Impact-reducing pad structure suitable for single machine with small heat conduction amount requirement on spacecraft

Abstract

The invention relates to an impact-reducing pad structure suitable for a single machine with a small heat conduction amount requirement on a spacecraft in the technical field of single-machine impact-reducing structures. The impact reducing pad structure comprises a fastening screw, a pressing gasket, an upper impact reducing rubber pad, a lower impact reducing rubber pad and a connecting embeddedpart; the fastening screw is used for fixing a single machine mounting foot and providing a pre-tightening force; the pressing gasket is used for pressing the upper impact-reducing rubber pad to enable the upper surface of the upper impact-reducing rubber pad to be uniformly stressed; the upper and lower impact-reducing rubber pads are respectively positioned above and below the single machine mounting foot; and the connecting embedded part is arranged in a cellular board and provides a connecting interface for the single machine. According to the structure, the impact-reducing rubber pads are padded above and below the single machine mounting foot, so that the impact-reducing efficiency is high; the impact-reducing rubber pad is formed by winding and pressing stainless steel wires, and has the characteristics of simple modification and light structure weight; any single machine with low requirement on heat conduction can adopt the impact-reducing pad structure, and the impact reducing pad structure has the characteristic of a wide application range.

Description

technical field [0001] The invention relates to the technical field of a stand-alone shock-reducing structure, in particular to a shock-reducing cushion structure suitable for a stand-alone stand-alone with a small demand for heat conduction on a spacecraft. Background technique [0002] When the weapon and arrow are separated or the compartment is separated, the impact generated by the explosive bolt will cause an instantaneous impact overload on the single machine on the star, which may cause damage to the structure of the single machine. In order to reduce the impact overload response of the single aircraft on the planet, a shock absorbing pad structure suitable for the single aircraft with small heat conduction requirements on the spacecraft was invented. Since the spacecraft needs to work in a harsh environment, in order to ensure that the temperature of the equipment and components on the spacecraft is within the range required by the mission during the working period ...

AI Technical Summary

Problems solved by technology

The impact reduction pad structure of the present invention solves the problem of excessive impact response of a single machine on the star, and has high impact reduction efficiency, small weight and wide application range

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