Angle adjusting support for posture adaptation of hydrogen power battery of unmanned aerial vehicle

Abstract

The utility model relates to hydrogen power battery support technical field discloses the angle adjusting support of unmanned aerial vehicle hydrogen power battery attitude adaptation, including main frame, the inside of main frame is provided with inner frame, the inside of inner frame is provided with installation platform, the top of installation platform is provided with the limiting mechanism, the limiting mechanism is used for the limiting fixed of battery, the top of main frame is provided with connecting mechanism, and connecting mechanism is used for quick with unmanned aerial vehicle body installation positioning, the limiting mechanism includes limit rod, and the bottom of limit rod and the top of installation platform are connected with the sliding, the pawl and the ratchet bar form self -locking along the guide groove sliding of limit rod, prevent limit rod reverse movement, the extension length of fine adjustment compression disc is prevented, ensures that battery is fixed, and the contact of buffer pad no.

Description

Technical Field

[0001] This utility model relates to the field of hydrogen power battery bracket technology, and in particular to an angle adjustment bracket for adapting the attitude of a drone's hydrogen power battery. Background Technology

[0002] The hydrogen-powered battery for drones achieves electrochemical conversion of hydrogen and oxygen through a fuel cell stack, directly converting the chemical energy of hydrogen into electrical energy to power the drone. It can support long-endurance drone operations, and the only byproduct is water with no carbon emissions. It also has the advantage of rapid recharging, making it suitable for the needs of high-frequency and long-cycle drone operations.

[0003] During flight, drones may accelerate, turn, and dive, causing the center of gravity of the hydrogen fuel cell to shift and the electrolyte to become unevenly distributed, resulting in a decrease in power generation efficiency. Inertial forces can also cause the battery to loosen and fall off. The angle adjustment bracket can dynamically adjust the battery angle according to the flight attitude, so that the battery always maintains the optimal working posture, which can meet the power stability and safety requirements in complex flight scenarios.

[0004] Early hydrogen-powered drones used rigid fixed brackets as support structures. These rigid brackets only provided installation and load-bearing functions and could not cope with the negative effects of attitude changes. To solve this problem, existing technologies use active adjustment brackets. By sensing the pitch and roll attitude angles of the drone in real time, the algorithm calculates the compensation angle based on the data, causing the bracket platform carrying the hydrogen battery to rotate in the opposite direction by a corresponding angle, thereby dynamically offsetting the changes in the drone's attitude. However, in actual use, because the load-bearing tray and the battery are directly fastened with screws, the adjustment bracket vibrates due to inertia during high-frequency fine-tuning or rapid directional adjustments. Over time, this causes the fixing screws to loosen, leading to battery loosening, affecting connection stability, and failing to meet the user's needs. Utility Model Content

[0005] To overcome the above shortcomings, this utility model provides an angle adjustment bracket for the attitude adaptation of the hydrogen-powered battery of a drone, which aims to improve the problem that the connection method of direct screw fastening in the prior art will loosen under long-term vibration, resulting in the battery becoming loose.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: an angle adjustment bracket for the attitude adaptation of a hydrogen-powered battery for a drone, including a main frame, an inner frame inside the main frame, an installation platform inside the inner frame, a limiting mechanism at the top of the installation platform for limiting and fixing the battery, and a connecting mechanism at the top of the main frame for installation and positioning with the drone's fuselage.

[0007] The limiting mechanism includes a limiting rod, the bottom of which is slidably connected to the top of the mounting platform. Pawls are rotatably connected to the left ends of both the front and rear sides of the limiting rod. A spring is fixedly connected to the right end of each adjacent side of the two pawls. The adjacent sides of each spring are fixedly connected to the front and rear sides of the limiting rod, respectively. Ratchets are fixedly connected to the front and rear sides of the top of the mounting platform. The two pawls engage with their corresponding ratchet racks. Sliding blocks are slidably connected to the front and rear sides of the top of the limiting rod. Bolts are threaded to the right ends of the two sliding blocks. A clamping plate is fixedly connected to the left end of the corresponding sliding block. A buffer assembly is provided on the right side of the limiting plate.

