inactive Publication Date: 2011-08-10
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] At present, there is no description or report of a technology similar to the present invention, and no domestic similar data has been collected yet.

Method used

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  • Ball bearing assembly for satellite deployment mechanism
  • Ball bearing assembly for satellite deployment mechanism

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Embodiment Construction

[0014] Preferred embodiments of the present invention will be described below in conjunction with the accompanying drawings.

[0015] Accompanying drawing is the structure schematic diagram of the spherical bearing assembly of the satellite deployment mechanism of the present invention, as figure 1 As shown, the device includes:

[0016] Outer ring 1, whose outer surface is coated with high-vacuum solid lubricating film, is connected with the male hinge of the expansion mechanism; middle ring 2; spherical inner ring 3, whose outer surface is coated with high-vacuum solid lubricating film, and is connected with the female hinge of the expansion mechanism. When the unfolding mechanism moves, the outer ring 1 and the middle ring 2 or the middle ring 2 and the spherical inner ring 3 rotate relative to each other.

[0017] The outer ring adopts a ring structure, with an outer diameter of Φ17.984mm and an inner diameter of Φ15mm. The material is made of stainless bearing steel 9Cr1...

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Abstract

The invention relates to a ball bearing assembly for a satellite deployment mechanism. The invention aims to provide a ball bearing assembly for a satellite deployment mechanism, which can improve the reliability of the ball bearing assembly and meets the use requirements of the satellite deployment mechanism under the space environment. The ball bearing assembly is characterized in that the ball bearing assembly comprises the following parts, namely an outer ring, a middle ring and a spherical inner ring, wherein the outer surface of the outer ring is coated with a high-vacuum solid lubricating film and is connected with the deployment mechanism through a male hinge; and the outer surface of the spherical inner ring is coated with a high-vacuum solid lubricating film and is connected with the deployment mechanism through a female hinge. When the deployment mechanism moves, the outer ring and the middle ring or the middle ring and the spherical inner ring generate opposite rotation. The ball bearing assembly reduces the movement friction damping of the employment mechanism and improves the functional reliability of a bearing; and even if the failure happens between the spherical inner ring or the outer ring and the middle, the middle ring and the outer ring or the spherical inner ring still can keep the rotation function.

Description

technical field [0001] The invention relates to satellite equipment, in particular to a spherical bearing assembly for a satellite deployment mechanism. Background technique [0002] The spherical bearing assembly is the key component of the satellite deployment mechanism and the core element that affects the success or failure of the satellite. In order to meet the use requirements of the satellite deployment mechanism in the space environment, the configuration design, material selection, bearing clearance control, and coating design of the spherical bearing assembly are particularly important. If the configuration design is unreasonable, the reliability of the spherical bearing assembly will be reduced; the material If the selection is unreasonable, it is prone to rust and cause the expansion mechanism to be stuck; if the bearing clearance is too small, the adaptability of the expansion mechanism to the space environment is not strong, and if the clearance is too large, t...

Claims

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Application Information

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IPC IPC(8): F16C23/02F16C33/10F16C33/12
Inventor 吴远波杜江华顾志悦茅敏
Owner SHANGHAI SATELLITE ENG INST
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