CN-122025699-A - Auxiliary power heat dissipation system of airborne fuel cell, aircraft and control method

Abstract

The invention relates to the technical field of airborne auxiliary heat dissipation, in particular to an airborne fuel cell auxiliary power heat dissipation system, an aircraft and a control method. An airborne fuel cell auxiliary power heat dissipation system comprises a fuel cell assembly and a heat dissipation assembly. The fuel cell assembly comprises a fuel cell unit, a cell air inlet pipeline, a cell air outlet pipeline and an injection mixing cavity, wherein the cell air inlet pipeline is connected with an air inlet of the fuel cell unit, the cell air outlet pipeline is connected with an air outlet of the fuel cell unit, the cell air outlet pipeline is connected with the injection mixing cavity, the heat dissipation assembly comprises a radiator, a cooling liquid pipeline, a heat dissipation air inlet channel and a heat dissipation air outlet channel, the radiator is connected with the fuel cell unit through the cooling liquid pipeline, and the heat dissipation air inlet channel is communicated with an air inlet end of the radiator, so that the problem that the energy efficiency of the airborne heat dissipation assembly needs to be further improved is solved.

Inventors

• LI XIAOYANG
• PAN JUN
• WANG XIAOPING
• YAO YEMING
• Xuan tao
• XU ZHICHENG
• TAN JINGQI

Assignees

• 中国航空工业集团公司金城南京机电液压工程研究中心

Dates

Publication Date

20260512

Application Date

20260415

Claims (16)

