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A kind of flexible braided soft interlayer for pulse engine and its manufacturing method

A technology for engines and interlayers, applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve problems such as stiffness and load-bearing capacity requirements, and achieve the effect of meeting pressure resistance and solving the stiffness and load-bearing capacity requirements of different positions

Active Publication Date: 2021-05-28
JIANGNAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The basic material of the present invention is heterocyclic aramid fiber and heat-insulating and corrosion-resistant rubber matrix. The column section of the interlayer of the prefabricated body and the cone section of the interlayer of the prefabricated body are respectively three-dimensionally woven and two-dimensionally knitted, and are molded with the rubber matrix to realize The preparation of the flexible braided soft interlayer of the pulse engine to meet the pressure resistance, heat insulation and load-bearing requirements of the soft interlayer of the pulse engine, and to solve the problem of stiffness and load-bearing capacity requirements at different positions of the soft interlayer

Method used

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  • A kind of flexible braided soft interlayer for pulse engine and its manufacturing method
  • A kind of flexible braided soft interlayer for pulse engine and its manufacturing method
  • A kind of flexible braided soft interlayer for pulse engine and its manufacturing method

Examples

Experimental program
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Effect test

Embodiment 1

[0043]In this example, the level length of the pulse engine soft compartment preform is 30 mm, the preform spacer cone length is 150 mm, the preform spacer section is 460 mm; the preform spacer cone is the maximum diameter of 324 mm, prefabricated The body compartment cone section minimum diameter is 103mm, the preform spacer section is 103mm; the preform compartment cone is 93.1mm horizontally projection length, the connection angle is 47.7 °; the fiber selects aramid 1414, the rubber substrate selection of three yuan ethylene ethylene ethylene The substrate content is 60%.

[0044]The specific preparation step is:

[0045](1) such asfigure 1 As shown, the structure of the soft spacer layer is shown. Fromfigure 1 It can be seen that the pulse engine soft compaction layer mainly includes a 1 partial layer segment, a 2 compartment cone section, a three part of a three part of a 4 compartment, a compartment section, and a compartment cone section. By connecting the connection; the preform s...

Embodiment 2

[0053]In this embodiment, the pulse engine soft compartment preform is 50 mm, and the preform spacer cone section is 300 mm, the preform spacer section is 800mm; the preform spacer cone hole is maximum diameter 600mm, prefabricated The body compartment is less than 220 mm, the preform spacer section is 220 mm; the preform spacer cone is 180 mm lateral projection length of 180 mm, the connection angle is 47.7 °; the fiber selects aramid 1414, the rubber substrate selection of three yuan ethylene ethylene ethylene ethylene ethylene ethylene The content is 60%.

[0054](1) a composite soft composite layer for a solid rocket multi-pulse engine, the pulse engine soft spacer, mainly including a composite level segment, a compartment cone, a partition column segment, and the compartment section, Between the partition cone sections, the preform spacer segment, the preform spacer cone section, the preform spacer level segment is aramid fiber reinforced ternium ethylene propylene compound.

[0055]...

Embodiment 3

[0062]In this embodiment, the pulse engine soft compartment preform is 50 mm, and the preform spacer cone section is 300 mm, the preform spacer section is 800mm; the preform spacer cone hole is maximum diameter 600mm, prefabricated The body isolation tapered segment minimum diameter of 220 mm, the prefabricated portion column section diameter is 220 mm; the preform compartment cone is 180 mm lateral projection length, the connection angle is 47.7 °; the fiber selects aramid 1313 fiber, the rubber substrate selector, the rubber substrate, the substrate is 60%.

[0063]The preparation method is consistent with Example 2, and the resulting pulse engine has a flexible braided soft compartment of 38 MPa, a pressure pressure time of 44S, and heat resistance temperature of 1000 ° C.

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Abstract

The invention discloses a flexible braided soft interlayer for a pulse engine and a manufacturing method, belonging to the field of functional materials. The flexible braided soft interlayer for the pulse motor of the present invention comprises three parts: the interlayer column section, the interlayer cone section, and the interlayer horizontal section, and the interlayer column section and the interlayer cone section are connected by connectors; wherein, The three parts of the interlayer column section, the interlayer cone section and the interlayer horizontal section are obtained by molding the prefabricated body interlayer column section, the prefabricated body interlayer cone section, and the prefabricated body interlayer horizontal section; the described The column section of the prefabricated body interlayer is woven with an overall variable thickness 2.5D structure, and the horizontal section of the prefabricated body interlayer and the cone section of the prefabricated body interlayer are woven by warp knitting or weft knitting. The flexible braided soft interlayer for the pulse engine of the present invention bears a pressure of more than 20 MPa, a pressure bearing time of more than 30s, and a heat-resistant temperature of more than 560°C.

Description

Technical field[0001]The present invention relates to a flexible braided soft spacer layer and a manufacturing method for pulsed engine, belonging to the field of functional materials.Background technique[0002]The multi-pin engine is a new type of solid rocket engine that can be stopped multiple times. It has high control, which can effectively reduce the speed of missile flight and aerodynamic resistance, improve the end of the missile, range, hit rate and protractive ability. Among them, the pulse isolation device is the core component of the multi-pulse solid engine, which isolates the combustion indoor propellant into a plurality of propellant units, each of which realizes the ignition combustion. The main function of the isolation device is to prevent a certain propellant unit from igniting its gas intrusion into other propellant units, thereby ensuring the independence of each propellant unit. The pulse isolation device not only requires pressure, heat insulation and bearing r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34F02K9/34
CPCB29C70/34F02K9/34
Inventor 张典堂袁琼钱坤
Owner JIANGNAN UNIV