An unmanned aerial vehicle fuel system test platform

Abstract

The present application relates to a kind of unmanned plane fuel system test platform, comprising: fixed frame, first rotating frame, second rotating frame, drive mechanism and oil delivery component, wherein, first rotating frame, it is set in the inner side of fixed frame, along the both ends of first axis line movably connected fixed frame, it can with first axis line as rotating shaft rotation;Second rotating frame, it is set in the inner side of first rotating frame, along the both ends of second axis line movably connected first rotating frame, for fixing equipment to be measured, it can with second axis line as rotating shaft rotation, and under the driving of first rotating frame with first axis line as rotating shaft rotation;The output end of drive mechanism movably connects first rotating frame and second rotating frame, for driving first rotating frame and second rotating frame rotation;Oil delivery component, it is set in the inside of first rotating frame and second rotating frame, for oil to equipment to be measured.This application can realize the simulation of the complex motion state of unmanned plane, satisfy the fuel consumption simulation of unmanned plane under a variety of flight attitudes.

Description

Technical Field

[0001] This invention belongs to the field of precision measurement and identification technology of industrial products, and specifically relates to a test platform for a drone fuel system. Background Technology

[0002] With the rapid development of the national economy, the research and production costs of drones have been continuously decreasing, leading to strong market demand. Drones have been widely used in agriculture, fire rescue, aerial photography, express delivery and logistics, and the military. In addition, drones have shown broad application prospects in film and entertainment, urban management, environmental monitoring, and distance education. Due to the widespread application of drones and the development and derivative of multiple drone models, accelerating the research and development process, reducing research and development costs, and ensuring successful development have become important tasks in the drone research and development phase.

[0003] Drones primarily use electricity or fuel as their power system. Fuel-powered drones have advantages such as better wind resistance and longer endurance, making fuel power the preferred power system for medium and large-sized drones. The fuel system of fuel-powered drones is a crucial component and has high design requirements, such as ensuring a continuous and uninterrupted supply of fuel to the engine and effectively cutting off the fuel supply.

[0004] Existing technology uses a three-degree-of-freedom (DOF) platform to mount a drone for fuel system testing. This platform typically consists of three servo electric cylinders, upper and lower platforms, and a universal hinge. Through the telescopic movement of the three servo electric cylinders, the upper platform can move linearly along the X, Y, and Z axes in space, achieving three degrees of freedom and simulating the drone's motion attitude. However, the roll and pitch angles simulated by the telescopic movement of the servo electric cylinders are small and cannot simulate the complex motion states of a drone. Summary of the Invention

[0005] To address the aforementioned problems in the existing technology, this invention provides a test platform for an unmanned aerial vehicle (UAV) fuel system. The technical problem to be solved by this invention is achieved through the following technical solution:

[0006] This invention provides a test platform for an unmanned aerial vehicle (UAV) fuel system, comprising: a fixed frame, a first rotating frame, a second rotating frame, a drive mechanism, and a fuel delivery assembly, wherein...

[0007] The first rotating frame is disposed inside the fixed frame and is movably connected to the fixed frame at both ends along the first axis, and can rotate about the first axis as the rotation axis;

[0008] The second rotating frame is disposed inside the first rotating frame and is movably connected to the first rotating frame at both ends along the second axis. It is used to fix the device under test and can rotate about the second axis as the rotation axis, and rotate about the first axis as the rotation axis under the drive of the first rotating frame; the first axis and the second axis are perpendicular to each other.

[0009] The output end of the drive mechanism is movably connected to the first rotating frame and the second rotating frame, and is used to drive the first rotating frame and the second rotating frame to rotate.

[0010] The oil delivery assembly is installed inside the first rotating frame and the second rotating frame, and is used to deliver oil to the device under test.

[0011] In one feasible embodiment, the fixing frame includes: a fixing frame, a first upright, a second upright, a first outer fixing ring, and a second outer fixing ring, wherein,

[0012] The first and second uprights are arranged opposite each other at both ends of the fixed frame along the first axis;

[0013] The first outer fixing ring and the second outer fixing ring are respectively disposed at the top of the first upright and the second upright.

[0014] In one feasible embodiment, the fixing frame further includes: a first reinforcing rod and a second reinforcing rod, wherein,

[0015] One end of the first reinforcing rod is fixedly connected to the fixed frame, and the other end is fixedly connected to the first upright.

