Solid rocket cold separation interstage section suitable for automatic manufacturing

Abstract

The invention provides a solid rocket cold separation interstage section suitable for automatic manufacturing, which comprises a front butt-joint frame, a rear butt-joint frame and a separation surface, the front butt-joint frame, the rear butt-joint frame and the separation surface are all circular ring-shaped, and the separation surface is positioned between the front butt-joint frame and the rear butt-joint frame; the opposite sides of the front butt-joint frame and the rear butt-joint frame are each provided with a clamping assembly surrounding the front butt-joint frame by a circle, one end of a rib is clamped on each clamping assembly, the other end of each rib is tightly attached to the separation face, the ribs surrounding the front butt-joint frame and the rear butt-joint frame form a cylindrical framework, the outer surface of each framework is wrapped with a skin, and the outer surface of each framework is covered with a protective film. The problems that in the prior art, most small solid rocket interstage section structures are of an integral structure, the structural form is complex, and machining is inconvenient are solved.

Description

technical field [0001] The invention relates to the technical field of rocket separation, in particular to a solid rocket cold separation interstage section adapted to automatic manufacturing. Background technique [0002] After the structural design of the rocket stage section meets the load-bearing requirements, the main design goal is to reduce weight, increase rocket capacity, and reduce mass manufacturing costs. [0003] The structural design of large rockets basically adopts the design of skin reinforcement, and then the manufacture of the interstage section is completed through the assembly and connection of various parts. However, in order to reduce the weight, the thickness of each part of the skin needs to be carefully designed to meet the weight reduction requirements, and the ribs cannot all use the same piece. [0004] The interstage structure of small solid rockets mostly adopts an integral structure with complex structural forms, such as the manufacturing for...

AI Technical Summary

Problems solved by technology

[0005] Aiming at the deficiencies in the prior art, the present invention provides a solid rocket cold-separated interstage section adapted to automatic manufacturing, which solves the structure of the small solid rocket interstage section existing in the prior art, and mostly adopts integral type Structure, the problem that the structure is complex and not easy to process

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