[0008] As a further description of the above technical solution:

[0009] The connecting mechanism includes two T-shaped blocks. The bottoms of the two T-shaped blocks are fixedly connected to the front and rear sides of the top of the main frame, respectively. Connecting frames are fixedly connected to the front and rear ends of the bottom right side of the main frame. Positioning rods are slidably connected to the inner sides of the two connecting frames. Limiting plates are fixedly connected to the middle of the outer walls of the two positioning rods. Springs are provided in the lower middle part of the outer walls of the two positioning rods. The bottoms of the two springs are fixedly connected to the bottom inner side of the corresponding connecting frames, and the tops of the two springs are fixedly connected to the bottom of the corresponding limiting plates.

[0010] As a further description of the above technical solution:

[0011] The buffer assembly includes a buffer pad one, the left side of which is fixedly connected to the right side of the limiting plate, and buffer pad two is fixedly connected to the left ends of both pressing plates.

[0012] As a further description of the above technical solution:

[0013] A rolling shaft is rotatably connected to the bottom inner side of the main frame. A connecting block is fixedly connected to the left and right sides of the outer wall of the rolling shaft. The top of the two connecting blocks is fixedly connected to the bottom of the inner frame. A servo motor is fixedly connected to the bottom right side of the outer wall of the main frame. The output end of the servo motor passes through the right side of the main frame and is fixedly connected to the right end of the rolling shaft.

[0014] As a further description of the above technical solution:

[0015] The inner bottom of the inner frame is rotatably connected to a pitch axis. The front and rear sides of the outer wall of the pitch axis are fixedly connected to connecting blocks two. The tops of the two connecting blocks two are fixedly connected to the bottom of the mounting platform. The front side of the outer wall of the inner frame is fixedly connected to a servo motor two. The output end of the servo motor two passes through the front side of the inner frame and is fixedly connected to the front end of the pitch axis.

[0016] As a further description of the above technical solution:

[0017] The top of the installation platform is provided with a guide groove, and the bottom of the limiting rod is slidably connected to the inner wall of the guide groove.

[0018] As a further description of the above technical solution:

[0019] A mounting bracket is fixedly connected to the left side of the main frame. A hydrogen cylinder is installed inside the mounting bracket. Fixing straps are fixedly connected to the front and rear sides of the top of the mounting bracket. The other ends of the two fixing straps are fixedly connected to female buckles. Female buckles are fixedly connected to the front and rear sides of the top of the left end of the mounting bracket.

[0020] As a further description of the above technical solution:

[0021] A cover plate is provided on the upper right side of the main frame. Hinges are fixedly connected to the top right side and the front and back sides of the cover plate. The cover plate is rotatably connected to the main frame through the hinges. Locks are fixedly connected to the middle right side and the front and back sides of the main frame.

[0022] This utility model has the following beneficial effects:

[0023] 1. In this utility model, the battery is placed on the mounting platform, with the left side of the battery pressed against the first buffer pad. The limiting rod slides along the guide groove, causing the clamping plate and the second buffer pad to move closer to the right side of the battery. The pawl and the ratchet form a self-locking mechanism to prevent the limiting rod from moving in the opposite direction. Tightening the bolt causes the clamping plate to move. The extension length of the clamping plate is finely adjusted to control the clamping force on the battery, ensuring that the battery is fixed. The first and second buffer pads can absorb and buffer vibrations through contact with the battery, preventing the battery from loosening.

