Large and medium-sized multilayer space experimental device with high effective load mass ratio and mounting method

Abstract

The invention belongs to the technical field of structural design of space experiment devices, and discloses a multilayer space experiment device with a high effective load mass ratio and a mounting method, aiming at solving the technical problems in the existing space science load design, a front vertical plate and a bottom plate are connected into an L-shaped structure through the bottom; a lower frame, a middle layer plate, and an upper frame are connected into a whole from bottom to top; the lower frame is connected with the bottom plate, the front end of the upper frame is connected withthe inner side of the front vertical plate, the bottom of a front ventilation structure is installed at the front end of the bottom plate, the upper portion of the front ventilation structure is connected with the outer side of the front vertical plate, and a notch-shaped skin is connected with the front vertical plate, the upper portion of the bottom plate, the lower frame and the upper frame ina surrounding mode. The upper cover plate is connected with the notch-shaped skin, the front vertical plate and the upper frame from the upper portion. Diversified functions and structural integrationand compact design are achieved, and the multilayer space experiment device is high in load structural mass ratio, compact in modular partition, convenient to assemble and debug, reliable in strength, rapid in iteration and low in cost.

Description

technical field [0001] The invention belongs to the technical field of structural design of space experiment devices, and in particular relates to a large and medium-sized multi-layer space experiment device with high payload mass ratio and an installation method. Background technique [0002] The vigorous development of space activities will inevitably give rise to a large number of opportunities for space science / technology experiments, followed by the development of a large number of space science payloads. The current national space experiment requirements are becoming more and more engineering-oriented, and the requirements for power consumption, machinery, etc. The margin is getting smaller and smaller, and the development cycle is getting shorter and shorter. Under the mission requirements of high safety, high reliability, and rapid iteration, it is necessary to carry out modular design. By decomposing the aerospace load into several independent functional modules, eac...

AI Technical Summary

Problems solved by technology

At present, the typical spacecraft structures used in my country include shell structures, plate structures, frame structures, bracket structures, connection structures and deployable structures, which have been relatively mature in spacecraft applications, and in aerospace loads, especially scientific loads In the structural design of the rocket, due to the single design, it mainly adopts the form of splicing the external thick plates after digging the ribs, and the internal partial brackets. Moreover, the integration of internal loads is relatively poor, and it is not easy to maintain uniform deformation of the structure, resulting in an increase in relative error; in addition, the non-modular design is a luxury for multiple research units to debug separately; finally, some structures are directly installed outside. On the board, the space openness is not enough when debugging, and the operating space is small, which is not conducive to local modification and correction

[0005] In the development of existing space scientific payloads, there is basically no precedent that takes into account both technology and economy. Therefore, if the structure developed for scientific payloads is compact in structure, high in load-to-structure-mass ratio, modular in partition, easy to debug, reliable in strength, and The beneficial exploration of rapid and low-cost structural design and installation has important practical significance in the design of future space science load structures

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