Shock-absorbing support structure suitable for single aircraft with small heat conduction requirements on spacecraft
A support structure and thermal conductivity technology, which is applied to space navigation equipment, space navigation aircraft, motor vehicles, etc., can solve the problems of not considering related design, complex device structure, etc., and achieve light weight, wide application range, bearing capacity powerful effect
Active Publication Date: 2020-11-24
SHANGHAI SATELLITE ENG INST
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- Description
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- Application Information
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Problems solved by technology
However, the structure of the device is still relatively complicated, and it has not considered the relevant design suitable for a single unit with a small heat transfer requirement on a spacecraft
Method used
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Embodiment
[0027] In this embodiment, the invention relates to a shock-absorbing support structure suitable for a single machine with a small demand for heat conduction on a spacecraft. The shock-absorbing support structure includes an upper fastening device, a shock-reducing support, a lower fastening device and connecting embedded parts ; The shock-reducing bracket provides threaded mounting holes for the single machine; the single-machine mounting feet provide through holes, and the single-machine mounting feet realize the connection between the shock-reducing bracket and the single machine through the upper fastening device; The mouth adopts an eccentric design; the connecting embedded parts are set in the honeycomb panel to provide threaded mounting holes for the impact reduction bracket. Realize the connection between the impact reduction bracket and the honeycomb panel.
[0028] Next, the present invention will be described in detail.
[0029] The shock-reducing support structure...
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The invention relates to an impact reducing support structure suitable for a single machine with a small heat conduction amount requirement on a spacecraft, and belongs to the technical field of impact reduction support structures. The impact reducing support structure comprises an upper fastening device, an impact reducing support, a lower fastening device and a connecting embedded part. The impact reducing support provides a threaded mounting hole for the single machine; a single machine mounting foot is a through hole and is connected with the single machine through a fastening screw and apressing gasket; a support interface, connected with the single machine, of the impact reducing support adopts an eccentric design; the connecting embedded part is arranged in a cellular board and provides a threaded mounting hole for the impact reducing support, and the mounting hole of the impact reducing support and the mounting hole of the cellular board are through holes and the impact reducing support and the cellular board are connected with the single machine through fastening screws and pressing gaskets. According to the impact reducing support structure, the step-by-step impact reduction mode is adopted, and the impact reduction efficiency is high; the upper support interface adopts an eccentric design, so that the bearing capacity is high; the impact reducing support is of a cylindrical hollow shell structure, and has the advantage of being low in structural weight and wide in application range.
Description
technical field [0001] The invention relates to the technical field of shock-absorbing support structures, in particular to a shock-reducing support structure suitable for a single machine 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, and the impact overload may cause damage to the structure of the single machine. In order to reduce the shock overload response of a single aircraft on a star, a shock-absorbing support structure suitable for a single aircraft with a small demand for heat conduction on a spacecraft is invented. 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....
Claims
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IPC IPC(8): B64G1/66B64G1/22
CPCB64G1/22B64G1/66
Inventor 赵鑫光王建炜张玉花张栖诚周益倩周星驰
Owner SHANGHAI SATELLITE ENG INST