Surface structure and hypersonic aircraft attached with same
A technology of hypersonic speed and surface structure, which is applied in the direction of aircraft, supersonic aircraft, and the direction of affecting the air flow passing through the surface of the aircraft, which can solve the problems of heat protection, heat reduction and drag reduction, and improve the heat resistance , to achieve the effect of delayed transition
Active Publication Date: 2022-05-13
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
[0005] The main purpose of the present invention is to provide a surface structure and a hypersonic aircraft attached to the surface structure, aiming to solve the technical problems of the current hypersonic aircraft surface structure with poor heat protection, heat reduction and drag reduction effects
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[0029] It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.
[0030] The embodiment of the present invention provides a surface structure, referring to figure 1 , figure 1 It is a structural schematic diagram of the first embodiment of the surface structure of the present invention.
[0031] In this embodiment, the surface structure includes a substrate 100 and an ablative material 300 . Wherein, the substrate 100 includes a first surface and a second surface oppositely arranged, the first surface is attached to the surface of the hypersonic vehicle, the second surface is provided with a microcavity 200, the microcavity 200 is filled with an ablation material 300, and the ablation material 300 The heat generated by the second mode wave in the microcavity 200 is absorbed during ablation.
[0032] It is easy to understand that, in this field, for a hypersonic boundary layer, th...
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The invention discloses a surface structure and a hypersonic flight vehicle attached with the surface structure, the surface structure comprises a substrate and an ablative material, one surface of the substrate is attached to the hypersonic flight vehicle, and the other surface of the substrate is provided with a microcavity filled with the ablative material. The microcavities used for being filled with the ablative material are formed in the substrate, and the protruding parts used for generating the reflected waves of the second modal waves and low-speed backflow are arranged on the portion, between every two adjacent microcavities, of the substrate table, so that incident waves of the second modal waves generated when the hypersonic flight vehicle flies at the hypersonic speed are counteracted; and meanwhile, energy generated by the second modal wave is conducted, and heat generated by the second modal wave is absorbed when the ablative material is ablated, so that delayed transition of the surface structure of the hypersonic aircraft can be realized, and the heat protection, heat reduction and resistance reduction capabilities of the hypersonic aircraft are improved.
Description
technical field [0001] The invention relates to the field of hypersonic aircraft, in particular to a surface structure and a hypersonic aircraft attached with the surface structure. Background technique [0002] When a hypersonic vehicle is flying at high speed, for the hypersonic boundary layer, the occurrence of transition will cause the wall friction coefficient and heat transfer coefficient of the turbulent boundary layer to increase sharply, and then propose a higher requirements. [0003] Studies have shown that the weight of the thermal protection system of full laminar flow and full turbulent flow can be about 4 times different, the total resistance of full laminar flow will be about 30% lower than that of full turbulent flow, and the payload is twice that of full turbulent flow. It can be seen that the precise control of the boundary layer transition is of great significance to the heat protection, heat reduction and drag reduction of hypersonic vehicles. Therefor...
Claims
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IPC IPC(8): B64C21/10B64C30/00
CPCB64C21/10B64C30/00
Inventor 李晓虎涂国华刘勇陈坚强袁先旭郭启龙黄文锋
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT