Active cooling system for aerospace aircraft based on magnetic fluid energy bypass

An active cooling, aerospace aircraft technology, applied in engine cooling, turbine/propulsion cooling, charging system, etc., can solve problems such as aircraft energy control, delay modal start, improve fuel efficiency, and expand work range effect

Active Publication Date: 2022-08-09
内蒙动力机械研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide an active cooling system for an aerospace aircraft based on a magnetic fluid energy bypass, so as to solve the problems of structural cooling and aircraft energy control during the flight process of an aerospace aircraft using combined power

Method used

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  • Active cooling system for aerospace aircraft based on magnetic fluid energy bypass
  • Active cooling system for aerospace aircraft based on magnetic fluid energy bypass
  • Active cooling system for aerospace aircraft based on magnetic fluid energy bypass

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Embodiment Construction

[0020] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0021] like figure 1 As shown, it is the working section of the integrated engine aircraft, including the aircraft active cooling waverider 11, the alkali metal coolant injector 12, the annular magnetic fluid power generation channel 13, the alkali metal-containing fuel injection hole 14, the electromagnetic energy control system 15, The annular electromagnetic acceleration channel 16 and the aircraft active cooling lip 17 .

[0022] The aircraft's active cooling waverider 11 is arranged on the leading edge of the aircraft. For the structure, see figure 2 , which consists of a high temperature alloy heat pipe 22 , an alkali metal alloy coolant 21 , an aircraft skin 23 and an alkali metal injection device 12 .

[0023] The alkali metal coolant injector 12 is located below the active cooling waverider 11 of the aircraft. The shape memory alloy t...

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PUM

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Abstract

The invention relates to an aerospace aircraft active cooling system based on magnetic fluid energy bypass, comprising an aircraft active cooling waverider and an aircraft active cooling lip, the aircraft active cooling waverider is arranged on the leading edge of the aircraft, and the aircraft active cooling lip is arranged on The leading edge of the ramjet air intake, the aircraft active cooling waverider and the aircraft active cooling lip respectively include the superalloy heat pipe and the aircraft skin. The superalloy heat pipe is located inside the aircraft skin. Corresponding to the determined thermal environment of the aircraft, the inner flow channel of the superalloy heat pipe leads to the liquid alkali metal coolant. The invention adopts the principle of magnetohydrodynamics, and uses the magnetohydrodynamic power generation technology to collect the total temperature in the high-speed incoming flow, which can effectively expand the working range of the ramjet engine, delay the modal start of the rocket engine, and improve the fuel efficiency of the aerospace aircraft.

Description

technical field [0001] The invention relates to a cooling system, in particular to an active cooling system for an aerospace aircraft based on a magnetic fluid energy bypass. Background technique [0002] The aerospace plane is a reusable aircraft that takes off from the ground (launch) and enters the space orbit to perform a payload launch mission and can glide and land back autonomously. Its orbiting process needs to go through a series of complex flight states such as stationary-subsonic flight-supersonic flight-hypersonic flight-extra-atmospheric flight. The power system of the aircraft needs to adopt the combined power technology of integrated ramjet and rocket engine, and transform the power system mode according to the flight altitude and flight speed. Combined power technologies that are currently researched more include Rocket Based Combined Cycle, Turbine Based Combined Cycle, and pre-cooling engines. To achieve orbital entry of the aircraft, it needs to be accel...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/04F02C7/16F02C7/141F02C3/30F02C7/22F02K1/78F28D15/02H02K44/08F02K9/60F02K9/52F02K9/97
CPCF02C7/04F02C7/16F02C7/141F02C3/305F02C7/22F02K1/78F28D15/02H02K44/08F02K9/60F02K9/52F02K9/97F28D2021/0021Y02T50/60
Inventor 王浩然尹顺华边磊付春楠沈杰
Owner 内蒙动力机械研究所
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