Joint heat radiation device for solar cell panel and propeller motor of high-altitude air vehicle

Abstract

The invention designs a device for the joint heat radiation of a solar cell panel and a propeller rear motor of a high-altitude air vehicle by utilizing a tail low-temperature high-speed airflow of a propeller of the air vehicle. According to the device, the heat exchange efficiency of a system can be improved by using a measure similar to forced convection heat radiation; the solar cell panel is enabled to meet a temperature needed by work; meanwhile, the heat radiation is also carried out through a fin to decrease the temperature of a centralized heat source propeller motor. In a sun irradiation condition, the temperature of the upper surface of the solar cell panel can reach 100 DEG C or above; the heat radiation efficiency is greatly reduced by low-density air at a 30,000-meter high altitude; therefore, in the severe working condition, the heat radiation design of a cell panel becomes very important. Through the way of carrying out convection heat radiation by using a wake flow of the propeller, the structural weight of a forced convection heat radiation fan can be omitted. Meanwhile, the inlet air drainage of the tail airflow of the propeller is carried out through a structure similar to an engine nacelle; the aerodynamic performance of the propeller can be also promoted to a certain extent; two things are achieved at one stroke.

Description

technical field [0001] The invention relates to a forced convection heat dissipation and thermoelectric power generation device for solar panels of high-altitude aircraft. Its purpose is to design a device suitable for the working height of 3 Heat dissipation device for solar panels of high-altitude aircraft with a single continuous flight time of more than 48 hours. At the same time, in order to reduce the structural weight of the heat sink as much as possible and simplify the composition of the heat sink as much as possible, a method of directly using the airflow at the tail of the propeller to dissipate heat is adopted. Specifically, it involves the determination of the geometric dimensions of the model, the determination of the shape and size of the bleed air structure, the design and arrangement of cooling channels, and other issues. Background technique [0002] With the development of science and technology and the introduction of the concept of information warfare, ...

AI Technical Summary

Problems solved by technology

This arrangement can solve the problem that the airflow behind the propeller is not easy to enter due to the vortex, and also improves the aerodynamic efficiency of the propeller in another aspect.

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