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Thermal protection cabin section, RTM forming method thereof and female die

A molding method and thermal protection technology, applied in the direction of weapon types, projectiles, self-propelled projectiles, etc., can solve problems such as adverse flight effects, deformation of textile rigid thermal protection cabins, etc. strong effect

Active Publication Date: 2021-02-05
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] For this new generation of heat protection cabin products, the butt joints of the butt joints of the protection cabins (the external surfaces of the opposite ends) are theoretically the same size, but due to the curing shrinkage characteristics of phenolic resin, textile rigid heat protection There are different degrees of deformation after the cabin section is formed
After assembly, in the direction of flight, if the external dimension of the rear end of the textile rigid heat protection cabin located at the front side is smaller than the front end of the rear textile rigid heat protection cabin (the shrinkage of the rear end of the front thermal protection cabin If the shrinkage of the front end of the thermal protection compartment on the rear side is large), then there will be a reverse air flow gradient at the junction of the two, and the reverse air flow gradient will have an adverse effect on the flight of supersonic and hypersonic cruise missiles

Method used

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  • Thermal protection cabin section, RTM forming method thereof and female die
  • Thermal protection cabin section, RTM forming method thereof and female die
  • Thermal protection cabin section, RTM forming method thereof and female die

Examples

Experimental program
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Effect test

Embodiment 1

[0041] see Figure 1-Figure 3 As shown, the female mold 1 of the heat protection cabin forming mold provided by the embodiment of the present invention is provided with a pre-occupied part 2 at the front end of the molding cavity of the female mold 2, and the pre-occupied part 2 includes a multi-layer single-sided adhesive strip Mold cloth, for example, two layers, three layers, four layers, five layers, six layers, seven layers, eight layers, nine layers, etc. The front end of each layer of single-sided adhesive release cloth is aligned with the front end of the cavity, and each layer The rear end of the single-sided adhesive release cloth has different extension dimensions in the axial direction of the cavity, and increases layer by layer from the inner layer to the outer layer.

[0042]When in use, put the fiber prefabricated body on the male mold, then put the female mold on the fiber prefabricated body, and complete the assembly of other parts of the forming mold. charac...

Embodiment 2

[0053] The RTM forming method of the heat protection compartment provided in the second embodiment includes a mold loading step, a glue injection step and a curing step. Before the assembly step, the front end of the molding cavity of the female mold is pre-occupied. Include the following steps:

[0054] According to the radial and axial dimensions of the pre-occupied space in the molding cavity, prepare a corresponding number and size of single-sided adhesive release cloth. The axial dimensions of each layer of single-sided adhesive release cloth in the molding cavity are different.

[0055] Lay multiple pieces of single-sided adhesive release cloth layered on the front end of the molding cavity of the female mold. When layering the single-sided adhesive release cloth, according to its size in the axial direction of the molding cavity, the From small to large, the molding cavity of the female mold is applied sequentially. After the application is completed, the single-sided a...

Embodiment 3

[0068] see Figure 4 and Figure 5 As shown, the heat protection compartment 3 provided in the third embodiment can be made by any molding method in the second embodiment, and the heat protection compartment 3 includes a conical cylindrical fiber preform and a resin compounded with the fiber preform Material. Preferably, the fiber preform is a multi-layer composite structure composed of fiber braids, and the composite method may be any one of needle punching method, laminated stitching method, and fine weaving puncture method. More preferably, the fiber braid can be made of quartz fiber woven fabric or glass fiber woven fabric.

[0069] see Figure 4 and Figure 5 As shown in the figure, the dotted line in the figure is the theoretical position of the front end exterior surface.

[0070] To sum up, the present invention pre-occupies the front end of the female mold through the above-mentioned molding method, and utilizes the compressibility of the fiber material to obtain...

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Abstract

The invention relates to the technical field of grease-based thermal protection material forming, in particular to a thermal protection cabin section, an RTM forming method thereof and a female die. The RTM forming method is characterized in that before a die filling step, pre-occupying is carried out on the front end of a forming cavity of the female die to obtain the thermal protection cabin section, the external dimension of the front end of the thermal protection cabin section is smaller than that of the rear end of a thermal protection cabin section to be butted on the front side, smoothtransition from the front end to the rear end is achieved through reduced dimension of the pre-occupied space, after butt-joint installation, reverse airflow jump at the butt-joint position of the twothermal protection cabin sections can be effectively avoided, the process is simple, the cost is low, implementation of an existing forming method is not affected, application and popularization arefacilitated, the size of the pre-occupied space can be conveniently adjusted according to needs, and the universality is high; and the female die is simple in structure, and can be obtained by modifying an existing female die, use and matching of other parts in the forming die are not affected, the cost can be effectively reduced, the size of the pre-occupied space can be conveniently adjusted according to needs, and the universality is high.

Description

technical field [0001] The invention relates to the technical field of forming fat-based thermal protection materials, in particular to a thermal protection compartment, an RTM forming method thereof, and a female mold. Background technique [0002] The thermal protection technology of supersonic and hypersonic cruise missiles is a key technology to ensure that the spacecraft will not overheat and burn out in the external heating environment of the ascent and reentry stages, and it is also a key technology to ensure the normal work and safety of the missile in the aerodynamic heating environment. A key technology to ensure the normal operation of rocket engines in severe internal heating environments. The purpose of thermal protection is to design the absorption or dissipation of aerodynamic heating, and the key technology to realize thermal protection is the selection of various heat-resistant structures and materials. [0003] According to the rigidity and flexibility of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/48B29C70/54B29C33/30B29C33/68F42B15/00F42B15/34
CPCB29C70/48B29C70/54B29C33/308B29C33/68F42B15/00F42B15/34
Inventor 韩蕾袁一博裴雨辰王国勇卢山
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH