Flow control type impact transpiration cooling nose cone

A sweat cooling and nose cone technology, applied in the field of hypersonic aircraft structure, can solve the problem of insufficient sweat cooling capacity, etc., and achieve the effects of preventing heat transfer deterioration, increasing temperature gradient, and increasing flow resistance

Active Publication Date: 2019-02-15
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem of the present invention is: to overcome the deficiencies of the prior art, a flow-controlling impact sweating cooling head cone is proposed, which solves the problem of insufficient sweating and cooling capacity of the cone head of the sweating head cone in the prior art, The invention improves the utilization rate of the coolant and reduces the amount of the coolant

Method used

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  • Flow control type impact transpiration cooling nose cone
  • Flow control type impact transpiration cooling nose cone
  • Flow control type impact transpiration cooling nose cone

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Embodiment Construction

[0028] The present invention utilizes the principle of perspiration seepage cooling and impingement cooling to design a nose cone structure combining impact sweat cooling. Through this technical means, the coolant is first supplied to the highest part of the thermal environment at the front end of the nose cone, and at the same time, two methods of sweating cooling and impact cooling are used to ensure the cooling demand of the highest part of the thermal environment. And by adjusting the flow channel structure of the flow control cone core, the supply of coolant to each part of the sweating head cone can be precisely controlled, so that more coolant is supplied to the higher thermal environment of the front end of the nose cone, and the lower thermal environment of the rear end of the nose cone is cooled. Dosage supply is low. Under the premise of keeping the surface temperature of the tip lower than the ablation temperature of the outer layer material, the utilization rate o...

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Abstract

A flow control type impact transpiration cooling nose cone comprises a porous nose cone and a flow control cone core; the porous nose cone is a circular cone; a conical blind hole is formed in the bigend of the porous nose cone; the flow control cone core is a circular cone; the flow control cone core is inserted into the conical blind hole of the porous nose cone; a cavity is formed between thehead of the flow control cone core and the bottom of the conical blind hole of the porous nose cone; a through hole is formed in the flow control cone core in the axis direction and used for enablinga coolant to flow into the through hole from the big end of the circular cone of the flow control cone core and flow out of the through hole from the small end; and the big end of the flow control cone core is connected with an aircraft downstream cabin section. According to the flow control type impact transpiration cooling nose cone, by using a transpiration cooling and impact cooling principle,the temperature of the nose cone part of an aircraft is reduced so that ablation deformation cannot be generated; and requirements on long-time, long-distance and repeated use of the aircraft are satisfied.

Description

technical field [0001] The invention relates to a flow-controlling impact sweating cooling nose cone, which belongs to the technical field of hypersonic aircraft structures. Background technique [0002] When the aircraft flies at hypersonic speed in the atmosphere, aerodynamic heating occurs, which makes the surface of the aircraft generate high temperature. The nose cone, wings, rudder leading edge and other parts of the aircraft are the most severely aerodynamically heated parts of the hypersonic vehicle. When the flight speed is higher than Mach 10, the stagnation point heat flow at the end can reach 10-20MW / m 2 , The stagnation point temperature of the nose cone of the aircraft can reach above 3000°C. [0003] In order to overcome the impact of the high temperature environment on the aircraft, the high heat parts such as the nose cone of the aircraft are usually made of ablation-resistant materials. Ablation-resistant carbon-based materials, with low ablation rate and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C30/00B64C1/00
CPCB64C30/00
Inventor 高翔宇焦子涵尘军王振峰马鸣陈伟华高扬
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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