A new type of hydrogen fuel cell aircraft

Abstract

This invention aims to enable the normal flight of a hydrogen fuel cell aircraft and designs a novel hydrogen fuel cell aircraft. The front and rear ends of the new hydrogen fuel cell aircraft are connected to the nose cone and fairing via hinges, facilitating easy opening and closing for the insertion and removal of the hydrogen tank and reactor. The hydrogen tank is secured to the front fuselage with cable ties, and the reactor is bolted to the rear fuselage, ensuring stable installation of both components within the fuselage. An air intake cover is located at the top of the rear fuselage, and a drain and exhaust port is located at the bottom. An internal drain pipe connects to the reactor, enabling air intake, drainage, and exhaust, thus ensuring the continuous and normal operation of the reactor.

Description

Technical Field

[0001] This invention relates to a novel hydrogen fuel cell aircraft. Background Technology

[0002] Hydrogen fuel cell aircraft, as a new energy aircraft, have broad application prospects in the future aviation field.

[0003] Hydrogen-fueled aircraft utilize the electrochemical reaction between hydrogen and oxygen to generate electricity to power the aircraft. In this process, hydrogen tanks supply hydrogen to the reactor, where it reacts with oxygen in a redox reaction, producing electricity.

[0004] For hydrogen-fueled aircraft, the space for hydrogen tanks and reactors and their loading and unloading are important issues. Summary of the Invention

[0005] According to one aspect of the present invention, a novel hydrogen fuel cell aircraft is provided, characterized by comprising: a nose cone, a forward fuselage, a fairing, a rear fuselage, a reactor disposed in the rear fuselage, and a hydrogen tank disposed in the forward fuselage.

[0006] in:

[0007] The front end of the forward fuselage is connected to the nose cone via a first hinge, allowing the nose cone to be opened to expose the front end of the forward fuselage, enabling the insertion and / or removal of the hydrogen tank.

[0008] The rear fuselage is higher than the front fuselage, serving both as a vertical tail and connecting to the rear wing, while also providing sufficient space for the reactor.

[0009] The front of the aft fuselage is connected to the fairing via a second hinge, which allows the reactor to be inserted into and / or removed from the aft fuselage by opening the fairing.

[0010] The reactor is fixed in the aft fuselage.

[0011] The top of the rear fuselage has an air intake cover, which allows air to enter the reactor from above to fully absorb oxygen from the air. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0013] Figure 2 This is a cross-sectional view of the fuselage of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention, and a schematic diagram of the installation positions of the hydrogen tank and reactor.

[0014] Figure 3 This is a schematic diagram of the nose cone hinge of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0015] Figure 4 This is a schematic diagram of the insertion and removal of a hydrogen tank in a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0016] Figure 5 This is a schematic diagram of the hydrogen tank fixing of a novel hydrogen fuel aircraft according to an embodiment of the present invention.

[0017] Figure 6 This is a schematic diagram of the fairing hinge of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0018] Figure 7 This is a schematic diagram of the reactor insertion of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0019] Figure 8 This is a schematic diagram of the reactor mounting of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0020] Figure 9 This is a schematic diagram of the reactor air intake of a novel hydrogen fuel cell aircraft according to an embodiment of the present invention.

[0021] Figure 10 This is a schematic diagram of reactor drainage and exhaust for a novel hydrogen fuel cell aircraft according to an embodiment of the present invention. Detailed Implementation

[0022] To address the issues of space constraints and loading / unloading of hydrogen tanks and reactors in hydrogen-fueled aircraft, this invention provides a novel solution for hydrogen-fueled aircraft, wherein the fuselage allows for stable installation and rapid disassembly of the hydrogen tanks and reactors, while facilitating reactor intake and drainage.

[0023] In a novel hydrogen fuel cell aircraft according to an embodiment of the present invention, the hydrogen tank and reactor need to be placed inside the fuselage and securely installed without affecting the installation of other components such as the wings. The hydrogen tank and reactor can be easily disassembled when the hydrogen is depleted and the tank needs to be replaced, or when the reactor needs to be removed for inspection. Simultaneously, to facilitate the reactor's intake of air to provide oxygen for the reaction and the discharge of reaction product water, the reactor's air intake and drainage issues need to be considered.

[0024] like Figure 1-3 As shown, a novel hydrogen fuel cell aircraft according to an embodiment of the present invention includes a nose cone (1), a forward fuselage (2), a fairing (3), and a rear fuselage (4).

[0025] like Figure 1-4As shown, the front end of the front fuselage (2) is connected to the nose cone (1) via a first hinge (11), allowing the nose cone (1) to be opened to expose the front end of the front fuselage (2), thus enabling the insertion and removal of the hydrogen tank (5). According to one embodiment of the present invention, as... Figure 5 As shown, the hydrogen tank (5) can be fixed to the upper part of the front fuselage (2) by cable ties (7).

[0026] like Figure 2 As shown, the rear fuselage (4) is higher than the front fuselage (2), serving as a vertical tail and connecting the rear wing, while also providing sufficient space for the placement of the reactor (6).

