A fixed-wing UAV air-cooled fuel cell dual-stack integrated power system

A fuel cell stack and power system technology, used in fuel cells, fuel cell additives, fuel cell heat exchange, etc., can solve the problems of low power system efficiency, poor stack heat dissipation, etc., to improve performance consistency, Improve power generation efficiency and drone endurance, and eliminate the effect of energy consumption

Active Publication Date: 2022-07-26
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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  • A fixed-wing UAV air-cooled fuel cell dual-stack integrated power system
  • A fixed-wing UAV air-cooled fuel cell dual-stack integrated power system
  • A fixed-wing UAV air-cooled fuel cell dual-stack integrated power system

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Embodiment 1

[0128] This embodiment provides a fixed-wing UAV air-cooled fuel cell dual-stack integrated power system, 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 horizontal plane located at the tail of the fuselage U0. The tail U6 and the vertical tail 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 symmetrically arranged in the middle of the fuselage U0 The stack U3, and a first heat dissipation system and a second heat dissipation system respectively corresponding to the first air-cooled fuel cell stack U2 and the second air-cooled fuel cell stack U3.

[0129] The first air-cooled fuel cell stack U2 and the second air-cooled fuel cell stack U3 both incl...

Embodiment 2

[0146] This embodiment provides a fixed-wing UAV air-cooled fuel cell dual-stack integrated power system, which is used for a fixed-wing UAV equipped with an auxiliary propeller U8 on the wing U5. When the fixed-wing UAV starts or flies, Auxiliary propeller U8 is automatically turned on; if Image 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, 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, symmetrically arranged on both sides of the wings U5 The first air-cooled fuel cell stack U2 and the second air-cooled fuel cell stack U3, and the first heat dissipation system and the third air-cooled fuel cell stack correspondi...

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Abstract

The invention provides a fixed-wing unmanned aerial vehicle air-cooled fuel cell dual-stack integrated power system, belonging to the field of fuel cells, comprising a fuselage, a power motor, a high-pressure hydrogen storage tank, a wing, two symmetrically arranged in the middle of the fuselage or The air-cooled fuel cell stack on the wing, and two heat dissipation systems corresponding to the air-cooled fuel cell stack; the air flow channel of the stack is a parallel wave-shaped flow channel; when the stack is arranged in the middle of the fuselage, the heat dissipation system It also includes a cooling fan; when the stack is set on the wing, the power system is suitable for the drone with auxiliary propellers on the wing, and the cooling system also includes the front wing shroud; when the drone starts or flies at a low speed, During medium-speed flight and high-speed flight, the reactor temperature is controlled to be within the ideal temperature range through different heat dissipation methods. The invention also proposes a consistency guarantee control scheme during the operation of the dual-stack system, which improves the stack performance consistency while ensuring the overall electric power demand.

Description

technical field [0001] The invention belongs to the field of fuel cells, and in particular relates to a fixed-wing unmanned aerial vehicle air-cooled fuel cell dual-stack integrated power system. 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 the cathode, and the electrons also reach the cathode through the external circuit at the same time. Protons, electrons and oxygen combine to form water. Fuel cells convert chemical energy into electrical energy in a non-combustion manner, and their direct power generation efficiency can be as high as 45% because they are not limited by the Carnot cycle. With the battery stack as the core power generation device, the fuel cell ...

Claims

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Application Information

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Patent Type & Authority Patents(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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