[0024] 2. In this utility model, the two T-shaped blocks at the top of the main frame are aligned and embedded into the T-shaped sliding grooves pre-set in the fuselage of the drone to complete the initial horizontal positioning. The positioning rod in the connecting frame is springed upward into the corresponding pin hole at the bottom of the fuselage under the action of the pre-tightening force of the spring, thereby realizing the vertical positioning and locking, and realizing the rapid installation of the main frame and the fuselage. Attached Figure Description

[0025] Figure 1 A perspective view of the angle adjustment bracket for the attitude adaptation of the hydrogen-powered battery of the UAV proposed in this utility model;

[0026] Figure 2 This is a front view of the angle adjustment bracket for adapting the attitude of a drone's hydrogen-powered battery, as proposed in this utility model.

[0027] Figure 3This is a cross-sectional view of the main frame structure of the angle adjustment bracket for adapting the attitude of a drone's hydrogen-powered battery, as proposed in this utility model.

[0028] Figure 4 This is a cross-sectional view of the inner frame structure of the angle adjustment bracket for adapting the attitude of a drone's hydrogen-powered battery, as proposed in this utility model.

[0029] Figure 5 This is a partial structural diagram of the angle adjustment bracket for the attitude adaptation of the hydrogen-powered battery of the UAV proposed in this utility model.

[0030] Legend:

[0031] 1. Main frame; 2. Limiting mechanism; 201. Limiting rod; 202. Pawl; 203. Spring 1; 204. Ratchet; 205. Sliding block; 206. Bolt; 207. Pressure plate; 208. Limiting plate; 209. Buffer assembly; 2091. Buffer pad 1; 2092. Buffer pad 2; 3. Connecting mechanism; 301. T-block; 302. Connecting frame; 303. Positioning rod; 304. Limiting piece; 305. Spring 2; 4. Inner frame; 5. Mounting platform; 6. Rolling shaft; 7. Connecting block 1; 8. Servo motor 1; 9. Pitch axis; 10. Connecting block 2; 11. Servo motor 2; 12. Guide groove; 13. Mounting bracket; 14. Hydrogen cylinder; 15. Fixing strap; 16. Female buckle; 17. Female buckle; 18. Cover plate; 19. Hinge; 20. Lock. Detailed Implementation

[0032] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0033] Reference Figure 3 , Figure 4 and Figure 5 An embodiment of this utility model provides an angle adjustment bracket for the attitude adaptation of a hydrogen-powered battery for a drone, including a main frame 1, an inner frame 4 inside the main frame 1, the inner frame 4 for transmitting roll attitude compensation force, an installation platform 5 inside the inner frame 4 for supporting the battery, a limiting mechanism 2 at the top of the installation platform 5 for limiting and fixing the battery, and a connecting mechanism 3 at the top of the main frame 1 for installation and positioning with the drone's fuselage.

[0034] The limiting mechanism 2 includes a limiting rod 201. The bottom of the limiting rod 201 is slidably connected to the top of the mounting platform 5. The limiting rod 201 is used to drive the clamping plate 207 closer to the battery to achieve initial clamping. Pads 202 are rotatably connected to the left ends of the front and rear sides of the limiting rod 201. The pads 202 mesh with the ratchet rack 204 to form a one-way self-locking structure to prevent the limiting rod 201 from moving in the opposite direction after clamping the battery. Springs 203 are fixedly connected to the right ends of adjacent sides of the two pads 202. Springs 203 provide preload to the pads 202 to ensure that the pads 202 are always tightly meshed with the ratchet rack 204. The adjacent sides of the two springs 203 are fixedly connected to the front and rear sides of the limiting rod 201, respectively. The ratchet rack 204 is fixedly connected to the front and rear sides of the top of the mounting platform 5. The ratchet rack 204 achieves self-locking positioning of the limiting rod 201 at different positions through a toothed structure. Each pawl 202 engages with a corresponding ratchet rack 204. Sliding blocks 205 are slidably connected to the front and rear sides of the top of the limiting rod 201. The sliding blocks 205 are used to install bolts 206 and adjust the lateral position of the clamping plate 207 to accommodate batteries of different widths. Bolts 206 are threaded to the right ends of both sliding blocks 205. Bolts 206 are used to finely adjust the extension length of the clamping plate 207 via threaded transmission, controlling the battery clamping force. The left ends of both bolts 206 pass through the right side of the corresponding sliding block 205 and are fixedly connected to the clamping plate 207. The clamping plate 207 transmits the preload of the bolts 206 to the battery, achieving precise clamping. A limiting plate 208 is fixedly connected to the top left end of the mounting platform 5. The limiting plate 208 restricts the left side position of the battery, forming a bidirectional positioning with the clamping plate 207. A buffer assembly 209 is provided on the right side of the limiting plate 208.

