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Self-adaptive porous material sweating cooling front edge structure based on pyrolysis

A porous material, sweating cooling technology, applied in the direction of fuselage insulation, power unit layout/installation, power unit air intake combustion, etc., can solve the problem of low cooling efficiency, uneven cooling, poor thermal protection effect, etc. problem, to achieve the effect of improving cooling efficiency, good fluidity, and improving thermal protection effect

Inactive Publication Date: 2021-05-07
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the deficiencies of the prior art, the present invention provides a pyrolysis-based self-adaptive porous material sweating cooling front structure, which solves the problems of uneven cooling at different parts of the front, low cooling efficiency, and thermal protection effect existing in the prior art. bad question

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  • Self-adaptive porous material sweating cooling front edge structure based on pyrolysis
  • Self-adaptive porous material sweating cooling front edge structure based on pyrolysis
  • Self-adaptive porous material sweating cooling front edge structure based on pyrolysis

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Embodiment 1

[0042]Such asFigure 1 to 6As shown, a thermally solved adaptive porous material swew cooling front structure, including the body 6, a front firmer 1 connected to the body 6, the front edge body 1 covering a thermosetting material layer 3 The cooling chamber 4 is connected in the front edge body 1, and the cooling chamber 4 is connected to a coolant supply passage 5, and a plurality of coolant passages 2 are provided on the front edge body 1, the coolant passage 2 and the The thermal solution material layer 3 is connected, and the coolant supply passage 5 is used to connect the coolant supply device.

[0043]Such asfigure 2 As shown, when the aircraft lifting is unprecedented or low-speed, the temperature of the pyrolytic carbonated material layer 3 is lower than its pyrolysis temperature, and the pyrolysis carbonated material layer 3 is closed, the coolant cannot penetrate, the pyrolysis of the carbonized material layer 3 is not There is a pore structure, at which time is passive heat ...

Embodiment 2

[0056]Such asFigure 1 to 6As shown, as further optimization of Embodiment 1, the present embodiment includes all of the technical features of Example 1. In addition, the embodiment includes the following technical features:

[0057]As a preferred technical solution, the thermal solution material layer 3 is a material structure having a thermal solution temperature lower than a safe use temperature of the front edge 1.

[0058]This avoids the safety of the temperature excessive affecting the safety use of the front firming 1 and the unfavorable case of the pyrolysis of the carbonized material layer 3, and improves the reliability of the present invention.

[0059]As a preferred technical solution, the thermal solution material layer 3 is a material structure having a pyrolysis temperature below its own ablation temperature.

[0060]This avoids the entire thermal solution layer 3 ablation, it can only heat the carbonized material when the pyrolysis is thermally solved, but retain the skeleton, th...

Embodiment 3

[0062]Such asFigure 1 to 6As shown, as further optimization of Embodiment 2, the present embodiment includes all of the technical features of Example 2, in addition to this, the embodiment includes the following technical features:

[0063]As a preferred technical solution, the front edge 1 is one or more of the head cone, a rudder edge, an intake tract, an engine wall surface, a tail fountain.

[0064]The present invention is used for one or more of the above parts of the aircraft, expanding the scope of application and application scenarios, facilitating the thermal protection of multiple parts of the aircraft.

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Abstract

The invention discloses a self-adaptive porous material sweating and cooling front edge structure based on pyrolysis, which comprises a fuselage and a front edge body connected with the fuselage, the front edge body is covered with a pyrolysis carbonization material layer, a cooling cavity is connected in the front edge body, the cooling cavity is connected with a coolant supply channel, the front edge body is provided with a plurality of coolant channels. The coolant channel is respectively communicated with the pyrolysis carbonization material layer and the cooling cavity, and the coolant supply channel is used for being connected with a coolant supply device. According to the structure, the problems of non-uniform cooling, low cooling efficiency and poor thermal protection effect of different parts of the leading edge in the prior art are solved.

Description

Technical field[0001]The present invention relates to the field of aircraft thermal protection technology, in particular to thermally solve-based adaptive porous material swew in the leading edge structure.Background technique[0002]The high ultrasound speed is moving toward the direction of Gao Mah, long-term air, and the hot protection problem is increasingly a key factor in restricting further improvement of its performance. The pneumatic heating problem of high ultrasound speed aircraft is very complicated. Its head cone, airfoil front, rudder shaft slits, interference zones, etc., due to the high-speed airflow, the harsh gas is heated, and with Mach The number of increases is increased dramatically. Therefore, it is one of the key technologies to solve high ultrasound speed aircraft problems in the development of high-efficiency and stable active thermal protection systems.[0003]At present, the ablation thermal protection currently can withstand the impact of high heat flow, but...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/40B64D33/02
CPCB64C1/40B64D33/02B64D2033/024
Inventor 沈斌贤李强刘骁葛强周述光
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT