Power system heat dissipation structure of hydrogen fuel cell aircraft

Abstract

The utility model relates to the technical field of hydrogen fuel cell power system heat dissipation, and discloses a power system heat dissipation structure of a hydrogen fuel cell aircraft, which comprises an upper power cover, the lower surface of the upper power cover is fixedly connected with a lower power cover, and the inner walls of the left upper side and the right upper side of the lower power cover are provided with motor cooling ventilation openings. A DC-DC cooling ventilation opening is formed in the lower side of the power lower cover, a seat ventilation assembly is arranged on the inner wall of the power lower cover, and the seat ventilation assembly is used for improving comfort in the driving process. According to the utility model, the power upper cover and the power lower cover are used as a whole and are provided with a plurality of ventilation openings, including a charging opening cover, a motor cooling ventilation opening, a cabin ventilation opening, a cabin ventilation pipe, an electric control cooling ventilation opening, a hydrogen fuel cell cooling ventilation opening and a motor auxiliary ventilation cooling opening, so that different parts can be cooled by different airflow channels; the structure is simple, heat dissipation can be conducted on a power system, and ventilation can be conducted on a manned cabin.

Description

Technical Field

[0001] The utility model relates to the technical field of heat dissipation of a hydrogen fuel cell power system, in particular to a heat dissipation structure of a power system of a hydrogen fuel cell aircraft. Background Art

[0002] A hydrogen fuel cell is a device that uses hydrogen and oxygen to generate electricity through an electrochemical reaction. It usually includes an electrolyte membrane (such as a polymer electrolyte membrane) to separate hydrogen and oxygen, while allowing protons (the ion form of hydrogen) to pass through, but blocking the flow of electrons. This causes the hydrogen atoms of hydrogen to be absorbed by the oxygen atoms of oxygen, thereby producing water and electricity.

[0003] Hydrogen fuel cells generate heat during operation, especially during electrochemical reactions. To ensure stable operation and long-term reliability of the battery system, an effective heat dissipation system is required to control and remove this heat. The power system heat dissipation structure in the aircraft can effectively remove heat from batteries and electronic equipment through radiators, coolant circulation systems, etc. The internal space of the aircraft is limited, so the heat dissipation structure design of the power system needs to take into account effective integration and optimization with other aircraft systems. This includes maximizing heat dissipation efficiency without affecting the aircraft's space and weight restrictions.

[0004] However, most heat dissipation structures dissipate heat mechanically during use, but the space inside the aircraft is limited. During use, the heat dissipation structure may be simplified due to weight reasons, which will cause the heat dissipation structure to shrink, resulting in uneven heat dissipation and affecting the performance of the machinery. Utility Model Content

[0005] In order to make up for the above deficiencies, the utility model provides a heat dissipation structure of a power system of a hydrogen fuel cell aircraft, aiming to improve the problem of poor heat dissipation effect caused by shrinking the heat dissipation structure due to weight considerations.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A heat dissipation structure for a power system of a hydrogen fuel cell aircraft comprises an upper power cover, wherein the lower surface of the power upper cover is fixedly connected to a power lower cover, the upper left inner wall and the upper right inner wall of the power lower cover are provided with motor cooling vents, the left outer wall of the power upper cover is provided with a charging port cover, the left bottom inner wall and the right bottom inner wall of the power lower cover are provided with cabin vents, the upper middle inner wall of the power lower cover is provided with an electric control cooling vent, the middle inner wall of the power lower cover is provided with a hydrogen fuel cell cooling vent, the lower side of the power lower cover is provided with a DC-DC cooling vent, and the inner wall of the power lower cover is provided with a seat ventilation assembly, and the seat ventilation assembly is used to improve comfort during driving.

[0008] Preferably, the seat ventilation assembly comprises a cabin ventilation duct, an outer wall of the cabin ventilation duct is arranged on the inner wall of the power lower cover, and the outer wall of the cabin ventilation duct is fixedly connected to the inner wall of the cabin vent.

[0009] Preferably, the outer wall of the cabin ventilation duct is fixedly connected to the inner wall of the motor cooling vent, and the outer wall of the cabin ventilation duct is fixedly connected to the inner wall of the motor auxiliary ventilation cooling port.

[0010] Preferably, the inner walls of the power upper cover and the power lower cover are fixedly connected with ventilation pipes, and the ends of the ventilation pipes are directly opposite to the motor body to guide the airflow to the motor.