[0035] The buffer assembly 209 includes a buffer pad 2091, which is used to contact the left side of the battery to absorb vibration energy and prevent the battery from rigidly colliding with the limiting plate 208. The left side of the buffer pad 2091 is fixedly connected to the right side of the limiting plate 208. The left ends of the two clamping plates 207 are each fixedly connected to a buffer pad 2092, which is used to contact the right side of the battery. Together with the buffer pad 2091, they achieve bidirectional vibration buffering and prevent the battery from loosening due to long-term vibration.

[0036] The top of the mounting platform 5 is provided with a guide groove 12, which is used to provide a sliding track for the bottom of the limiting rod 201, ensuring that the limiting rod 201 moves smoothly along a straight line. The bottom of the limiting rod 201 is slidably connected to the inner wall of the guide groove 12.

[0037] Specifically, during battery installation, the battery should be placed on the installation platform 5, ensuring that the left side of the battery is tightly against the buffer pad 2091 on the right side of the limiting plate 208. Then, the limiting rod 201 is pushed to the right, causing it to slide along the guide groove 12. This, in turn, moves the clamping plate 207 and the second buffer pad 2092 closer to the right side of the battery. When the limiting rod 201 moves to the right and clamps the battery, the pawl 202 slides over the teeth of the ratchet rack 204 and, under the elastic force of the spring 203, engages with the groove of the ratchet rack 204. A self-locking structure is formed to prevent the limit rod 201 from moving in the opposite direction. When the bolt 206 is tightened, the bolt 206 will move left and right by means of the thread engagement with the sliding block 205, thereby driving the clamping plate 207 to move left and right. By rotating the bolt 206, the extension length of the clamping plate 207 can be finely adjusted, thereby controlling the clamping force on the battery and ensuring that the battery is firmly fixed. The buffer pad 1 2091 and buffer pad 2092 can absorb and buffer vibration by contacting the battery, preventing the battery from becoming loose.

[0038] Reference Figure 1 , Figure 2 and Figure 3 The connecting mechanism 3 includes two T-blocks 301, which cooperate with the T-shaped slide grooves of the machine body to achieve rapid horizontal guiding and positioning of the main frame 1. The bottoms of the two T-blocks 301 are fixedly connected to the front and rear sides of the top of the main frame 1, respectively. Connecting brackets 302 are fixedly connected to the front and rear ends of the bottom right side of the main frame 1. The connecting brackets 302 are used to install positioning rods 303 and springs 305. The inner sides of the two connecting brackets 302 are slidably connected to the positioning rods 303. The positioning rods 303 are used to insert into the pin holes of the machine body under the action of springs 305 to achieve vertical positioning and locking of the main frame 1. Limiting pieces 304 are fixedly connected to the middle of the outer wall of the two positioning rods 303 to limit the maximum extension of the positioning rods 303. Springs 305 are provided in the lower middle part of the outer wall of the two positioning rods 303 to provide upward preload for the positioning rods 303. To ensure that the positioning rod 303 fits tightly with the pin hole of the machine body, the bottom of the two springs 305 are fixedly connected to the bottom of the inner side of the corresponding connecting frame 302, and the top of the two springs 305 are fixedly connected to the bottom of the corresponding limiting piece 304. The left side of the main frame 1 is fixedly connected to the mounting frame 13, which is used to support the hydrogen cylinder 14 and provide a stable installation space for the hydrogen cylinder 14. The hydrogen cylinder 14 is set inside the mounting frame 13. The top front and rear sides of the mounting frame 13 are fixedly connected to the fixing straps 15. The fixing straps 15 are used to wrap around the hydrogen cylinder 14 and cooperate with the female buckle 17 through the male buckle 16 to realize the quick binding and fixing of the hydrogen cylinder 14. The other end of the two fixing straps 15 is fixedly connected to the male buckle 16. The top front and rear sides of the left end of the mounting frame 13 are fixedly connected to the female buckle 17. The male buckle 16 and the female buckle 17 are used to quickly fasten and lock the fixing straps 15, so as to realize the convenient disassembly and assembly of the hydrogen cylinder 14.

