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Novel inorganic thermal protection structure and manufacturing method thereof

A thermal protection structure and manufacturing method technology, applied in the direction of chemical instruments and methods, fuselage insulation, lamination, etc., can solve the problems affecting the normal operation of the equipment in the cabin that affect the structural strength of the projectile, and achieve a simple and fast molding method with average density Low, strengthen the effect of heat insulation effect

Inactive Publication Date: 2010-02-17
国营江北机械厂
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The object of the present invention is to provide a novel inorganic thermal protection structure for a hypersonic maneuvering aircraft and a manufacturing method thereof, so as to solve the problem that during the high-speed cruising process of the aircraft, aerodynamic heating makes the temperature in the aircraft cabin close to the surface temperature of the skin, which affects the structural strength and Problems with the normal operation of the instruments in the cabin

Method used

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  • Novel inorganic thermal protection structure and manufacturing method thereof
  • Novel inorganic thermal protection structure and manufacturing method thereof
  • Novel inorganic thermal protection structure and manufacturing method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] Embodiment 1: A new inorganic thermal protection structure cabin heat protection test piece, the steps are:

[0039] 1. Production of heat-proof layer:

[0040] a) Prepare silicon nitride powder.

[0041] b) Compression: The powder is compressed and formed with a mold.

[0042] c) Isostatic pressing: performing isostatic pressing on the billet, performing isostatic pressing on the billet, and controlling the pressure to 150MPa±10MPa.

[0043] d) Sintering: Carry out sintering molding according to the sintering temperature of 1800°C±30°C.

[0044] e) Grinding: Grinding to size, the thickness of the silicon nitride heat-resistant layer is 4mm.

[0045] 2. Production of insulation layer:

[0046] a) Aluminum alloy substrate treatment: cleaning with acetone, roughening by sandblasting.

[0047] b) Glue coating: coat a thin layer of silicone rubber adhesive on the surface of the treated aluminum alloy.

[0048] c) winding forming:

[0049] According to Al 2 o 3 , SiO ...

Embodiment 2

[0061] Example 2 The cabin heat protection test piece 2, the thickness of the heat protection layer is 2 mm, and the thickness of the heat insulation layer is 42 mm. The steps are:

[0062] 1. Production of heat-proof layer

[0063] a) Prepare silicon nitride powder.

[0064] b) Compression: The powder is compressed and formed with a mold.

[0065] c) Isostatic pressing. The blank is subjected to isostatic pressing, and the pressure is controlled at 150MPa±10MPa.

[0066] d) Sintering: Carry out sintering molding according to the sintering temperature of 1800°C±30°C.

[0067] e) Grinding: According to the size of the aluminum alloy substrate, the grinding process is carried out to the required size.

[0068] 2. Production of heat insulation layer

[0069] a) Surface treatment of aluminum alloy compartment: cleaning with acetone, roughening by sandblasting.

[0070] b) Glue application: coat a thin layer of silicone rubber adhesive on the surface of the treated aluminum a...

Embodiment 3

[0083] Example 3: Experiments were carried out with different thicknesses, different spacings and different winding parameters. The thickness of the inner circumferential winding layer was 1-4mm; the thickness of the middle spiral winding layer was 20-35mm; the thickness of the outer circumferential winding layer was 5-20mm; the middle spiral winding The layer helix angle is about 70°~85°, and the casing spacing is 1~4mm. details as following:

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Abstract

The invention discloses a novel inorganic thermal protection structure and a manufacturing method thereof. The novel inorganic thermal protection structure comprises an aluminum alloy basal body, a heat insulation layer and a heat-protection layer, wherein the heat insulation layer is a space reticular structure with a plurality of staggered hole gaps, the staggered hole gaps comprise a hollow sleeve pipe braided by a plurality of layers of quartz fibre wound on the aluminum alloy basal body, and the heat-protection layer is a model body which is formed by pressing a silicon nitride powder body and is matched with the heat insulation layer. The internal diameter of the quartz fibre sleeve pipe is 0.5-1.0 mm. The quartz fibre sleeve pipe is wound by a wet method, and the distance of the sleeve pipe is 1-4 mm; the quartz fibre sleeve pipe comprises the following parameters from the inside to the outside: the internal ring direction winding layer thickness H 1 is 1-4 mm, the spiral winding layer thickness H2 is 20-35 mm, and the external ring direction winding layer thickness H3 is 5-20 mm; the winding parameter of the spiral winding layer thickness is 75-85 degrees, and the winding direction between layers is formed by opposite superposition. The thickness of the silicon nitride heat-protection layer is 2-4 mm.

Description

technical field [0001] The invention relates to a novel inorganic thermal protection structure and a manufacturing method thereof, belonging to the technical field of composite ceramic materials, and in particular to a surface thermal protection structure of a hypersonic aircraft. Background technique [0002] Since hypersonic maneuvering aircraft need to fly at hypersonic speed in the atmosphere for a long time, the thermal protection technology of the aircraft will be a major key technology that must be solved. It is very different from traditional thermal protection technology. During the flight, aerodynamic heating will make the temperature in the aircraft cabin close to the surface temperature of the skin, affecting the structural strength and the normal operation of the instruments in the cabin. The leading edge of the sharpened wing (rudder) needs to withstand the high temperature of aerodynamic heat of several thousand degrees. Materials can no longer meet the needs ...

Claims

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Application Information

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IPC IPC(8): B64C1/40B32B1/08B32B3/24B32B9/04B32B15/14B32B37/12B32B7/08C04B35/584C04B35/66
Inventor 胡良元佘平江冯昌文魏小平
Owner 国营江北机械厂
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