X-type composite rocket inter-stage section or inter-box section connecting structure

Abstract

Provided is an X-type composite rocket inter-stage section or inter-box section connecting structure. The connecting structure comprises a plurality of X-type inter-stage section/inter-box section connecting pieces (1), a front storage box rear short shell (2) and a rear storage box front shot shell (3), wherein the front storage box rear short shell (2) and a front rocket body/storage box structure (5) are integrally welded to be formed, and the rear storage box/rocket body front short shell (3) and a rear rocket body/storage box structure (4) are integrally welded to be formed. The front ends and the rear ends of the eight X-type inter-stage section/inter-box section connecting pieces (1) are separately and mechanically connected with the front storage box rear short shell (2) and the rear storage box front short shell (3) through anti-shear bolts, the connecting problem of existing rocket inter-stage sections/inter-box sections and inter-box sections of deep space exploration propelling aircrafts is solved, the low heat conductivity of front and rear storage boxes of low-temperature propelling aircrafts is achieved, structure efficiency is improved further and good assembly manufacturability is achieved.

Description

technical field [0001] The invention relates to an X-type composite material rocket stage or box section connection structure, which is suitable for the connection between the launch vehicle stage or the box section and the deep space exploration aircraft propeller box section connection, belonging to the space vehicle stage Segment or inter-segment connection field. Background technique [0002] In order to meet the needs of deep space exploration in the future, it is necessary to optimize the design of the connection structure between the low-temperature propellant / oxidant tanks on the upper stage of the Type 1 vehicle. thermal insulation. Therefore, first of all, from the perspective of material selection, the traditional metal structure scheme has high thermal conductivity, which cannot meet the low thermal conductivity requirements of low-temperature propellant vehicles. Therefore, it is necessary to propose a light-weight, high-rigidity, low-thermal-conductivity comp...

AI Technical Summary

Problems solved by technology

Although the traditional wound rod system frame structure of composite materials has the characteristics of low thermal conductivity and lighter weight and higher efficiency than metal structures, it is difficult to coordinate and assemble the rod system. They are independent of each other and cannot support each other to further improve the structural rigidity. Therefore, it is necessary to propose a new composite material integrally formed inter-stage / inter-box connection structure to further improve structural efficiency.

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