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Cutting and separating device of fiber-reinforced composite material structure

A composite material and fiber-reinforced technology, which is applied to the docking device of space navigation vehicle, transportation and packaging, and space navigation equipment, etc. Design simple effects

Active Publication Date: 2017-08-11
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Application Information

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Problems solved by technology

[0005] The problem solved by the technology of the present invention is: solve the problem that additional metal separation ring shell segments are added as the connection and separation structure between stages in the main load-bearing structure of the composite material of the existing space vehicle, and it is difficult to realize weight reduction and simplify the design, thereby To achieve comprehensive lightweight

Method used

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  • Cutting and separating device of fiber-reinforced composite material structure

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Embodiment Construction

[0021] The present invention will be described in detail below in conjunction with the accompanying drawings and examples.

[0022] A cutting and separating device for a fiber-reinforced composite material structure, comprising a composite material plate 1; a gathering energy cutting cable 2; a buffer sheath 3; a protective cover 4; The bottom edge of the sheath 3 has a groove, the size of the groove matches the back size of the energy-concentrating cutting cable 2; the main part of the protective cover 4 is covered on the outer surface of the buffer sheath 3, and the mounting surface extending from one side is connected with the The cutting and separating part of the composite material plate 1 is fixed by the connecting bolt Ⅰ6; the working principle: the energy-concentrating cutting cable 2 is detonated to generate energy-concentrating jet and high-temperature and high-pressure gas, and the composite material plate 1 (ring) is cut and separated at the preset groove , to achi...

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Abstract

A cutting and separating device of a fiber-reinforced composite material structure comprises a composite material plate (1), an energy-gathered cutting cable (2), a buffer sheath (3) and a protective cover (4). The energy-gathered cutting cable (2) is mounted on one side of a separating face of the composite material plate (1), a groove is formed in the bottom edge of the buffer sheath (3), and the size of the groove is matched with the back size of the energy-gathered cutting cable (2). The outer surface of the buffer sheath (3) is sleeved with a main body part of the protective cover (4), and the main body part of the protective cover (4) and a cutting and separating part of the composite material plate (1) are fixed through an extending mounting face on one side. Energy-gathered jet flows generated by the energy-gathered cutting cable (2) cut off the composite material plate (1), and separating is completed.

Description

technical field [0001] The invention belongs to the structural technical field of launch vehicle stages, star-rocket separation and payload release, and in particular relates to a device capable of realizing effective connection and unlocking between two structural parts. Background technique [0002] In order to improve the carrying capacity of aerospace vehicles, foreign countries have long applied lightweight composite material structures in the main load-bearing structure of aircraft, so as to realize the lightweight of spacecraft structures, effectively improve the load ratio of aerospace vehicles, and reduce launch costs. The application of lightweight composite materials meets the requirements of aerospace structural integrity and lightweight, but for multi-stage aerospace vehicles, it is faced with the problem of how to cut and separate the inter-stage structures with lightweight composite materials as the main load-bearing structure. [0003] Preliminary research re...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/641
Inventor 孙璟张志峰石玉红吴晗玲曾雅琴张希王帅田建东卢红立宋保永唐科张晓晖王江路志峰苏晗胡振兴
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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