[0016] One end of the second reinforcing rod is fixedly connected to the fixed frame, and the other end is fixedly connected to the second upright.

[0017] In one feasible embodiment, the first rotating frame includes: a first frame body, a first outer connecting ring, a second outer connecting ring, a first inner fixing ring, and a second inner fixing ring, wherein...

[0018] The first outer connecting ring and the second outer connecting ring are disposed opposite to each other at both ends of the first frame along the first axis, and the first outer connecting ring and the second outer connecting ring are movably connected to the fixed frame;

[0019] The first inner fixing ring and the second inner fixing ring are disposed opposite to each other at both ends of the first frame along the second axis.

[0020] In one feasible embodiment, the second rotating frame includes: a fixed plate, a first inner connecting ring, and a second inner connecting ring, wherein...

[0021] The fixing plate is used to fix the device under test;

[0022] The first inner connecting ring and the second inner connecting ring are disposed opposite each other at both ends of the fixed plate along the second axis, and both the first inner connecting ring and the second inner connecting ring are movably connected to the first rotating frame.

[0023] In one feasible manner, the first inner connecting ring is rotatably connected to the first inner fixing ring;

[0024] The second inner connecting ring is rotatably connected to the second inner fixing ring;

[0025] The first outer connecting ring is rotatably connected to the first outer fixing ring;

[0026] The second outer connecting ring is rotatably connected to the second outer fixing ring.

[0027] In one feasible embodiment, the inner walls of the first outer connecting ring, the second outer connecting ring, the first inner connecting ring, and the second inner connecting ring are all provided with internal teeth.

[0028] The outer end face of the first outer fixing ring, the outer end face of the second outer fixing ring, the outer end face of the first inner fixing ring, and the outer end face of the second inner fixing ring are all provided with outer end caps;

[0029] The inner end face of the first outer connecting ring, the inner end face of the second outer connecting ring, the inner end face of the first inner connecting ring, and the inner end face of the second inner connecting ring are all provided with inner end caps.

[0030] In one feasible implementation, the drive mechanism includes: a first drive component, a second drive component, a third drive component, and a fourth drive component, wherein,

[0031] The first drive component has a fixed end that is fixedly connected to the second outer fixing ring, and an output end that engages with the second outer connecting ring;

[0032] The second drive component has a fixed end that is fixedly connected to the second inner fixing ring, and an output end that engages with the second inner connecting ring;

[0033] The third drive component has a fixed end that is fixedly connected to the first inner fixed ring, and an output end that meshes with the first inner connecting ring.

[0034] The fourth drive component has a fixed end that is fixedly connected to the first outer fixing ring, and an output end that meshes with the first outer connecting ring.

[0035] In one feasible embodiment, the oil delivery assembly includes: a first oil delivery pipe, a second oil delivery pipe, a first oil delivery rotary head, and a second oil delivery rotary head, wherein...

[0036] The first oil delivery rotary head is located at the center of the first outer connecting ring, with its fixed end fixedly connected to the first outer fixed ring and its rotating end fixedly connected to the first outer connecting ring. It has a first channel and a second channel inside.

[0037] The second oil delivery rotary head is located at the center of the second inner connecting ring. The fixed end is fixedly connected to the second inner fixed ring, and the rotating end is fixedly connected to the second inner connecting ring. It has a third channel and a fourth channel inside.

[0038] The first oil pipeline connects the first channel and the third channel, and is used to deliver fuel to the device under test;

[0039] The second oil pipeline connects the second channel and the fourth channel, and is used to discharge fuel from the device under test.

[0040] In one feasible approach, a conductive slip ring and a cable are also included, wherein...

[0041] The conductive slip ring is disposed at the center of the second outer connecting ring, with its fixed end fixedly connected to the second outer fixed ring and its rotating end fixedly connected to the second outer connecting ring;

[0042] The cable electrically connects the conductive slip ring and the drive mechanism.

