Heat insulation structure used for high-mach-number air vehicle

An aircraft and support structure technology, applied in the direction of fuselage insulation, etc., can solve the problems of low connection strength, complex assembly process, increase the weight of the aircraft, etc., to achieve the effect of improving the structural strength and simplifying the assembly process

Inactive Publication Date: 2015-10-28
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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AI Technical Summary

Problems solved by technology

The existing heat insulation structure design principle is to use the low thermal conductivity of heat insulation materials to realize the heat insulation function. Specifically, it is a method of pasting heat insulation blankets inside the heat insulation structure or pasting rigid heat insulation tiles 1 on the outside, such as figure 1 As shown, this method is to paste the heat insulation material on the metal skin 2 through adhesive, the assembly process is complicated, and the connection strength is low. More importantly, this design introduces heat insulation material, which will increase the weight of the entire aircraft

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  • Heat insulation structure used for high-mach-number air vehicle
  • Heat insulation structure used for high-mach-number air vehicle
  • Heat insulation structure used for high-mach-number air vehicle

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specific Embodiment approach

[0015] The specific implementation method is: design the heat insulation structure according to the temperature distribution and aerodynamic shape of the aircraft, and design different forms of hollow sandwich structure modules 3 with gas cooling channels for different parts, and several modules can be connected in series Or in parallel, cold air is introduced from the engine or the atmosphere to cool the insulation structure, and finally discharged into the atmosphere.

[0016] The concrete heat insulation structure is: described heat insulation structure comprises skin 4, the fuselage 5 of aircraft and support structure 6, and described support structure is supported between skin and the fuselage of aircraft, by skin, the fuselage of aircraft And the support structure forms a cooling channel, the cooling channel communicates with the cold air source, and the heat of the skin is taken away by the cold air to dissipate heat from the high Mach aircraft.

[0017] Further, the su...

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Abstract

The invention relates to a design principle of a heat insulation structure used for a high-mach-number air vehicle. When the heat insulation structure of the high-mach-number air vehicle is designed through the principle, the weight of the heat insulation structure can be reduced on the premise that the heat insulation effect is guaranteed. The principle is that heat is taken away through high-speed flowing air and discharged out of the air vehicle, and the heat insulation aim is achieved. The principle is mainly used for designing structures, requiring heat insulation parts, of the high-mach-number air vehicle.

Description

1. Technical field [0001] The invention relates to a heat insulation structure design principle for a high Mach aircraft. Using this principle to design a heat insulation structure for a high Mach aircraft can reduce the weight of the heat insulation structure on the premise of ensuring the heat insulation effect, and further realize the overall reduction of the aircraft. Heavy. It is mainly used in the structural design of high Mach aircraft that requires heat insulation. 2. Background technology [0002] For a high-Mach aircraft, when entering and exiting the atmosphere, the surface of the aircraft rubs against the air violently, which will cause the surface temperature of the aircraft to rise sharply. Taking a Mach 6 aircraft as an example, the temperature of the nose cone and the leading edge of the wing can reach up to 1600°C. In order to ensure the normal function of the internal parts of the flight, the internal temperature must be kept at a low level. Ordinary stru...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/40
Inventor 魏绍斌张学军唐思熠李能张庆茂杨家勇
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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