1. 1. An auxiliary power heat dissipation system of an airborne fuel cell is characterized in that, the auxiliary power heat dissipation system of the airborne fuel cell comprises: the fuel cell assembly comprises a fuel cell unit, a cell air inlet pipeline, a cell air exhaust pipeline and an injection mixing cavity, wherein the cell air inlet pipeline is connected with an air inlet of the fuel cell unit, the cell air exhaust pipeline is connected with an air outlet of the fuel cell unit, the cell air exhaust pipeline is connected with the injection mixing cavity, the channel section of the cell air exhaust pipeline is gradually reduced along the direction from the fuel cell unit to the injection mixing cavity, the cell air inlet pipeline is communicated with the external environment of the aircraft, the opening of the cell air inlet pipeline communicated with the external environment faces the same direction as the head of the aircraft, the injection mixing cavity is communicated with the external environment of the aircraft, and the opening of the injection mixing cavity communicated with the external environment faces the tail of the aircraft; The heat dissipation assembly comprises a heat radiator, a cooling liquid pipeline, a heat dissipation air inlet channel and a heat dissipation air outlet channel, wherein the heat radiator is connected with the fuel cell unit through the cooling liquid pipeline, the heat dissipation air inlet channel is communicated with an air inlet end of the heat radiator, the heat dissipation air outlet channel is connected with an air outlet end of the heat radiator, the heat dissipation air inlet channel is communicated with the external environment of the aircraft, the opening of the heat dissipation air inlet channel communicated with the external environment faces towards the same direction as the head of the aircraft, and the heat dissipation air outlet channel is communicated with the injection mixing cavity.
2. 2. The auxiliary power radiating system of an airborne fuel cell according to claim 1, wherein the fuel cell assembly further comprises an exhaust regulating door, the exhaust regulating door is movably connected with the battery exhaust pipeline, the exhaust regulating door is located at one end of the battery exhaust pipeline close to the injection mixing cavity, and the exhaust regulating door is movable to regulate the outlet size of the battery exhaust pipeline.
3. 3. An airborne fuel cell auxiliary power heat dissipation system as defined in claim 1 wherein the opening size of said heat dissipation exhaust channel increases gradually in the direction from said heat sink to said ejector mixing chamber.
4. 4. The auxiliary power radiating system of the airborne fuel cell according to claim 1, wherein the radiating assembly further comprises a radiating adjusting door movably connected with the radiating air inlet channel, the radiating adjusting door divides an air inlet end of the radiator into a shielding area and a ventilation area, the radiating air inlet channel is communicated with the radiator through the ventilation area, the shielding area is mutually isolated from the radiating air inlet channel, and the radiating adjusting door can adjust the size proportion of the shielding area to the ventilation area.
5. 5. The auxiliary power radiating system of an airborne fuel cell according to claim 4, wherein the radiating assembly further comprises an air inlet regulating door, the air inlet regulating door is movably connected with the radiating air inlet channel, the air inlet regulating door and the radiating air inlet regulating door are distributed at intervals along the extending direction of the radiating air inlet channel, the distance from the air inlet regulating door to the radiator is larger than the distance from the radiating air regulating door to the radiator, and the air inlet regulating door is movable to regulate the size of an air inlet opening of the radiating air inlet channel.
6. 6. The auxiliary power radiating system of an airborne fuel cell according to claim 1, wherein the radiating component further comprises a fan unit, the fan unit is located in the radiating exhaust channel, the fan unit comprises a radiating fan, a stamping valve and a supporting frame, the supporting frame is connected with the radiating exhaust channel, the radiating fan is connected with the supporting frame, an air inlet end of the radiating fan faces the radiator, the stamping valve is movably connected with the supporting frame, the supporting frame separates the radiating exhaust channel into a stamping flow channel and a radiating flow channel, and when the air pressure in the stamping flow channel is larger than the air pressure in the radiating flow channel, the stamping valve is movable to communicate the stamping flow channel with the radiating flow channel.
7. 7. The auxiliary power radiating system of claim 6 wherein the axis of said radiator fan is parallel to and spaced from the axis of said heat dissipating exhaust channel and wherein the axis of said radiator fan is located on the side of the axis of said heat dissipating exhaust channel remote from said battery exhaust duct.
8. 8. The auxiliary power heat dissipation system for an on-board fuel cell of claim 1, wherein the axis of the cell exhaust line and the axis of the heat dissipation exhaust line have a mixed flow intersection point, and the outlet end of the cell exhaust line extends to a side of the mixed flow intersection point near the outlet of the injection mixing chamber.
9. 9. The auxiliary power heat dissipation system of an on-board fuel cell as defined in claim 1, wherein the fuel cell assembly further comprises a return conduit, wherein the return conduit is in communication with the battery exhaust line and the heat dissipation air intake passage, respectively, and wherein the battery exhaust line is located higher on the aircraft than the heat dissipation air intake passage is located on the aircraft.
10. 10. The auxiliary power radiating system of an airborne fuel cell according to claim 9, wherein the air inlet pipeline of the battery is connected with the radiating air inlet channel to communicate with the external environment of the aircraft, and the water outlet of the return pipe and the air inlet of the air inlet pipeline of the battery are sequentially arranged at intervals along the air flow direction of the radiating air inlet channel.
11. 11. An aircraft comprising an on-board fuel cell auxiliary power heat dissipation system as claimed in any one of claims 1 to 10.
12. 12. An airborne fuel cell auxiliary power heat dissipation control method applied to the airborne fuel cell auxiliary power heat dissipation system as defined in any one of claims 1 to 10, characterized in that the airborne fuel cell auxiliary power heat dissipation control method comprises: Responding to a fuel cell starting instruction, and starting the fuel cell unit to work; and controlling the coolant in the coolant pipe to circulate between the radiator and the fuel cell unit for heat exchange based on the fuel cell unit being in an operating state.
13. 13. The on-board fuel cell auxiliary power heat dissipation control method according to claim 12, further comprising: acquiring the flying height of the aircraft based on the working state of the fuel cell unit; And adjusting the opening of the outlet end of the battery exhaust pipeline according to the flying height, wherein the opening of the outlet end of the battery exhaust pipeline is inversely related to the flying height.
14. 14. The on-board fuel cell auxiliary power heat dissipation control method according to claim 13, further comprising: and adjusting the rotating speed of the cooling fan according to the flying height.
15. 15. The on-board fuel cell auxiliary power heat dissipation control method according to claim 12, further comprising: Acquiring the temperature change speed of the cooling liquid in the cooling liquid pipeline in real time based on the working state of the fuel cell unit; and adjusting the ventilation size of the communication area of the heat dissipation air inlet channel and the radiator based on the temperature change speed being higher than a threshold value until the temperature change speed is lower than the threshold value.
16. 16. The on-board fuel cell auxiliary power heat dissipation control method according to claim 15, further comprising: And adjusting the ventilation size to a maximum value based on the temperature change speed being lower than the threshold value, and adjusting the air intake size of the air inlet of the heat dissipation air intake channel so as to control the temperature change speed to be continuously lower than the threshold value.