[0039] Specifically, when installing the main frame 1 on the bottom of the fuselage, the two T-shaped blocks 301 on the top of the main frame 1 need to be aligned and embedded into the T-shaped slide grooves pre-set in the fuselage. As the main frame 1 moves along the slide groove, the initial horizontal positioning is completed, thereby limiting the horizontal displacement of the main frame 1. When the main frame 1 slides to the predetermined position, the positioning rod 303 in the connecting frame 302 springs upward into the corresponding pin hole at the bottom of the fuselage under the pre-tightening force of the second spring 305, thereby achieving vertical positioning and locking. When disassembling, the two positioning rods 303 need to be pulled down at the same time. The positioning rods 303 squeeze the second spring 305 through the limiting piece 304, overcome the elastic force of the second spring 305 and move downward, thereby disengaging from the positioning hole. Then the main frame 1 slides in the opposite direction to achieve rapid separation of the main frame 1 from the fuselage. The hydrogen cylinder 14 installed on the left side of the main frame 1 is quickly fixed by the cooperation of the fixing strap 15, the male buckle 16 and the female buckle 17.

[0040] Reference Figure 1 , Figure 3 and Figure 4A roll shaft 6 is rotatably connected to the bottom inner side of the main frame 1. The roll shaft 6 transmits power from the servo motor 8 and drives the inner frame 4 to rotate around the roll shaft 6 via connecting block 7. Connecting blocks 7 are fixedly connected to the left and right sides of the outer wall of the roll shaft 6. Connecting blocks 7 convert the rotational motion of the roll shaft 6 into the roll adjustment of the inner frame 4. The tops of both connecting blocks 7 are fixedly connected to the bottom of the inner frame 4. A servo motor 8 is fixedly connected to the bottom right side of the outer wall of the main frame 1. The servo motor 8 provides the power source for roll attitude adjustment and drives the roll shaft 6 to rotate. The output end of the servo motor 8 passes through the right side of the main frame 1 and is fixedly connected to the right end of the roll shaft 6. A pitch shaft 9 is rotatably connected to the bottom inner side of the inner frame 4. The pitch shaft 9 transmits power from the servo motor 11 and drives the mounting platform 5 to rotate around the pitch shaft 9 via connecting block 10. Connecting blocks 10 are fixedly connected to the front and rear sides of the outer wall of the pitch shaft 9. 10 is used to convert the rotational motion of the pitch axis 9 into the pitch adjustment of the mounting platform 5. The tops of the two connecting blocks 10 are fixedly connected to the bottom of the mounting platform 5. A servo motor 11 is fixedly connected to the front side of the outer wall of the inner frame 4. The servo motor 11 is used to provide the power source for pitch attitude adjustment and drive the pitch axis 9 to rotate. The output end of the servo motor 11 passes through the front side of the inner frame 4 and is fixedly connected to the front end of the pitch axis 9. A cover plate 18 is provided on the upper right side of the main frame 1. The cover plate 18 is used to cover the opening on the right side of the main frame 1, which serves to protect the internal servo motor and transmission components and provide a convenient maintenance channel. Hinges 19 are fixedly connected to the front and rear sides of the top right end of the cover plate 18. The hinges 19 are used to realize the rotational connection between the cover plate 18 and the main frame 1. The cover plate 18 is rotatably connected to the main frame 1 through the hinges 19. Locks 20 are fixedly connected to the front and rear sides of the middle right end of the main frame 1. The locks 20 are used to lock the cover plate 18 after it is closed.