[0043] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0044] The UAV fuel system test platform of the present invention uses a first rotating frame to rotate around a first axis, which drives the device under test on a second rotating frame to rotate around the first axis, simulating the pitch motion of the UAV. The second rotating frame rotates around a second axis to simulate the roll motion of the UAV, thereby simulating the complex motion state of the UAV and satisfying the fuel consumption simulation of the UAV under various flight attitudes. Attached Figure Description

[0045] Figure 1 This is a schematic diagram of the structure of a test platform for an unmanned aerial vehicle (UAV) fuel system provided in an embodiment of the present invention;

[0046] Figure 2 This is a schematic diagram of the structure of the fixing frame provided in an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of the structure of the first rotating frame provided in an embodiment of the present invention;

[0048] Figure 4 This is a schematic diagram of the structure of the second rotating frame provided in an embodiment of the present invention;

[0049] Figure 5This is a top view of a test platform for an unmanned aerial vehicle (UAV) fuel system provided in an embodiment of the present invention;

[0050] Figure 6 This is a schematic diagram showing the connection between the fixed frame, the first rotating frame, and the second rotating frame provided in an embodiment of the present invention;

[0051] Figure 7 This is a schematic diagram of the internal structure of the first outer fixing ring and the first outer connecting ring provided in an embodiment of the present invention.

[0052] Figure label:

[0053] 1: Fixed frame; 11: Fixed frame body; 12: First upright frame; 13: Second upright frame; 14: First outer fixing ring; 15: Second outer fixing ring; 16: First reinforcing rod; 17: Second reinforcing rod; 2: First rotating frame; 21: First frame body; 22: First outer connecting ring; 23: Second outer connecting ring; 24: First inner fixing ring; 25: Second inner fixing ring; 3: Second rotating frame; 31: Fixed plate; 32: First inner connecting ring; 33: Second inner connecting ring; 4: Drive mechanism; 41: First drive assembly; 42: Second drive assembly; 43: Third drive assembly; 44: Fourth drive assembly; 441: Drive motor; 442: Gear; 5: Oil delivery assembly; 51: First oil delivery pipeline; 52: Second oil delivery pipeline; 53: First oil delivery rotating head; 54: Second oil delivery rotating head; 6: Conductive slip ring; 7: Cable. Detailed Implementation

[0054] The present invention will be further described in detail below with reference to specific embodiments, but the implementation of the present invention is not limited thereto.

[0055] Example 1

[0056] Please see Figure 1 , Figure 1 This is a schematic diagram of the structure of a test platform for an unmanned aerial vehicle (UAV) fuel system provided in an embodiment of the present invention.

[0057] This embodiment provides a test platform for a drone fuel system, comprising: a fixed frame 1, a first rotating frame 2, a second rotating frame 3, a drive mechanism 4, and a fuel delivery assembly 5. The first rotating frame 2 is disposed inside the fixed frame 1, and its two ends are movably connected to the fixed frame 1 along a first axis, allowing it to rotate about the first axis. The second rotating frame 3 is disposed inside the first rotating frame 2, and its two ends are movably connected to the first rotating frame 2 along a second axis. It is used to fix the device under test and can rotate about the second axis, and rotates about the first axis under the drive of the first rotating frame 2. The first and second axes are perpendicular to each other. The output end of the drive mechanism 4 is movably connected to the first rotating frame 2 and the second rotating frame 3, driving their rotation. The fuel delivery assembly 5 passes through the interiors of the first rotating frame 2 and the second rotating frame 3, and is used to deliver fuel to the device under test.

[0058] Specifically, the first axis and the second axis are two mutually perpendicular axes of the first rotating frame 2. The first rotating frame 2 can rotate 360° about the first axis, and the second rotating frame 3 can rotate 360° about the second axis. The device under test is fixed on the second rotating frame 3 and fuel is supplied through the fuel supply assembly 5. The rotation of the first rotating frame 2 about the first axis drives the device under test on the second rotating frame 3 to rotate about the first axis, simulating the pitch motion of the UAV. The rotation of the second rotating frame 3 about the second axis simulates the roll motion of the UAV, thus simulating the complex motion states of the UAV and meeting the fuel consumption simulation requirements of the UAV under various flight attitudes.

[0059] Specifically, please see Figure 2 The fixing frame 1 includes: a fixing frame 11, a first upright 12, a second upright 13, a first outer fixing ring 14, a second outer fixing ring 15, a first reinforcing rod 16, and a second reinforcing rod 17. The first upright 12 and the second upright 13 are positioned opposite each other at both ends of the fixing frame 11 along a first axis. The first outer fixing ring 14 and the second outer fixing ring 15 are respectively positioned at the top ends of the first upright 12 and the second upright 13. One end of the first reinforcing rod 16 is fixedly connected to the fixing frame 11, and the other end of the first reinforcing rod 16 is fixedly connected to the first upright 12. One end of the second reinforcing rod 17 is fixedly connected to the fixing frame 11, and the other end of the second reinforcing rod 17 is fixedly connected to the second upright 13.

