Ball-type guiding damping mechanism suitable for general cone rod capturing mechanism of high-orbit satellite

A high-orbit satellite and damping mechanism technology, which is applied to motor vehicles, space navigation equipment, space navigation aircraft, etc., can solve problems such as unsmooth guidance, large frictional resistance in the guidance process, and no consideration of arrest, and achieve smooth guidance. , the effect of large relative velocity and angular velocity tolerance

Inactive Publication Date: 2019-03-15
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

A weak-impact universal capture mechanism and its guide damping device (ZL 201410783968.6 and ZL 201410784431.1) designed by the early research group for the capture and docking mechanism of satellites in orbit The guide damping of the capture process when t

Method used

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  • Ball-type guiding damping mechanism suitable for general cone rod capturing mechanism of high-orbit satellite
  • Ball-type guiding damping mechanism suitable for general cone rod capturing mechanism of high-orbit satellite
  • Ball-type guiding damping mechanism suitable for general cone rod capturing mechanism of high-orbit satellite

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Embodiment Construction

[0023] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings.

[0024] Such as figure 2 , image 3 As shown, a ball-type guide damping mechanism suitable for the general taper rod capture mechanism of high-orbit satellites, including rocker arm 1, rocker arm mounting seat 2, roller 3, sliding seat 4, connecting arm 5, damping rod 6, pad Plate 7, damping rod support seat 8, guide cylinder 9. Wherein, one end of the guide cylinder 9 is installed with a rocker mounting seat 2, and the sliding seat 4 is installed on the guide cylinder 9, and slides along the outer wall of the guide cylinder 9; the ring-shaped damping rod support seat 8 is installed on the flange plate at the other end of the guide cylinder 9;

[0025] The rocker arm 1 is evenly distributed around the central axis of the guide ...

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Abstract

The invention relates to a ball-type guiding damping mechanism suitable for a general cone rod capturing mechanism of a high-orbit satellite, which comprises a rocker arm mounting seat (2), roller rocker arm structures and the like, wherein one end of a guide cylinder (9) is provided with the rocker mounting seat (2), and a sliding seat (4) is arranged on the guide cylinder (9) and slides along an outer wall of the guide cylinder (9); an annular damping rod supporting seat (8) is arranged on a flange plate at the other end of the guide cylinder (9); the roller rocker arm structures are uniformly distributed around a central axis of the guide cylinder (9), the one end of each roller rocker arm structure is rotationally connected with the rocker arm mounting seat (2), and the other end of the each roller rocker arm structure is rotationally connected with an end part of a damping rod (6); the one end of the damping rod (6) connected with the roller rocker arm structure is fixed on the flange plate at the end part of the sliding seat (4), and the other end of the damping rod (6) extends into a damping rod mounting seat (8) and slides along an inner wall of the damping rod mounting seat (8). The ball-type guiding damping mechanism suitable for the general cone rod capturing mechanism of the high-orbit satellite can adapt to a rolling target capture under a condition of weak impactand can provide larger relative speed and angular velocity tolerance for the cone rod capturing mechanism.

Description

technical field [0001] The invention belongs to the technical field of on-orbit service and maintenance of spacecraft, and relates to a ball-type guiding and damping mechanism. Background technique [0002] Geostationary Orbit (GEO) is an important earth orbit resource for human beings, and the on-orbit resources are limited by the orbital position and are extremely scarce. However, with the rapid development of space missions, the total number of satellites in the GEO belt (GEO±200km) contains more than 40% of uncontrollable or abandoned satellites and their wreckage. Security poses a threat, and it also leads to a serious waste of GEO orbital resources. Another statistics show that among the GEO satellites that have failed in orbit, more than 50% of the failures are due to the loss of a certain function of the service system, while the payload and platform main functions that account for more than 70% of the satellite cost are intact. Therefore, there is an urgent need t...

Claims

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Application Information

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IPC IPC(8): B64G1/64B64G4/00
CPCB64G1/646B64G4/00
Inventor 黄龙飞李志黄剑斌蒙波韩旭张志民庞羽佳王尹
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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