[0011] Preferably, an electric control radiator is provided on the inner wall of the power lower cover, a cooling water pipe B is fixedly connected to the outer wall of the electric control radiator, and an electric control body is fixedly connected to the outer wall of the cooling water pipe B.

[0012] Preferably, a stack radiator is provided on the inner wall of the power lower cover, and the outer wall of the stack radiator is fixedly connected to the inner wall of the cooling vent of the hydrogen fuel cell.

[0013] Preferably, the outer wall of the stack radiator is fixedly connected to a cooling water pipe A, the outer wall of the cooling water pipe A is fixedly connected to a hydrogen fuel cell body, and the outer wall of the hydrogen fuel cell body is fixedly connected to the inside of the power upper cover and the power lower cover.

[0014] Preferably, the inner wall of the power lower cover is fixedly connected to a radiator bracket, the outer wall of the electronically controlled radiator is fixedly connected to the left outer wall of the radiator bracket, and the outer wall of the battery stack radiator is fixedly connected to the left outer wall of the radiator bracket.

[0015] The utility model has the following beneficial effects:

[0016] 1. In the utility model, the power upper cover and the power lower cover are taken as a whole, and some vents are arranged, including charging port covers, motor cooling vents, cabin vents, cabin ventilation ducts, electronically controlled cooling vents, hydrogen fuel cell cooling vents and motor auxiliary ventilation cooling vents. Different airflow channels can cool different components during operation, with good heat dissipation effect and simple structure, which can not only dissipate heat for the power system, but also ventilate the manned cabin.

[0017] 2. In the utility model, outside air is introduced into the aircraft cabin through the cabin vent, and the outside air in the motor auxiliary ventilation cooling port is assisted by the cabin ventilation duct installed on the motor cooling vent and the cabin vent to provide sufficient cooling air for the motor body, and all the incoming air flows out through the large opening at the bottom protrusion of the power lower cover. The front placement of the radiator is conducive to the airflow cooling the motor, thereby improving the life and reliability of the motor, and is conducive to the airflow cooling the fuel cell, thereby improving the battery life and reliability.

[0018] 3. In the utility model, the outside air in the electronically controlled cooling vents cools the water in the installed cooling water pipe B through the electronically controlled radiator and then enters the electronically controlled body for cooling. The outside air in the hydrogen fuel cell cooling vents cools the water in the installed cooling water pipe A through the stack radiator and then enters the hydrogen fuel cell body for cooling. The electronically controlled radiator and the stack radiator form a channel for free air flow to take away heat. The above components are assembled to meet the heat dissipation performance of the hydrogen fuel cell power system. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a side view of a heat dissipation structure of a power system of a hydrogen fuel cell aircraft proposed by the utility model;

[0020] Figure 2 This is a top view of a heat dissipation structure of a power system of a hydrogen fuel cell aircraft proposed by the utility model;

[0021] Figure 3 This is a front view of a heat dissipation structure of a power system of a hydrogen fuel cell aircraft proposed by the utility model.

[0022] Legend:

[0023] 1. Motor body; 2. Hydrogen fuel cell body; 3. Electronic control radiator; 4. Stack radiator; 5. Cabin ventilation duct; 6. Charging port cover; 7. Power upper cover; 8. Power lower cover; 9. Motor cooling vents; 10. Cabin vents; 11. Electronic control cooling vents; 12. Hydrogen fuel cell cooling vents; 13. DC-DC cooling vents; 14. Motor auxiliary ventilation cooling vents; 15. Radiator bracket; 16. Electronic control body; 17. Cooling water pipe A; 18. Cooling water pipe B. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings of the specification of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0025] Reference Figure 1-Figure 3 , the utility model provides an embodiment: a power system heat dissipation structure of a hydrogen fuel cell aircraft, including an upper power cover 7, the lower surface of the power upper cover 7 is fixedly connected to a power lower cover 8, the upper left inner wall and the upper right inner wall of the power lower cover 8 are provided with motor cooling vents 9, the left outer wall of the power upper cover 7 is provided with a charging port cover 6, the left bottom and the right bottom inner wall of the power lower cover 8 are provided with cabin vents 10, the upper middle inner wall of the power lower cover 8 is provided with an electric control cooling vent 11, the middle inner wall of the power lower cover 8 is provided with a hydrogen fuel cell cooling vent 12, the lower side of the power lower cover 8 is provided with a DC-DC cooling vent 13, the inner wall of the power lower cover 8 is provided with a seat ventilation assembly, the seat ventilation assembly is used to improve comfort during driving; the seat ventilation assembly includes a cabin ventilation pipe 5, the outer wall of the cabin ventilation pipe 5 is arranged on the inner wall of the power lower cover 8, and the outer wall of the cabin ventilation pipe 5 is fixedly connected to the inner wall of the cabin vent 10;

