Power system mounting structure of hydrogen fuel cell aircraft

Abstract

The utility model relates to the technical field of aerospace, and discloses a power system mounting structure of a hydrogen fuel cell aircraft, which comprises an aircraft main body, a fixing frame is mounted at the front end of the aircraft main body, a hydrogen fuel cell main body is arranged in the fixing frame, and a damping mechanism is arranged outside one end, far away from the hydrogen fuel cell main body, of the fixing frame. The damping mechanism is used for damping the motor main body, the motor main body is fixedly connected to the exterior of the damping mechanism, a propeller is fixedly connected to the output end of the motor main body, a front wheel rod is installed outside the end, away from the hydrogen fuel cell main body, of the fixing frame, and a supporting structural part is arranged outside the middle end of the aircraft main body. According to the utility model, the motor main body is driven to rotate by the hydrogen fuel cell main body, and when the motor main body rotates, the impact force of the motor is buffered by damping the motor connecting plate, so that the motor main body works stably, is safe and reliable, and is not easy to loosen.

Description

Technical Field

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

[0002] The aircraft power system generates enough thrust to propel the aircraft in the air, which is critical to overcoming gravity and air resistance, enabling the aircraft to take off, maintain flight altitude and speed, and land. The aircraft power system not only provides forward thrust, but also controls engine thrust to achieve attitude adjustment, altitude change and speed control during flight. This control is crucial to the safety and comfort of the aircraft. The aircraft has different demands on the power system during each flight phase, such as take-off, climb, cruise, descent and landing. The power system must be able to provide appropriate thrust and response speed to cope with the different flight requirements and environmental changes in these phases.

[0003] However, the current traditional fuel engines have problems such as very unstable motor operation during use, which causes large vibrations of the entire machine, unstable motor operation, and excessively high fuel engine temperatures during use, resulting in a shorter battery life. Utility Model Content

[0004] In order to make up for the above shortcomings, the utility model provides a power system installation structure of a hydrogen fuel cell aircraft, aiming to improve the problems of large vibration of the whole machine and low battery life during use of the fuel engine.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a power system installation structure of a hydrogen fuel cell aircraft, comprising an aircraft body, a fixing frame is installed at the front end of the aircraft body, a hydrogen fuel cell body is arranged inside the fixing frame, a shock absorbing mechanism is arranged outside the end of the fixing frame away from the hydrogen fuel cell body, the shock absorbing mechanism is used to reduce shock to the motor body, the motor body is fixedly connected to the outside of the shock absorbing mechanism, a propeller is fixedly connected to the output end of the motor body, a front wheel rod is installed outside the end of the fixing frame away from the hydrogen fuel cell body, a supporting structure is arranged outside the middle end of the aircraft body, a battery fixing box is installed inside the middle end of the aircraft body, and a lithium battery is arranged inside the battery fixing box.

[0006] Preferably, the shock absorbing mechanism includes a motor connecting plate, one side of the motor connecting plate is externally mounted on the outside of one end of the fixing frame, the other side of the motor connecting plate is externally mounted on the outside of the motor body, and shock absorbing rubber is installed on the four external ends of both sides of the motor connecting plate.

[0007] Preferably, a gas cylinder clamp is installed on the top of the supporting structure, and a hydrogen cylinder is arranged inside the gas cylinder clamp.

[0008] Preferably, the bottom of the battery fixing box is arranged on the top of the supporting structure.

[0009] Preferably, one end of the fixing bracket close to the motor connecting plate is externally arranged between the motor connecting plate and the shock absorbing rubber.

[0010] Preferably, a battery pressure strip is provided on the outside of the hydrogen fuel cell body, and the outside of the battery pressure strip is mounted on the outside of the fixing frame.

[0011] Preferably, the exterior of the hydrogen fuel cell body is arranged inside the square frame area of ​​the fixing frame.

[0012] The utility model has the following beneficial effects:

[0013] 1. In the utility model, the motor body is driven to rotate by the hydrogen fuel cell body. When the motor body is rotating, the motor connecting plate is damped by a plurality of damping rubbers arranged outside the motor body. The damping of the motor connecting plate can buffer the impact force of the motor, thereby reducing the vibration of the whole machine, and making the motor body work stably, safely and reliably, and not easy to loosen.

