Center-of-gravity-adjustable hydrogen tank mounting structure of hydrogen energy unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a gravity-center-adjustable hydrogen tank mounting structure of a hydrogen energy unmanned aerial vehicle, which comprises a vehicle body frame assembly, a hoop assembly and a locking pad assembly, and the section of the vehicle body frame assembly is C-shaped; the hoop assembly and the machine body frame assembly are connected to form a circular piece, and the circular piece is used for locking the outer ring of the hydrogen tank; the locking pad assembly is arranged on the inner ring of the circular piece formed by the machine body frame assembly and the clamping hoop assembly. The device limits the axial movement degree of freedom, the axial rotation degree of freedom and the radial degree of freedom of the hydrogen tank, so that the hydrogen tank is conveniently mounted.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a hydrogen tank mounting structure of a hydrogen energy UAV with an adjustable center of gravity. Background Art

[0002] The position of a drone's center of gravity is closely related to its flight performance. During flight tests during the drone's R&D and testing phase, discrepancies between the designed center of gravity of each system and the actual integrated center of gravity can cause the drone's center of gravity to differ from the design. This often necessitates additional counterweighting to ensure satisfactory flight performance. Furthermore, during the testing phase, some test subjects do not require a mission payload and require counterweights to replace it. The weight of these additional counterweight structures affects the drone's takeoff weight. Adjusting the center of gravity by adjusting the hydrogen tank's heading position during testing can reduce the counterweight weight and ultimately lower the overall drone weight.

[0003] Hydrogen, the most abundant element in the universe, is used as a fuel for cars, forklifts, and other types of ground vehicles. Currently, hydrogen fuel is being used in aircraft. Hydrogen fuel cell aircraft require hydrogen tanks to store and supply hydrogen, using technology from ground vehicles that is highly impact-resistant.

[0004] Currently, the installation structure of hydrogen tanks on aircraft is relatively complex. Generally, additional structures are added for fixation and axial limitation, which increases the weight and complexity of the aircraft.

[0005] Therefore, it is necessary to provide a hydrogen tank installation structure with an adjustable center of gravity for a hydrogen-powered UAV to solve the above problems. Utility Model Content

[0006] The utility model provides a hydrogen tank mounting structure with an adjustable center of gravity for a hydrogen-powered UAV, so as to solve the problem that the existing hydrogen tank mounting structure on an aircraft is relatively complicated. Generally, a special hydrogen tank mounting structure is added to the frame beam structure in the traditional UAV structure for structural fixation and axial limitation, which increases the weight and complexity of the aircraft. The utility model reduces the number and weight of structures by adapting and redesigning the existing frame structure.

[0007] The utility model discloses a hydrogen tank mounting structure with an adjustable center of gravity for a hydrogen-powered UAV, which adopts the following technical solution, including: a body frame assembly, a clamp assembly, and a locking pad assembly. The cross-section of the body frame assembly is C-shaped; the clamp assembly is connected to the body frame assembly to form a circular part, which is used to lock the outer ring of the hydrogen tank; the locking pad assembly is arranged on the inner ring of the circular part formed by the body frame assembly and the clamp assembly.

[0008] Preferably, the fuselage frame assembly comprises: two C-shaped fuselage frames and a fuselage skin, the outer circumferences of the two C-shaped fuselage frames are connected by fuselage beams to form a skeleton; the fuselage skin is covered on the outer surface of the skeleton.

[0009] Preferably, a weight-reducing hole is provided on the axial surface of the C-shaped body frame.

[0010] Preferably, the C-shaped body frame comprises: a semicircular member, each of whose two ends is connected to an arc segment, and the connecting end surface of the arc segment and the semicircular member forms a connecting step surface.

[0011] Preferably, the clamp assembly comprises: a semicircular clamp, the outer peripheral surface of the end of which is provided with a connecting ear piece, and the connecting ear piece is connected to the connecting step surface of the semicircular member through a locking bolt.

[0012] Preferably, the locking pad assembly comprises: a first semicircular rubber pad and a second semicircular rubber pad, the first semicircular rubber pad is arranged on the inner ring of the semicircular clamp, and the second semicircular rubber pad is arranged on the inner ring of the semicircular member.

[0013] The beneficial effects of the utility model are:

[0014] 1. The load-bearing design of the hydrogen tank utilizes the classic fuselage frame and skin structure of traditional oil-powered UAVs. Compared with the classic structure of oil-powered UAVs, no new structural parts are added, thus achieving the lightest weight. A circular part that locks the outer ring of the hydrogen tank is formed by the clamp assembly and the fuselage frame assembly to achieve the restriction of the radial freedom of the hydrogen tank. At the same time, a locking pad assembly is set on the inner ring of the circular part formed by the fuselage frame assembly and the clamp assembly. That is, the friction force brought by the locking pad assembly limits the axial movement freedom and axial rotation freedom of the hydrogen tank. As long as the clamp assembly is installed and disassembled, the hydrogen tank can be easily installed.