[0026] Specifically, during the operation of the aircraft, when the aircraft moves forward, wind enters different cooling vents through the cabin vents 10, the electronically controlled cooling vents 11, the DC-DC cooling vents 13, the hydrogen fuel cell cooling vents 12 and the cabin ventilation pipes 5 to cool the internal structure. The heat dissipation effect is good, and the simple structure can not only dissipate heat for the power system, but also ventilate the manned cabin.

[0027] Reference Figure 1-Figure 3 The outer wall of the cabin ventilation pipe 5 is fixedly connected to the inner wall of the motor cooling vent 9, and the outer wall of the cabin ventilation pipe 5 is fixedly connected to the inner wall of the motor auxiliary ventilation cooling port 14; the inner walls of the power upper cover 7 and the power lower cover 8 are fixedly connected with ventilation pipes, and the ends of the ventilation pipes are directly opposite to the motor body 1 to guide the airflow to the motor; the inner wall of the power lower cover 8 is provided with an electric control radiator 3, and the outer wall of the electric control radiator 3 is fixedly connected to the cooling water pipe B18, and the outer wall of the cooling water pipe B18 is fixedly connected to the electric control body 16;

[0028] Specifically, during use, the outside air in the electronically controlled cooling vent 11 passes through the electronically controlled radiator 3 to cool the water in the installed cooling water pipe B18 and then enters the electronically controlled body 16 for cooling. During use, the incoming airflow flows out through the large opening at the bottom protrusion of the power lower cover 8, forming a channel for free air flow to take away heat.

[0029] Reference Figure 1-Figure 3 The inner wall of the power lower cover 8 is provided with a stack radiator 4, and the outer wall of the stack radiator 4 is fixedly connected to the inner wall of the hydrogen fuel cell cooling vent 12; the outer wall of the stack radiator 4 is fixedly connected to the cooling water pipe A17, and the outer wall of the cooling water pipe A17 is fixedly connected to the hydrogen fuel cell body 2, and the outer wall of the hydrogen fuel cell body 2 is fixedly connected to the inside of the power upper cover 7 and the power lower cover 8; the inner wall of the power lower cover 8 is fixedly connected to the radiator bracket 15, the outer wall of the electronic control radiator 3 is fixedly connected to the left outer wall of the radiator bracket 15, and the outer wall of the stack radiator 4 is fixedly connected to the left outer wall of the radiator bracket 15;

[0030] Specifically, the outside air in the hydrogen fuel cell cooling vent 12 cools the water in the installed cooling water pipe A17 through the stack radiator 4 and then enters the hydrogen fuel cell body 2 for cooling. All incoming air flows out through the large opening at the bottom protrusion of the power lower cover 8, forming a channel for free air flow, taking away heat, and achieving the heat dissipation performance of the hydrogen fuel cell power system.