[0014] 2. In the present invention, by arranging the hydrogen fuel cell body at the front end of the aircraft body, the airflow in the air can be used to cool the hydrogen fuel cell body during use, thereby achieving the effect of improving the battery life and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is an overall layout diagram of the power system installation structure of a hydrogen fuel cell aircraft proposed by the utility model;

[0016] Figure 2 This is a front end layout diagram of a power system installation structure of a hydrogen fuel cell aircraft proposed by the utility model;

[0017] Figure 3 This is a mid-section layout diagram of a power system installation structure of a hydrogen fuel cell aircraft proposed by the utility model.

[0018] Legend:

[0019] 1. Propeller; 2. Motor body; 3. Fixing frame; 4. Shock absorption mechanism; 5. Front wheel rod; 6. Hydrogen fuel cell body; 7. Lithium battery; 8. Hydrogen cylinder; 9. Support structure; 10. Aircraft body; 11. Motor connecting plate; 12. Shock absorption rubber; 13. Battery pressure strip; 14. Battery fixing box; 15. Gas cylinder clamp. DETAILED DESCRIPTION

[0020] 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.

[0021] Reference Figure 1-Figure 3 The utility model provides an embodiment: a power system installation structure of a hydrogen fuel cell aircraft, including an aircraft body 10, a fixing frame 3 is installed at the front end of the aircraft body 10, a hydrogen fuel cell body 6 is arranged inside the fixing frame 3, and the outside of the hydrogen fuel cell body 6 is arranged inside the square frame area of ​​the fixing frame 3, and a shock absorbing mechanism 4 is arranged outside the end of the fixing frame 3 away from the hydrogen fuel cell body 6, and the shock absorbing mechanism 4 is used to shock the motor body 2, and the outside of the shock absorbing mechanism 4 is fixedly connected to the motor body 2, and the output end of the motor body 2 is fixedly connected to the propeller 1, and the outside of the fixing frame 3 away from the hydrogen fuel cell body 6 is installed with a front wheel rod 5, and the aircraft body A supporting structure 9 is provided outside the middle end of the aircraft body 10, and a battery fixing box 14 is installed inside the middle end of the aircraft body 10. The bottom of the battery fixing box 14 is arranged on the top of the supporting structure 9, and a lithium battery 7 is arranged inside the battery fixing box 14; the hydrogen fuel cell body 6 is fixed by the fixing frame 3, and the motor body 2 is driven to rotate by the hydrogen fuel cell body 6. When the motor body 2 is rotating, the shock absorbing mechanism 4 arranged outside the motor body 2 buffers the impact force of the motor body 2, so as to achieve the effect of reducing the vibration of the whole machine, making the motor body 2 stable, safe and reliable, and not easy to loosen, and driving the propeller 1 fixedly connected to its output end to rotate through the motor body 2. The hydrogen fuel cell body 6 drives the motor body 2 to rotate to reduce the sound and vibration during takeoff, which helps to reduce the noise pollution during the takeoff and landing of the aircraft and the flight.

[0022] Reference Figure 1 , Figure 2 The shock absorbing mechanism 4 includes a motor connecting plate 11, one side of the motor connecting plate 11 is externally mounted on the outside of one end of the fixing frame 3, and the other side of the motor connecting plate 11 is externally mounted on the outside of the motor body 2. Shock absorbing rubbers 12 are installed on the four ends of the two sides of the motor connecting plate 11, and the end of the fixing frame 3 close to the motor connecting plate 11 is externally arranged between the motor connecting plate 11 and the shock absorbing rubber 12; when the motor body 2 vibrates during operation, the motor connecting plate 11 is damped by multiple shock absorbing rubbers 12, and the motor body 2 is damped by damping the motor connecting plate 11.

[0023] Reference Figure 1 , Figure 3A gas cylinder clamp 15 is installed on the top of the supporting structure 9, and a hydrogen cylinder 8 is arranged inside the gas cylinder clamp 15; the gas cylinder clamp 15 is used to fix the hydrogen cylinder 8.