[0060] Specifically, please see Figure 3The first rotating frame 2 includes: a first frame body 21, a first outer connecting ring 22, a second outer connecting ring 23, a first inner fixing ring 24, and a second inner fixing ring 25. The first outer connecting ring 22 and the second outer connecting ring 23 are positioned opposite each other at both ends of the first frame body 21 along a first axis, and are movably connected to the fixed frame 1. The first inner fixing ring 24 and the second inner fixing ring 25 are positioned opposite each other at both ends of the first frame body 21 along a second axis.

[0061] Specifically, please see Figure 4 The second rotating frame 3 includes a fixed plate 31, a first inner connecting ring 32, and a second inner connecting ring 33. The fixed plate 31 is used to fix the device under test. The first inner connecting ring 32 and the second inner connecting ring 33 are disposed opposite each other at both ends of the fixed plate 31 along a second axis, and both the first inner connecting ring 32 and the second inner connecting ring 33 are movably connected to the first rotating frame 2.

[0062] Specifically, please combine Figure 5 and Figure 6 The first inner connecting ring 32 is rotatably connected to the first inner fixing ring 24. The second inner connecting ring 33 is rotatably connected to the second inner fixing ring 25. The first outer connecting ring 22 is rotatably connected to the first outer fixing ring 14. The second outer connecting ring 23 is rotatably connected to the second outer fixing ring 15.

[0063] In this embodiment, the inner walls of the first outer connecting ring 22, the second outer connecting ring 23, the first inner connecting ring 32, and the second inner connecting ring 33 are all provided with internal teeth. The outer end faces of the first outer fixing ring 14, the second outer fixing ring 15, the first inner fixing ring 24, and the second inner fixing ring 25 are all provided with outer end caps. The inner end faces of the first outer connecting ring 22, the second outer connecting ring 23, the first inner connecting ring 32, and the second inner connecting ring 33 are all provided with inner end caps. It should be understood that the outer end faces of the first outer fixing ring 14, the second outer fixing ring 15, the first inner fixing ring 24, and the second inner fixing ring 25 are end faces away from the center of the UAV fuel system test platform, while the inner end faces of the first outer connecting ring 22, the second outer connecting ring 23, the first inner connecting ring 32, and the second inner connecting ring 33 are end faces facing the center of the UAV fuel system test platform.

[0064] In this embodiment, the drive mechanism 4 includes a first drive assembly 41, a second drive assembly 42, a third drive assembly 43, and a fourth drive assembly 44. The fixed end of the first drive assembly 41 is fixedly connected to a second outer fixing ring 15, and the output end of the first drive assembly 41 engages with a second outer connecting ring 23. The fixed end of the second drive assembly 42 is fixedly connected to a second inner fixing ring 25, and the output end of the second drive assembly 42 engages with a second inner connecting ring 33. The fixed end of the third drive assembly 43 is fixedly connected to a first inner fixing ring 24, and the output end of the third drive assembly 43 engages with a first inner connecting ring 32. The fixed end of the fourth drive assembly 44 is fixedly connected to a first outer fixing ring 14, and the output end of the fourth drive assembly 44 engages with a first outer connecting ring 22.

