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Air-cooled fuel cell double-stack integrated power system of fixed-wing unmanned aerial vehicle

A fixed-wing unmanned aerial vehicle air cooling and fuel cell stack technology, which is applied in the directions of fuel cells, fuel cell additives, fuel cell heat exchange, etc., can solve the problems of low power system efficiency and poor stack heat dissipation, etc. Consistent performance, improving power generation efficiency and drone endurance, and enhancing the effect of convection heat dissipation

Active Publication Date: 2021-07-30
UNIV OF ELECTRONICS SCI & TECH OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Aiming at the problems of poor stack heat dissipation and low efficiency of the power system in the above-mentioned prior art, the present invention proposes an air-cooled fuel cell double-stack integrated power system for fixed-wing unmanned aerial vehicles, which ensures the weight balance of the unmanned aerial vehicle and at the same time Improve the performance consistency of the stack, and improve the power generation efficiency of the fuel cell system and the endurance of the drone

Method used

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  • Air-cooled fuel cell double-stack integrated power system of fixed-wing unmanned aerial vehicle
  • Air-cooled fuel cell double-stack integrated power system of fixed-wing unmanned aerial vehicle
  • Air-cooled fuel cell double-stack integrated power system of fixed-wing unmanned aerial vehicle

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Embodiment 1

[0128] This embodiment provides an air-cooled fuel cell double-stack integrated power system for a fixed-wing unmanned aerial vehicle, such as image 3 As shown, it includes the fuselage U0, the power motor U1 located at the front of the fuselage U0, the high-pressure hydrogen storage tank U4 located at the rear of the fuselage U0, the wings U5 located on both sides of the fuselage U0, and the level at the tail of the fuselage U0. Empennage U6 and vertical empennage U7, the task load U100 located between the power motor U1 and the air-cooled fuel cell stack, the first air-cooled fuel cell stack U2 and the second air-cooled fuel cell arranged symmetrically side by side in the middle of the fuselage U0 The stack U3, and the first heat dissipation system and the second heat dissipation system corresponding to the first air-cooled fuel cell stack U2 and the second air-cooled fuel cell stack U3 respectively.

[0129] The first air-cooled fuel cell stack U2 and the second air-cooled...

Embodiment 2

[0146] This embodiment provides an air-cooled fuel cell double-stack integrated power system for a fixed-wing unmanned aerial vehicle, which is used for a fixed-wing unmanned aerial vehicle equipped with an auxiliary propeller U8 on the wing U5. When the fixed-wing unmanned aerial vehicle starts or flies, Auxiliary propeller U8 is automatically turned on; if Figure 6 As shown, the power system includes a fuselage U0, a power motor U1 located at the front of the fuselage U0, a high-pressure hydrogen storage tank U4 located at the rear of the fuselage U0, wings U5 located on both sides of the fuselage U0, and a The auxiliary propeller U8 on U5, the horizontal stabilizer U6 and vertical stabilizer U7 located at the tail of the fuselage U0, the task load U100 located between the power motor U1 and the air-cooled fuel cell stack, and the U5 placed symmetrically side by side on both sides The first air-cooled fuel cell stack U2 and the second air-cooled fuel cell stack U3, and the ...

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Abstract

The invention provides a fixed-wing unmanned aerial vehicle air cooling type fuel cell double-stack integrated power system, and belongs to the field of fuel cells. The system comprises a fuselage, a power motor, a high-pressure hydrogen storage tank, wings, two air cooling type fuel cell stacks symmetrically arranged in the middle of the fuselage or on the wings, and two heat dissipation systems corresponding to the air cooling type fuel cell stacks; an air flow channel of the electric pile is a parallel wave-shaped flow channel; when the galvanic pile is arranged in the middle of the machine body, the cooling system further comprises a cooling fan; when the galvanic pile is arranged on the wings, the power system is suitable for the unmanned aerial vehicle with auxiliary propellers on the wings, and the heat dissipation system further comprises a wing front air guide cover; when the unmanned aerial vehicle is started or flies at a low speed, a medium speed and a high speed, the reaction temperature of the galvanic pile is controlled to be in an ideal temperature interval through different heat dissipation modes. The invention further provides a consistency guarantee control scheme during operation of the double-stack system, and the performance consistency of the stack is improved while the total electric power requirement is guaranteed.

Description

technical field [0001] The invention belongs to the field of fuel cells, and in particular relates to an air-cooled double-stack integrated power system of a fixed-wing unmanned aerial vehicle. Background technique [0002] A fuel cell is an environmentally friendly, high-efficiency, long-life power generation device. Taking the proton exchange membrane fuel cell (PEMFC) as an example, the fuel gas enters from the anode side, the hydrogen atoms lose electrons at the anode and become protons, the protons pass through the proton exchange membrane to reach the cathode, and the electrons also reach the cathode through the external circuit, the cathode at the cathode Protons, electrons and oxygen combine to form water. The fuel cell converts chemical energy into electrical energy in a non-combustion manner, and its direct power generation efficiency can be as high as 45% because it is not limited by the Carnot cycle. With the battery stack as the core power generation device, t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01M8/0263H01M8/0267H01M8/04014H01M8/2457B64D27/24B64D33/10
CPCH01M8/0263H01M8/0267H01M8/04014H01M8/2457B64D27/24B64D33/10B64U10/25B64U50/19B64U30/10Y02T50/60
Inventor 殷聪汤浩曹继申王仁康宋亚婷
Owner UNIV OF ELECTRONICS SCI & TECH OF CHINA
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