Cooling system of long-endurance high-power airborne electronic equipment

By designing a cooling system with multi-layered internal and parallel coolant channels in a subsonic aircraft, the problem of low heat dissipation efficiency of high-power airborne electronic equipment with long flight time was solved, and a highly efficient heat dissipation effect was achieved.

CN122121109APending Publication Date: 2026-05-29BEIJING HUAHANG RADIO MEASUREMENT & RES INST
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Patent Information

Application Number
CN202411927692.4
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Priority Date
2024-11-29
Filing Date
2024-12-25
Publication Date
2026-05-29

AI Technical Summary

Technical Problem

Existing technologies cannot effectively solve the problem of low heat dissipation efficiency caused by high heat generation and long operating time of high-power electronic equipment in subsonic aircraft, especially when the space for airborne equipment is limited and water-cooled machines cannot be configured.

Method used

A cooling system for long-endurance, high-power airborne electronic equipment was designed. It employs heat dissipation structural components, a drive pump, and a heat storage tank. Through heat conduction and convection heat transfer, the coolant circulates between the heat dissipation structural components, the heat storage tank, and the aircraft skin, realizing the design of multi-layer internal and parallel flow channels of the coolant, thereby improving heat dissipation capacity and heat exchange efficiency.

Benefits of technology

The design of multi-layered internal coolant channels and parallel channels significantly improves heat dissipation capacity, reduces flow resistance, and enables rapid heat dissipation of electronic equipment, meeting the heat dissipation requirements of long-endurance, high-power airborne equipment.

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Abstract

The invention relates to a cooling system for long-endurance high-power airborne electronic equipment, belongs to the technical field of heat dissipation of aircraft equipment, and solves the problem of insufficient heat dissipation efficiency of high-heating-power electronic equipment of a subsonic aircraft. The cooling system comprises a heat dissipation structural part, a driving pump, a heat storage pool and an aircraft skin. The electronic equipment is in contact with the heat dissipation structural member, and the electronic equipment is cooled while the heat dissipation structural member is heated in a heat conduction mode; a cooling liquid inner flow channel used for circulation of cooling liquid is arranged in the heat dissipation structural part. The driving pump is used for driving the cooling liquid to circulate between the heat dissipation structural part and the heat storage pool; cooling liquid is stored in the heat storage pool. The cooling liquid can circulate between the heat storage pool and the aircraft skin to conduct heat to the external environment. The cooling liquid is driven to circulate among the heat dissipation structural part, the heat storage pool and the aircraft skin, heat can be transferred to the external environment, and effective and rapid heat dissipation of the electronic equipment is achieved.
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