[0065] In this embodiment, the first outer fixing ring 14, the second outer fixing ring 15, the first inner fixing ring 24, and the second inner fixing ring 25 have the same structure; the first outer connecting ring 22, the second outer connecting ring 23, the first inner connecting ring 32, and the second inner connecting ring 33 have the same structure; and the first drive assembly 41, the second drive assembly 42, the third drive assembly 43, and the fourth drive assembly 44 have the same structure, all including a servo motor and gears. The connection methods between each drive assembly, fixing ring, and connecting ring are also the same. The first outer fixing ring 14, the first outer connecting ring 22, and the fourth drive assembly 44 will be used as examples for explanation. Please refer to [link to relevant documentation]. Figure 7 The fourth drive assembly 44 includes a drive motor 441 and a gear 442. The first outer fixed ring 14 is the fixed end, and the first outer connecting ring 22 is the rotating end. The first outer fixed ring 14 and the first outer connecting ring 22 are connected to form a slewing bearing. The outer wall of the first outer connecting ring 22 is rotatably connected to the inner wall of the first outer fixed ring 14 via ball bearings. The drive motor 441 is eccentrically positioned within the first outer fixed ring 14. The housing of the drive motor 441 is fixedly connected to the first outer fixed ring 14 via a flange. The output shaft of the drive motor 441 is fixedly connected to the gear 442. The gear 442 meshes with the internal teeth of the first outer connecting ring 22. The drive motor 441 drives the gear 442 to rotate, and the gear 442 transmits power to the first outer connecting ring 22, causing the first outer connecting ring 22 to rotate relative to the first outer fixed ring 14. The first outer connecting ring 22 and the second outer connecting ring 23 rotate synchronously, thus enabling the first rotating frame 2 to rotate around a first axis. It should be understood that the first axis is the axis connecting the centers of the first outer connecting ring 22 and the second outer connecting ring 23. The first inner connecting ring 32 and the second inner connecting ring 33 rotate synchronously, so that the second rotating frame 3 can rotate around the second axis.

[0066] In this embodiment, the fuel delivery assembly 5 includes: a first fuel delivery pipe 51, a second fuel delivery pipe 52, a first fuel delivery rotary head 53, and a second fuel delivery rotary head 54. The first fuel delivery rotary head 53 is located at the center of a first outer connecting ring 22. The fixed end of the first fuel delivery rotary head 53 is fixedly connected to a first outer fixing ring 14, and the rotating end of the first fuel delivery rotary head 53 is fixedly connected to the first outer connecting ring 22. The interior of the first fuel delivery rotary head 53 has a first channel and a second channel. The second fuel delivery rotary head 54 is located at the center of a second inner connecting ring 33. The fixed end of the second fuel delivery rotary head 54 is fixedly connected to a second inner fixing ring 25, and the rotating end of the second fuel delivery rotary head 54 is fixedly connected to the second inner connecting ring 33. The interior of the second fuel delivery rotary head 54 has a third channel and a fourth channel. The first fuel delivery pipe 51 connects the first channel and the third channel and is used to deliver fuel to the device under test. The second fuel delivery pipe 52 connects the second channel and the fourth channel and is used to discharge fuel from the device under test.

[0067] Specifically, please combine Figure 5 , Figure 6 and Figure 7 The first oil delivery rotary head 53 and the second oil delivery rotary head 54 have the same structure and connection method. Taking the first oil delivery rotary head 53 as an example, the fixed end of the first oil delivery rotary head 53 is fixedly connected to the fixed flange of the drive motor 441, and the rotating end of the first oil delivery rotary head 53 is fixedly connected to the outer end cover of the first outer connecting ring 22. When the first outer connecting ring 22 rotates, the rotating end of the first oil delivery rotary head 53 rotates synchronously with the first outer connecting ring 22. The two ends of the first channel and the second channel are located on the side of the fixed end of the first oil delivery rotary head 53 and the end face of the rotating end of the first oil delivery rotary head 53. The first oil delivery pipe 51 is connected to the external oil delivery station, the first channel, and the third channel in sequence, and finally connected to the device under test. The second oil delivery rotary head 54 is connected to the external oil delivery station, the second channel, and the fourth channel in sequence, and finally connected to the device under test. Under the action of the first oil delivery rotary head 53 and the second oil delivery rotary head 54, when the first rotating frame 2 and the second rotating frame 3 are rotating, the first oil delivery pipe 51 and the second oil delivery pipe 52 can still continuously deliver oil to the device under test. The portions of the first oil delivery pipe 51 and the second oil delivery pipe 52 located between the first oil delivery rotary head 53 and the second oil delivery rotary head 54 are inserted inside the first frame 21. In this embodiment, both the first oil delivery pipe 51 and the second oil delivery pipe 52 are flexible hoses, and the first oil delivery rotary head 53 and the second oil delivery rotary head 54 have a diameter of 25 mm, a pressure resistance of 2 MPa, and a maximum rotational speed of 0.4 m / s.

