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Integral vibration isolation platform of astrovehicle

A vibration isolation platform, spacecraft technology, applied in space navigation equipment, space navigation aircraft, aircraft and other directions, can solve problems such as adding spacecraft

Inactive Publication Date: 2006-08-30
郑钢铁 +3
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Aiming at the problem that the mass of the spacecraft must be greatly increased in order to ensure the successful launch of the spacecraft at the current stage, the present invention provides an overall vibration isolation platform for the spacecraft that can still ensure the successful launch of the spacecraft without significantly increasing the mass of the spacecraft

Method used

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  • Integral vibration isolation platform of astrovehicle
  • Integral vibration isolation platform of astrovehicle
  • Integral vibration isolation platform of astrovehicle

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specific Embodiment approach 1

[0005] Embodiment 1: This embodiment relates to an overall vibration isolation platform for a spacecraft, which includes a spacecraft connection end frame 1 and a launch vehicle connection end frame 2, and the spacecraft connection end frame 1 and launch vehicle connection end frame 2 An elastic element 3 and a damping element 4 are installed between them, and the ends of the elastic element 3 and the damping element 4 are respectively connected with the spacecraft connection end frame 1 and the launch vehicle connection end frame 2 .

[0006] The connecting end frame 1 of the spacecraft and the connecting end frame 2 of the launch vehicle of the present invention are connecting parts, so they are made of materials with higher rigidity; when working, the elastic element 3 is elastically deformed under the action of the vibration load, and the damping element 4 is elastically deformed. Deformation consumes vibration energy, thereby reducing the vibration load on the spacecraft a...

specific Embodiment approach 2

[0007] Embodiment 2: In this embodiment, both ends of the elastic element 3 and the damping element 4 are respectively connected to the spacecraft connection end frame 1 and the launch vehicle connection end frame 2 through ball bearings or flexible hinges 5 . refer to figure 1 In this embodiment, the elastic element 3 and the damping element 4 are arranged at intervals, and the damping element 4 is a magneto-rheological damper or an electromagnetic eddy current damper or a fluid damper. The damper is only subjected to axial forces through ball bearings or flexible joints.

specific Embodiment approach 3

[0008] Specific embodiment three: the difference between this embodiment and specific embodiment two is that the elastic element 3 and the damping element 4 are integrally structured, and its two ends are connected to the end frame 1 and the spacecraft through ball bearings or flexible hinges 5 The launch vehicle is connected to the end frame 2 for connection. The elastic element 3 and the damping element 4 in this embodiment are realized by metal rubber.

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Abstract

The present invention relates to an integral vibration-isolating platform for space vehicle. It is characterized by that between the space vehicle connection end frame and freight rocket end frame an elastic element and a damping element are mounted.

Description

technical field [0001] The invention relates to a vibration isolation and damping device used on a spacecraft. Background technique [0002] During the entire working life of the spacecraft, compared with the state of in-orbit flight, the dynamic environment of the spacecraft during the rocket launch process is the worst. A major effort in the structural strength design of spacecraft. The usual way is to increase the strength of the spacecraft itself, at the cost of increasing the quality of the spacecraft, thereby increasing the launch cost, and the increased quality is useless in the normal operation of the spacecraft in orbit. The vibration load received by the spacecraft mainly comes from the vibration of the launch vehicle engine, the aerodynamic load generated by the friction between the launch vehicle fairing and the atmosphere, and is transmitted to the spacecraft through the connecting parts. The existing star-rocket connectors mainly play a load-bearing role, wit...

Claims

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Application Information

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IPC IPC(8): B64G1/22
Inventor 郑钢铁刘丽坤梁鲁何玲
Owner 郑钢铁
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