[0024] Reference Figure 1 , Figure 2 A battery pressure strip 13 is provided on the outside of the hydrogen fuel cell body 6, and the outside of the battery pressure strip 13 is installed on the outside of the fixing frame 3; the battery pressure strip 13 is used to limit the hydrogen fuel cell body 6.

[0025] Working principle: When the device is needed, the hydrogen fuel cell body 6 is fixed by the fixing frame 3, and the motor body 2 is driven to rotate by the hydrogen fuel cell body 6. When the motor body 2 is rotating, the motor connecting plate 11 is damped by multiple shock-absorbing rubbers 12 arranged outside the motor body 2. The motor connecting plate 11 is damped to achieve the effect of buffering the impact force of the motor body 2, so that the vibration of the whole machine is small, the motor body 2 works stably, safely and reliably, and is not easy to loosen. The propeller 1 fixedly connected to its output end is driven to rotate by the motor body 2, and the motor body 2 is driven to rotate by the hydrogen fuel cell body 6 to reduce the sound and vibration during take-off, which helps to reduce the noise pollution during aircraft take-off and landing and flight. The hydrogen cylinder 8 of the aircraft body 10 can store hydrogen under high pressure. Since hydrogen is gaseous at room temperature, in order to store enough energy in a limited space, the hydrogen needs to be compressed to a very high pressure. The hydrogen cylinder 8 can usually withstand a pressure of hundreds to thousands of atmospheres. In this way, a large amount of hydrogen can be stored in a smaller space, providing the long range and high efficiency required by the aircraft. In addition, the safety of the high-pressure gas needs to be considered when designing and manufacturing the hydrogen cylinder 8, so as to ensure that it can withstand external environmental conditions and internal pressure changes without leakage or explosion. In addition, by arranging the hydrogen fuel cell body 6 at the front end of the aircraft body 10, the airflow in the air can be used to cool the hydrogen fuel cell body 6 during use, thereby improving the life and reliability of the hydrogen fuel cell body 6.

[0026] 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 power system installation structure for a hydrogen fuel cell aircraft, comprising an aircraft body (10), characterized in that: A fixing frame (3) is installed at the front end of the aircraft body (10), a hydrogen fuel cell body (6) is arranged inside the fixing frame (3), a shock absorbing mechanism (4) is arranged outside the end of the fixing frame (3) away from the hydrogen fuel cell body (6), the shock absorbing mechanism (4) is used to reduce the vibration of the motor body (2), the motor body (2) is fixedly connected to the outside of the shock absorbing mechanism (4), the output end of the motor body (2) is fixedly connected to the propeller (1), a front wheel rod (5) is installed outside the end of the fixing frame (3) away from the hydrogen fuel cell body (6), a supporting structure (9) is arranged outside the middle end of the aircraft body (10), a battery fixing box (14) is installed inside the middle end of the aircraft body (10), and a lithium battery (7) is arranged inside the battery fixing box (14).

2. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: The shock absorbing mechanism (4) comprises a motor connecting plate (11), one side of the motor connecting plate (11) is externally mounted on the outside of one end of a fixing frame (3), the other side of the motor connecting plate (11) is externally mounted on the outside of a motor body (2), and shock absorbing rubber (12) is installed on the four ends of both sides of the motor connecting plate (11).

3. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: A gas cylinder clamp (15) is installed on the top of the supporting structure (9), and a hydrogen cylinder (8) is arranged inside the gas cylinder clamp (15).

4. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: The bottom of the battery fixing box (14) is arranged on the top of the supporting structure (9).

5. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: One end of the fixing frame (3) close to the motor connecting plate (11) is externally arranged between the motor connecting plate (11) and the shock absorbing rubber (12).

6. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: A battery pressure strip (13) is provided on the outside of the hydrogen fuel cell body (6), and the outside of the battery pressure strip (13) is mounted on the outside of the fixing frame (3).

7. The power system installation structure of a hydrogen fuel cell aircraft according to claim 1, characterized in that: The exterior of the hydrogen fuel cell body (6) is arranged inside the square frame area of ​​the fixing frame (3).

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