[0068] In this embodiment, the UAV fuel system test platform also includes a conductive slip ring 6 and a cable 7. The conductive slip ring 6 is located at the center of the second outer connecting ring 23. The fixed end of the conductive slip ring 6 is fixedly connected to the second outer fixed ring 15, and the rotating end of the conductive slip ring 6 is fixedly connected to the second outer connecting ring 23. The cable 7 electrically connects the conductive slip ring 6 and the drive mechanism 4.

[0069] Specifically, the conductive slip ring 6 is used to transmit power and signals when the first rotating frame 2 and the second rotating frame 3 rotate, preventing the cables 7 from tangling during rotation. In this embodiment, since the fourth drive assembly 44 and the first drive assembly 41 are located at the top of the first support 12 and the second support 13 respectively, the fourth drive assembly 44 is directly electrically connected to the cable 7 fixed on the first support 12, and the first drive assembly 41 is directly electrically connected to the cable 7 fixed on the second support 13. The cable 7 fixed on the second support 13 is connected to the input end of the conductive slip ring 6, and the output end of the conductive slip ring 6 is electrically connected to the second drive assembly 42 and the third drive assembly 43. Furthermore, the conductive slip ring 6 also has two independent gas channels inside. Correspondingly, a conductive slip ring 6 is also provided at the center of the first inner connecting ring 32. The gas pipes are connected to the device under test through the conductive slip ring 6 at the center of the second outer connecting ring 23 and the conductive slip ring 6 at the center of the first inner connecting ring 32, forming an engine bleed air boosting simulation system.

[0070] In this embodiment, angle sensors are installed on the first and second axes to collect the angles of movement of the first rotating frame 2 and the second rotating frame 3 in real time and send them to the operation panel. When testing the device under test, the pitch and roll angles are set, and the programmable logic controller (PLC) controls the second drive assembly 42 and the third drive assembly 43 to operate synchronously, and the first drive assembly 41 and the fourth drive assembly 44 to operate synchronously, so as to ensure the stability of the rotation of the first rotating frame 2 and the second rotating frame 3.

[0071] This embodiment provides a test platform for a drone fuel system. A first rotating frame 2 rotates about a first axis, causing the device under test (DUT) on a second rotating frame 3 to rotate about the first axis, simulating the drone's pitch motion. The second rotating frame 3 rotates about a second axis, simulating the drone's roll motion, thus simulating complex drone motion states and meeting the fuel consumption simulation requirements for drones in various flight attitudes. This drone fuel system test platform has high load-bearing capacity and a wide range of adaptability, meeting the principle verification requirements of existing medium-sized drone fuel systems. It can continuously perform pitch and roll motions and provide uninterrupted fuel supply during both pitch and roll movements.

[0072] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

Claims

1. A test platform for an unmanned aerial vehicle (UAV) fuel system, characterized in that, include: The components include a fixed frame (1), a first rotating frame (2), a second rotating frame (3), a drive mechanism (4), and an oil delivery assembly (5), wherein... The first rotating frame (2) is disposed inside the fixed frame (1) and is movably connected to the fixed frame (1) at both ends along the first axis, and can rotate about the first axis as the rotation axis; The second rotating frame (3) is disposed inside the first rotating frame (2) and is movably connected to the first rotating frame (2) at both ends along the second axis. It is used to fix the device under test and can rotate about the second axis as the rotation axis. Under the drive of the first rotating frame (2), it rotates about the first axis as the rotation axis. The first axis and the second axis are perpendicular to each other. The output end of the drive mechanism (4) is movably connected to the first rotating frame (2) and the second rotating frame (3) for driving the first rotating frame (2) and the second rotating frame (3) to rotate; The oil delivery assembly (5) is installed inside the first rotating frame (2) and the second rotating frame (3) and is used to deliver oil to the device under test. The fixing frame (1) includes: a fixing frame (11), a first upright (12), a second upright (13), a first outer fixing ring (14), and a second outer fixing ring (15), wherein, The first upright (12) and the second upright (13) are arranged opposite each other at both ends of the fixed frame (11) along the first axis; The first outer fixing ring (14) and the second outer fixing ring (15) are respectively disposed at the top of the first upright (12) and the second upright (13). The first rotating frame (2) includes: a first frame body (21), a first outer connecting ring (22), a second outer connecting ring (23), a first inner fixing ring (24), and a second inner fixing ring (25), wherein, The first outer connecting ring (22) and the second outer connecting ring (23) are disposed opposite to each other at both ends of the first frame (21) along the first axis, and the first outer connecting ring (22) and the second outer connecting ring (23) are movably connected to the fixed frame (1); The first inner fixing ring (24) and the second inner fixing ring (25) are disposed opposite to each other at both ends of the first frame (21) along the second axis. The second rotating frame (3) includes: a fixed plate (31), a first inner connecting ring (32), and a second inner connecting ring (33), wherein, The fixing plate (31) is used to fix the device under test; The first inner connecting ring (32) and the second inner connecting ring (33) are disposed opposite each other at both ends of the fixed plate (31) along the second axis, and both the first inner connecting ring (32) and the second inner connecting ring (33) are movably connected to the first rotating frame (2). The inner walls of the first outer connecting ring (22), the second outer connecting ring (23), the first inner connecting ring (32), and the second inner connecting ring (33) are all provided with internal teeth; The outer end face of the first outer fixing ring (14), the outer end face of the second outer fixing ring (15), the outer end face of the first inner fixing ring (24), and the outer end face of the second inner fixing ring (25) are all provided with outer end caps; The inner end face of the first outer connecting ring (22), the inner end face of the second outer connecting ring (23), the inner end face of the first inner connecting ring (32), and the inner end face of the second inner connecting ring (33) are all provided with inner end caps.