[0031] Working principle: When the heat dissipation structure is needed, the front end of the aircraft is composed of a power upper cover 7 and a power lower cover 8 to form an inclusive space, in which the hydrogen fuel cell power system and the heat dissipation device are arranged. The power upper cover 7 and the power lower cover 8 are connected together by bolts. As a whole, some vents are arranged to facilitate air entry, including a charging port cover 6, a motor cooling vent 9, a cabin vent 10, an electric control cooling vent 11, a hydrogen fuel cell cooling vent 12, a motor auxiliary ventilation cooling vent 14, etc. Different airflow channels cool different components respectively, among which the vent installed on the cabin vent 10 The cabin ventilation duct 5 introduces outside air into the aircraft cabin, the outside air in the motor cooling vent 9 and the motor auxiliary ventilation cooling vent 14 provides sufficient cooling air to the motor body 1, the outside air in the electronically controlled cooling vent 11 cools the water in the installed cooling water pipe B18 through the electronically controlled radiator 3 and then enters the electronically controlled body 16 for cooling, the outside air in the hydrogen fuel cell cooling vent 12 cools the water in the installed cooling water pipe A17 through the stack radiator 4 and then enters the hydrogen fuel cell body 2 for cooling, wherein the electronically controlled radiator 3 and the stack radiator 4 are fixed to the radiator bracket 15 by bolts. All incoming air flows out through the large opening at the bottom protrusion of the power lower cover 8, forming a channel for free air flow to take away heat. After the above components are assembled, the heat dissipation performance of the hydrogen fuel cell power system is met. During use, the heat dissipation structure of the aircraft power system not only achieves the charging port cover 6, the motor cooling vents 9, the cabin vents 10, the cabin ventilation pipe 5, the electronically controlled cooling vents 11, the hydrogen fuel cell cooling vents 12 and the motor auxiliary ventilation cooling vents 14. During operation, different air flow channels can cool different components, and the heat dissipation effect is good. It can not only dissipate heat for the power system, but also ventilate the manned cabin. It also has the characteristics that the outside air in the electronically controlled cooling vents 11 cools the water in the installed cooling water pipe B18 through the electronically controlled radiator 3 and then enters the electronically controlled body 16 for cooling. The outside air in the hydrogen fuel cell cooling vents 12 cools the water in the installed cooling water pipe A17 through the stack radiator 4 and then enters the hydrogen fuel cell body 2 for cooling. The electronically controlled radiator 3 and the stack radiator 4 form a channel for free air flow to take away heat, which improves the heat dissipation performance of the fuel cell power system.

[0032] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A heat dissipation structure of a power system of a hydrogen fuel cell aircraft, comprising an upper power cover (7), characterized in that: The lower surface of the power upper cover (7) is fixedly connected to the power lower cover (8); the upper left inner wall and the upper right inner wall of the power lower cover (8) are provided with motor cooling vents (9); the left outer wall of the power upper cover (7) is provided with a charging port cover (6); the left bottom inner wall and the right bottom inner wall of the power lower cover (8) are provided with cabin vents (10); the upper middle inner wall of the power lower cover (8) is provided with electric control cooling vents (11); the middle inner wall of the power lower cover (8) is provided with hydrogen fuel cell cooling vents (12); the lower side of the power lower cover (8) is provided with DC-DC cooling vents (13); the inner wall of the power lower cover (8) is provided with a seat ventilation assembly, and the seat ventilation assembly is used to improve comfort during driving.

2. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 1, characterized in that: The seat ventilation assembly comprises a cabin ventilation pipe (5), the outer wall of the cabin ventilation pipe (5) being arranged on the inner wall of the power lower cover (8), and the outer wall of the cabin ventilation pipe (5) being fixedly connected to the inner wall of the cabin ventilation opening (10).

3. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 2, characterized in that: The outer wall of the cabin ventilation pipe (5) is fixedly connected to the inner wall of the motor cooling vent (9), and the outer wall of the cabin ventilation pipe (5) is fixedly connected to the inner wall of the motor auxiliary ventilation cooling port (14).

4. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 3, characterized in that: The inner walls of the power upper cover (7) and the power lower cover (8) are both fixedly connected with ventilation pipes, and the ends of the ventilation pipes are directly opposite to the motor body (1) to guide the airflow to the motor.

5. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 4, characterized in that: An electric control radiator (3) is provided on the inner wall of the power lower cover (8), a cooling water pipe B (18) is fixedly connected to the outer wall of the electric control radiator (3), and an electric control body (16) is fixedly connected to the outer wall of the cooling water pipe B (18).

6. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 5, characterized in that: The inner wall of the power lower cover (8) is provided with a stack radiator (4), and the outer wall of the stack radiator (4) is fixedly connected to the inner wall of the hydrogen fuel cell cooling vent (12).

7. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 6, characterized in that: The outer wall of the stack radiator (4) is fixedly connected to a cooling water pipe A (17), the outer wall of the cooling water pipe A (17) is fixedly connected to a hydrogen fuel cell body (2), and the outer wall of the hydrogen fuel cell body (2) is fixedly connected to the inside of a power upper cover (7) and a power lower cover (8).

8. The heat dissipation structure of the power system of a hydrogen fuel cell aircraft according to claim 7, characterized in that: The inner wall of the power lower cover (8) is fixedly connected to a radiator bracket (15), the outer wall of the electronically controlled radiator (3) is fixedly connected to the left outer wall of the radiator bracket (15), and the outer wall of the battery stack radiator (4) is fixedly connected to the left outer wall of the radiator bracket (15).

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