[0027] like Figure 6 As shown, the front of the rear fuselage (4) is connected to the fairing cover (3) via a second hinge (12).

[0028] like Figure 7 As shown, the reactor (6) can be placed into the aft fuselage (4) or removed from the aft fuselage (4) by opening the rectifier cover (3).

[0029] like Figure 8 As shown, the reactor (6) can be fixed to the aft fuselage (4) by bolts (8). Eight bolts (8) pass through the mounting plate of the aft fuselage (4) from bottom to top and are screwed into the bottom of the reactor (6) to connect the reactor (6) to the aft fuselage (4).

[0030] like Figure 9 As shown, in order to fully absorb oxygen from the air, there is an air intake cover (9) on the top of the rear fuselage (4), which allows air to enter the reactor (6) from above. During flight, air can enter the rear fuselage (4) through the air intake cover (9) and flow downward from the top inside the rear fuselage (4), with some of it entering the reactor (6) to participate in the reaction.

[0031] like Figure 10 As shown, the drain pipe (10) is connected to the rear of the reactor (6) and is used to discharge the reaction product water. The reaction product water can be discharged downwards through the drain pipe (10) from the opening at the lower end of the rear fuselage (4). At the same time, the unreacted air discharged from the reactor (6) can also be discharged through the opening next to the drain pipe (10) and eventually discharged from the rear fuselage (4) together with the water.

[0032] Beneficial effects

[0033] The advantages and beneficial effects of this invention include:

[0034] 1) The front fuselage is designed with an openable head cover, and the rear fuselage is designed with an openable rectifier cover, which makes it easier to put the hydrogen tank and reactor into or take out the fuselage.

[0035] 2) The nose cone at the front of the forward fuselage and the fairing at the front of the aft fuselage can protect the hydrogen tanks and reactor while reducing the drag of the fuselage.

[0036] 3) The rear fuselage is connected to the rear wing to enhance the strength and rigidity of the structure.

[0037] 4) The rear fuselage can function as a vertical tail, improving the aircraft's directional stability.

[0038] 5) The hydrogen tank can be securely installed in the front fuselage with cable ties, and the reactor can be securely installed in the rear fuselage with bolts.

[0039] 6) Placing the hydrogen tanks and reactor one in front of the other can balance the weight of the aircraft.

[0040] 7) The air inlet cover, drain pipe, and exhaust port facilitate air intake, drainage, and exhaust of the rear fuselage, thus contributing to the normal operation of the reactor.

Claims

1. A novel hydrogen fuel cell aircraft, characterized in that... include: The nose cone (1), the front fuselage (2), the fairing cover (3), the rear fuselage (4), the reactor (6) located in the rear fuselage (4), and the hydrogen tank (5) located in the front fuselage (2). in: The front end of the front fuselage (2) is connected to the nose cone (1) via a first hinge (11), thereby allowing the nose cone (1) to be opened to expose the front end of the front fuselage (2), enabling the insertion and / or removal of the hydrogen tank (5). The rear fuselage (4) is higher than the front fuselage (2), serving both as a vertical tail and connecting to the rear wing, and also providing sufficient space for the placement of the reactor (6). The front of the aft fuselage (4) is connected to the fairing cover (3) via a second hinge (12) for inserting the reactor (6) into the aft fuselage (4) and / or removing the reactor (6) from the aft fuselage (4) by opening the fairing cover (3). The reactor (6) is fixed in the aft fuselage (4). The rear fuselage (4) has an air inlet cover (9) on top, which is used to allow air to enter the reactor (6) from above, so as to fully absorb oxygen in the air.

2. The novel hydrogen fuel cell aircraft according to claim 1, characterized in that... Further includes: A drain pipe (10) connected to the rear of the reactor (6) is used to discharge water, which is a product of the reaction.

3. The novel hydrogen fuel cell aircraft according to claim 2, characterized in that: The reaction product water is discharged downward through the drain pipe (10) from the opening at the lower end of the rear fuselage (4).

4. The novel hydrogen fuel cell aircraft according to claim 3, characterized in that: Unreacted air from the reactor (6) is discharged through an opening next to the drain pipe (10) and eventually discharged with water from the rear fuselage (4).

5. The novel hydrogen fuel cell aircraft according to claim 1, characterized in that: The hydrogen tank (5) is secured to the upper part of the front fuselage (2) by cable ties (7).

6. The novel hydrogen fuel cell aircraft according to claim 1, characterized in that: The reactor (6) is fixed to the rear fuselage (4) by bolts (8).

7. The novel hydrogen fuel cell aircraft according to claim 6, characterized in that: Eight bolts (8) pass through the mounting plate on the rear fuselage (4) from bottom to top and are screwed into the bottom of the reactor (6) to connect the reactor (6) to the rear fuselage (4).

8. The novel hydrogen fuel cell aircraft according to claim 1, characterized in that: During flight, air enters the rear fuselage (4) through the air intake cover (9) and flows downward from the top inside the rear fuselage (4). A portion of the air enters the reactor (6) to participate in the reaction.

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