2. The unmanned aerial vehicle (UAV) fuel system test platform according to claim 1, characterized in that, The fixing frame (1) further includes: a first reinforcing rod (16) and a second reinforcing rod (17), wherein, One end of the first reinforcing rod (16) is fixedly connected to the fixed frame (11), and the other end is fixedly connected to the first upright (12); One end of the second reinforcing rod (17) is fixedly connected to the fixed frame (11), and the other end is fixedly connected to the second upright (13).

3. The unmanned aerial vehicle (UAV) fuel system test platform according to claim 2, characterized in that, The first inner connecting ring (32) is rotatably connected to the first inner fixing ring (24); The second inner connecting ring (33) is rotatably connected to the second inner fixing ring (25); The first outer connecting ring (22) is rotatably connected to the first outer fixing ring (14); The second outer connecting ring (23) is rotatably connected to the second outer fixing ring (15).

4. The unmanned aerial vehicle (UAV) fuel system test platform according to claim 3, characterized in that, The driving mechanism (4) includes: a first driving component (41), a second driving component (42), a third driving component (43), and a fourth driving component (44), wherein, The first drive component (41) has a fixed end that is fixedly connected to the second outer fixing ring (15), and an output end that meshes with the second outer connecting ring (23); The second drive assembly (42) has a fixed end that is fixedly connected to the second inner fixing ring (25), and an output end that engages with the second inner connecting ring (33); The third drive component (43) has a fixed end that is fixedly connected to the first inner fixing ring (24), and an output end that meshes with the first inner connecting ring (32); The fourth drive component (44) has its fixed end fixedly connected to the first outer fixing ring (14), and its output end engaged with the first outer connecting ring (22).

5. The unmanned aerial vehicle (UAV) fuel system test platform according to claim 4, characterized in that, The oil delivery assembly (5) includes: a first oil delivery pipe (51), a second oil delivery pipe (52), a first oil delivery rotary head (53), and a second oil delivery rotary head (54), wherein, The first oil delivery rotary head (53) is located at the center of the first outer connecting ring (22), with the fixed end fixedly connected to the first outer fixed ring (14) and the rotating end fixedly connected to the first outer connecting ring (22). It has a first channel and a second channel inside. The second oil delivery rotary head (54) is located at the center of the second inner connecting ring (33), with the fixed end fixedly connected to the second inner fixed ring (25) and the rotating end fixedly connected to the second inner connecting ring (33). It has a third channel and a fourth channel inside. The first oil pipeline (51) connects the first channel and the third channel and is used to deliver fuel to the device under test; The second oil pipeline (52) connects the second channel and the fourth channel and is used to discharge fuel from the device under test.

6. The unmanned aerial vehicle (UAV) fuel system test platform according to claim 5, characterized in that, It also includes a conductive slip ring (6) and a cable (7), wherein, The conductive slip ring (6) is located at the center of the second outer connecting ring (23), with its fixed end fixedly connected to the second outer fixed ring (15) and its rotating end fixedly connected to the second outer connecting ring (23); The cable (7) is electrically connected to the conductive slip ring (6) and the drive mechanism (4).

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