Description

Auxiliary power heat dissipation system of airborne fuel cell, aircraft and control method Technical Field The invention relates to the technical field of auxiliary heat dissipation of an airborne fuel cell, in particular to an auxiliary power heat dissipation system of an airborne fuel cell, an aircraft and a control method. Background The auxiliary power system is an important system of an aircraft (such as an airplane, an unmanned aerial vehicle and the like) and is used for providing functions of environmental control, illumination, starting a main engine, restarting the engine in the air, providing emergency power and the like on the ground, and the energy form is mainly electric energy output. The hydrogen fuel cell can efficiently convert chemical energy into electric energy, has the advantages of high energy density, low noise and no pollution, and is beneficial to propelling carbon emission reduction in aviation industry. Because the power level of the auxiliary power system is matched with that of the hydrogen fuel cell system, the hydrogen fuel cell is adopted as the auxiliary power system, so that the aim of reducing aviation carbon emission and promoting the development of the multi-electric aircraft can be fulfilled. However, when the hydrogen fuel cell is used as an auxiliary power system, the efficiency is about 50%, and the residual energy is converted into heat, so that high-power heat dissipation is required in time to ensure the stable operation of the system. The aircraft applying the auxiliary power system has high requirements on lightweight design and integrated layout of the heat dissipation assembly of the auxiliary power system, the current technical level and application are limited, and the heat dissipation energy efficiency of the heat dissipation assembly is required to be further improved. Disclosure of Invention The invention provides an airborne fuel cell auxiliary power heat dissipation system, an aircraft and a control method for solving the problem that the energy efficiency of an airborne heat dissipation assembly needs to be further improved. In a first aspect, the present invention provides an airborne fuel cell auxiliary power heat dissipation system, comprising: the fuel cell assembly comprises a fuel cell unit, a cell air inlet pipeline, a cell air exhaust pipeline and an injection mixing cavity, wherein the cell air inlet pipeline is connected with an air inlet of the fuel cell unit, the cell air exhaust pipeline is connected with an air outlet of the fuel cell unit, the cell air exhaust pipeline is connected with the injection mixing cavity, the channel section of the cell air exhaust pipeline is gradually reduced along the direction from the fuel cell unit to the injection mixing cavity, the cell air inlet pipeline is communicated with the external environment of the aircraft, the opening of the cell air inlet pipeline communicated with the external environment faces the same direction as the head of the aircraft, the injection mixing cavity is communicated with the external environment of the aircraft, and the opening of the injection mixing cavity communicated with the external environment faces the tail of the aircraft; The heat dissipation assembly comprises a heat radiator, a cooling liquid pipeline, a heat dissipation air inlet channel and a heat dissipation air outlet channel, wherein the heat radiator is connected with the fuel cell unit through the cooling liquid pipeline, the heat dissipation air inlet channel is communicated with an air inlet end of the heat radiator, the heat dissipation air outlet channel is connected with an air outlet end of the heat radiator, the heat dissipation air inlet channel is communicated with the external environment of the aircraft, the opening of the heat dissipation air inlet channel communicated with the external environment faces towards the same direction as the head of the aircraft, and the heat dissipation air outlet channel is communicated with the injection mixing cavity. Optionally, the fuel cell assembly further comprises an exhaust adjusting door, the exhaust adjusting door is movably connected with the battery exhaust pipeline, the exhaust adjusting door is located at one end, close to the injection mixing cavity, of the battery exhaust pipeline, and the exhaust adjusting door is movable to adjust the outlet size of the battery exhaust pipeline. Optionally, the opening size of the heat dissipation exhaust channel gradually increases along the direction from the radiator to the injection mixing cavity. Optionally, the heat dissipation assembly further comprises a heat dissipation adjusting door movably connected with the heat dissipation air inlet channel, the heat dissipation adjusting door divides the air inlet end of the heat radiator into a shielding area and a ventilation area, the heat dissipation air inlet channel is communicated with the heat radiator through the ventilation area, the shielding area