[0041] Specifically, when the UAV performs pitch and roll maneuvers, it uses sensors to detect changes in the pitch and roll angles of the aircraft in real time. After calculation, it sends commands to servo motor 8 and servo motor 11. After receiving the signal, servo motor 8 drives the roll shaft 6 to rotate through its output shaft. The roll shaft 6 drives the inner frame 4 and all internal components to rotate around the roll shaft 6 through connecting block 7, compensating for changes in the UAV's roll attitude. At the same time, servo motor 11 drives the pitch shaft 9 to rotate, which drives the mounting platform 5 and battery load to rotate around the pitch shaft 9 through connecting block 10, thereby compensating for the pitch attitude and keeping the battery at a suitable working angle. When servo motor 8 and servo motor 11 start, stop, and quickly reverse, they will generate inertial impact and high-frequency vibration. The cover plate 18 on the right side of the main frame 1, connected by hinge 19 and latch 20, provides a convenient maintenance channel for easy inspection and maintenance of the internal servo motors and transmission components.

[0042] Working principle: When installing the battery, place the battery on the installation platform 5, with the left side of the battery pressed against the buffer pad 2091 on the right side of the limiting plate 208. Then, push the limiting rod 201 to the right to slide along the guide groove 12, causing the pressing plate 207 and the second buffer pad 2092 to move closer to the right side of the battery. When the limiting rod 201 moves to the right to press the battery, the pawl 202 slides over the tooth surface of the ratchet rack 204. Under the elastic force of the spring 203, the pawl 202 will be engaged in the tooth groove of the ratchet rack 204. This forms a self-locking mechanism to prevent the limit rod 201 from moving in the opposite direction. When the bolt 206 is tightened, the bolt 206 will move left and right through the thread engagement with the sliding block 205. The bolt 206 can then drive the clamping plate 207 to move left and right. By rotating the bolt 206, the extension length of the clamping plate 207 can be finely adjusted to control the clamping force on the battery and ensure that the battery is firmly fixed. The buffer pad 1 2091 and buffer pad 2092 can absorb and buffer vibration through contact with the battery to prevent the battery from loosening.

[0043] Furthermore, when installing the main frame 1 at the bottom of the fuselage, the two T-shaped blocks 301 at the top of the main frame 1 are aligned and embedded into the T-shaped slide grooves pre-set in the fuselage. As the main frame 1 moves along the slide groove, the initial horizontal positioning is completed, limiting the horizontal displacement of the main frame 1. When the main frame 1 slides to the predetermined position, the positioning rod 303 in the connecting frame 302 springs upward into the corresponding pin hole at the bottom of the fuselage under the pre-tightening force of the second spring 305, realizing vertical positioning and locking. During disassembly, by simultaneously pulling down the two positioning rods 303, the positioning rods 303 squeeze the second spring 305 through the limiting piece 304, overcome the elastic force of the second spring 305, move downward to disengage from the positioning hole, and then slide the main frame 1 in the opposite direction to achieve rapid separation of the main frame 1 from the fuselage.