[0015] 2. Simply loosen the locking bolt to release the semicircular clamp from locking the hydrogen tank. The hydrogen tank can then be moved axially to adjust the drone's center of gravity. This means that while limiting the hydrogen tank's freedom in all directions, the present invention does not disrupt the main force transmission path of the aircraft. Furthermore, during the test phase, the hydrogen tank can be moved to adjust the drone's center of gravity, thereby reducing the error between the design and actual weight and the counterweight weight when not loaded with a mission payload. The installation method provided by this invention features a lightweight structure and simple and effective center of gravity adjustment. It is highly practical and adaptable, and can be promoted. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1This is a schematic diagram of the overall installation structure of a hydrogen tank on the body of a hydrogen-powered UAV with an adjustable center of gravity.

[0018] Figure 2 This is a schematic diagram of the use state of the hydrogen tank installation structure of the hydrogen energy UAV with adjustable center of gravity in the body of the utility model;

[0019] Figure 3 This is a schematic diagram of the hydrogen tank installation structure;

[0020] Figure 4 This is the left view of the hydrogen tank installation structure;

[0021] Figure 5 This is a partial structural diagram of the connection between the semicircular clamp and the C-shaped body frame;

[0022] Figure 6 This is a schematic diagram of the installation of the hydrogen tank in a fixed axial position.

[0023] In the figure: 1. C-shaped fuselage frame; 11. Weight-reducing hole; 2. Semicircular clamp; 3. Locking assembly; 31. First semicircular rubber pad; 32. Second semicircular rubber pad; 4. Locking bolt; 5. Fuselage skin; 6. Fuselage beam; 7. Hydrogen tank, 8. Fuselage. DETAILED DESCRIPTION

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

[0025] An embodiment of a hydrogen tank mounting structure for a hydrogen energy UAV with adjustable center of gravity is provided in the present invention. Figure 2 As shown, it includes: a body frame assembly, a clamp assembly and a locking pad assembly 3. The cross-section of the body frame assembly is C-shaped; the clamp assembly is connected to the body frame assembly to form a circular part, which is used to lock the outer ring of the hydrogen tank 7; the locking pad assembly 3 is arranged on the inner ring of the circular part formed by the body frame assembly and the clamp assembly.

[0026] Specifically, the fuselage frame assembly includes: two C-shaped fuselage frames 1 and a fuselage skin 5. The outer peripheral surfaces of the two C-shaped fuselage frames 1 are connected by fuselage beams 6 to form a skeleton; the fuselage skin 5 is covered on the outer surface of the skeleton.

[0027] Specifically, a weight-reducing hole 11 is opened on the axial surface of the C-shaped body frame 1 .

[0028] Specifically, the C-shaped body frame 1 includes: a semicircular member, each of whose two ends is connected to an arc segment, and the connecting end surface of the arc segment and the semicircular member forms a connecting step surface.

[0029] Specifically, the clamp assembly includes: a semicircular clamp 2, the outer peripheral surface of the end of which is provided with a connecting ear piece, and the connecting ear piece is connected to the connecting step surface of the semicircular part through a locking bolt 4.

[0030] Specifically, the locking pad assembly 3 includes: a first semicircular rubber pad 31 and a second semicircular rubber pad 32 . The first semicircular rubber pad 31 is arranged on the inner ring of the semicircular clamp 2 , and the second semicircular rubber pad 32 is arranged on the inner ring of the semicircular member.

[0031] It should be noted that, according to the overall center of gravity requirements of the drone, the locking bolt 4 is loosened to release the semicircular clamp 2 from locking the hydrogen tank 7, and then the position of the hydrogen tank 7 is adjusted to adjust the overall center of gravity of the drone.

[0032] This embodiment will be described with reference to the accompanying drawings:

[0033] Figure 1 This is a schematic diagram of the overall arrangement of hydrogen tanks in the fuselage of a hydrogen-powered UAV, with the hydrogen tank 7 placed in the middle section of the fuselage 8.

[0034] Figure 2 This is a state diagram of a hydrogen-powered UAV loaded with a hydrogen tank 7. The hydrogen tank 7 is placed on the inner ring of the C-shaped fuselage frame 1 inside the UAV. The C-shaped fuselage frame 1 is fixed to the fuselage skin 5 and the fuselage beam 6 by screwing / gluing to form an integral fuselage structure. This structural form and connection and fixing form are typical UAV fuselage structures, which can stably and efficiently withstand load conditions such as take-off and landing loads, aerodynamic loads, and concentrated equipment loads.

