A flow control type impact sweating cooling head cone

A sweat cooling and nose cone technology, which is applied in the field of hypersonic aircraft structure, can solve the problems of insufficient sweat cooling capacity, etc., to prevent the deterioration of heat transfer, reduce the internal temperature, and improve the utilization rate
CN109334974BActive Publication Date: 2020-09-18BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
Publication Date
2020-09-18

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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.
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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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