[0044] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. An angle adjustment bracket for attitude adaptation of a hydrogen-powered UAV battery, comprising a main frame (1), characterized in that: The main frame (1) is provided with an inner frame (4), and the inner frame (4) is provided with an installation platform (5). The top of the installation platform (5) is provided with a limiting mechanism (2), which is used to limit and fix the battery. The top of the main frame (1) is provided with a connecting mechanism (3), which is used to install and position the drone with the drone body. The limiting mechanism (2) includes a limiting rod (201), the bottom of which is slidably connected to the top of the mounting platform (5). Pawls (202) are rotatably connected to the left ends of both the front and rear sides of the limiting rod (201). Springs (203) are fixedly connected to the right ends of adjacent sides of the two pawls (202). The adjacent sides of the two springs (203) are respectively fixedly connected to the front and rear sides of the limiting rod (201). Ratchets (204) are fixedly connected to the front and rear sides of the top of the mounting platform (5). The claws (202) are respectively engaged with the corresponding ratchet racks (204). The top front and rear sides of the limiting rod (201) are slidably connected with sliding blocks (205). The right ends of the two sliding blocks (205) are threaded with bolts (206). The left ends of the two bolts (206) pass through the right side of the corresponding sliding block (205) and are fixedly connected with a pressure plate (207). The top left end of the mounting platform (5) is fixedly connected with a limiting plate (208). The right side of the limiting plate (208) is provided with a buffer assembly (209).

2. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: The connecting mechanism (3) includes two T-shaped blocks (301). The bottoms of the two T-shaped blocks (301) are fixedly connected to the front and rear sides of the top of the main frame (1), respectively. The front and rear ends of the bottom right side of the main frame (1) are fixedly connected to connecting brackets (302). The inner sides of the two connecting brackets (302) are slidably connected to positioning rods (303). The middle of the outer wall of the two positioning rods (303) is fixedly connected to limiting pieces (304). The lower middle part of the outer wall of the two positioning rods (303) is provided with springs (305). The bottoms of the two springs (305) are fixedly connected to the bottom inner side of the corresponding connecting brackets (302), respectively. The tops of the two springs (305) are fixedly connected to the bottom of the corresponding limiting pieces (304).

3. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: The buffer assembly (209) includes a buffer pad one (2091), the left side of which is fixedly connected to the right side of the limiting plate (208), and the left ends of the two pressing plates (207) are each fixedly connected to a buffer pad two (2092).

4. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: The inner bottom of the main frame (1) is rotatably connected to a rolling shaft (6). The outer walls of the rolling shaft (6) are fixedly connected to the left and right sides of the outer walls of the rolling shaft (6). The tops of the two connecting blocks (7) are fixedly connected to the bottom of the inner frame (4). The outer bottom of the main frame (1) is fixedly connected to a servo motor (8). The output end of the servo motor (8) passes through the right side of the main frame (1) and is fixedly connected to the right end of the rolling shaft (6).

5. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: The inner bottom of the inner frame (4) is rotatably connected to a pitch axis (9). The front and rear sides of the outer wall of the pitch axis (9) are fixedly connected to connecting blocks two (10). The tops of the two connecting blocks two (10) are fixedly connected to the bottom of the mounting platform (5). The front side of the outer wall of the inner frame (4) is fixedly connected to a servo motor two (11). The output end of the servo motor two (11) passes through the front side of the inner frame (4) and is fixedly connected to the front end of the pitch axis (9).

6. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: The top of the installation platform (5) is provided with a guide groove (12), and the bottom of the limiting rod (201) is slidably connected to the inner wall of the guide groove (12).

7. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: A mounting bracket (13) is fixedly connected to the left side of the main frame (1). A hydrogen cylinder (14) is provided on the inner side of the mounting bracket (13). Fixing straps (15) are fixedly connected to the front and back sides of the top of the mounting bracket (13). A female buckle (16) is fixedly connected to the other end of each of the two fixing straps (15). A female buckle (17) is fixedly connected to the front and back sides of the top of the left end of the mounting bracket (13).

8. The angle adjustment bracket for drone hydrogen-powered battery attitude adaptation according to claim 1, characterized in that: A cover plate (18) is provided on the upper right side of the main frame (1). A hinge (19) is fixedly connected to the front and back sides of the top right end of the cover plate (18). The cover plate (18) is rotatably connected to the main frame (1) through the hinge (19). A latch (20) is fixedly connected to the front and back sides of the middle right end of the main frame (1).

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