[0035] like Figure 3 and Figure 4 As shown, the hydrogen tank 7 is placed on the C-shaped fuselage frame 1 and the semicircular clamp 2 is connected to the C-shaped fuselage frame 1 through the locking bolt 4 on the semicircular clamp 2 to form a circular part. The outer peripheral surface of the circular arc segment of the C-shaped fuselage frame 1 is in contact with the fuselage skin 5. A locking pad assembly 3 is arranged between the inner ring of the circular part and the outer periphery of the hydrogen tank 7, including a first semicircular rubber pad 31 and a second semicircular rubber pad 32. The locking pad assembly 3 is a rubber pad with high friction and elastic properties. The pre-tightening force brought by tightening the locking bolt 4 compresses the first semicircular rubber pad 31 and the second semicircular rubber pad 32, thereby locking the hydrogen tank 7. The C-shaped fuselage frame 1, the semicircular clamp 2, the locking pad assembly 3 and the locking bolt 4 form at least two groups of fixed structures, such as Figure 5As shown, the circular space formed by the two groups of structures limits the radial freedom of the hydrogen tank 7. The friction between the locking pad assembly 3 and the hydrogen tank 7 limits the axial movement freedom and the axial rotation freedom of the hydrogen tank 7. At the same time, the load brought by the hydrogen tank 7 is transmitted to the main force transmission mechanism body beam 6 through the body frame 1. Figure 3 A lightening hole 11 is provided on the C-shaped body frame 1 to reduce the weight of the structure and at the same time serve as a channel for routing cables of the entire machine.

[0036] like Figure 5 As shown, when installing the hydrogen tank 7, first place the second semicircular rubber pad 32 on the C-shaped housing frame 1, then place the hydrogen tank 7 inside the second semicircular rubber pad 32, and finally place the first semicircular rubber pad 31 inside the semicircular clamp 2 and secure it. A gap is provided between the semicircular clamp 2 and the C-shaped housing frame 1 at the connection between the locking bolt 4. This gap provides space for tightening the bolt 4 to compress the first and second semicircular rubber pads 31, 32 of the locking pad assembly 3.

[0037] like Figure 6 As shown, the axial direction of the hydrogen tank 7 aligns with the UAV's heading. During flight testing, the UAV's heading center of gravity must be maintained within the design range. The UAV's heading center of gravity can be adjusted by axially shifting the hydrogen tank 7. The surface of the hydrogen tank 7 is smooth and free of protrusions. The tank 7 is secured primarily through the friction of the locking pad assembly 3. Axial movement of the tank 7 does not affect the secure locking mechanism, making it easy to operate and highly practical. The UAV's center of gravity can be quickly adjusted based on the desired center of gravity at the test site.

[0038] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV, characterized in that: include: The fuselage frame assembly has a C-shaped cross section; A clamp assembly connected to the body frame assembly to form a circular piece, the circular piece is used to lock the outer ring of the hydrogen tank (7); And a locking pad assembly (3) is arranged on the inner ring of the circular part formed by the body frame assembly and the clamp assembly.

2. The hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV according to claim 1 is characterized in that: The airframe components include: At least two C-shaped body frames (1), the outer peripheral surfaces of which are connected by body beams (6) to form a skeleton; and a body skin (5) which is arranged on the outer surface of the frame.

3. The hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV according to claim 2 is characterized in that: A weight-reducing hole (11) is provided on the axial surface of the C-shaped body frame (1).

4. The hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV according to claim 2 is characterized in that: The C-shaped machine body frame (1) comprises a semicircular member, the two ends of which are each connected to an arc segment, and the connecting end surface of the arc segment and the semicircular member forms a connecting step surface.

5. The hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV according to claim 4 is characterized in that: The clamp assembly comprises: a semicircular clamp (2), the outer peripheral surface of the end of which is provided with a connecting lug, and the connecting lug is connected to the connecting step surface of the semicircular part through a locking bolt (4).

6. The hydrogen tank mounting structure with adjustable center of gravity for a hydrogen-powered UAV according to claim 5 is characterized in that: The locking pad assembly (3) comprises a first semicircular rubber pad (31) and a second semicircular rubber pad (32), wherein the first semicircular rubber pad (31) is arranged on the inner ring of the semicircular clamp (2), and the second semicircular rubber pad (32) is arranged on the inner ring of the semicircular member.

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