Unmanned aerial vehicle fuel system test platform

Abstract

The invention relates to an unmanned aerial vehicle fuel oil system test platform, which comprises a fixed frame, a first rotating frame, a second rotating frame, a driving mechanism and an oil transportation assembly, and is characterized in that the first rotating frame is arranged at the inner side of the fixed frame, is movably connected with the fixed frame along two ends of a first axis, and can rotate by taking the first axis as a rotating shaft; the second rotating frame is arranged on the inner side of the first rotating frame, is movably connected with the first rotating frame along two ends of a second axis, is used for fixing equipment to be tested, can rotate by taking the second axis as a rotating shaft, and is driven by the first rotating frame to rotate by taking the first axis as a rotating shaft; the output end of the driving mechanism is movably connected with the first rotating frame and the second rotating frame and used for driving the first rotating frame and the second rotating frame to rotate. And the oil conveying assembly is arranged in the first rotating frame and the second rotating frame in a penetrating manner and is used for conveying oil to the to-be-tested equipment. According to the invention, the complex motion state of the unmanned aerial vehicle can be simulated, and the oil consumption simulation of the unmanned aerial vehicle under various flight attitudes is satisfied.

Description

Technical Field

[0001] The invention belongs to the technical field of precision measurement and identification of industrial products, and in particular relates to a fuel system test platform for unmanned aerial vehicles. Background Art

[0002] With the rapid development of the national economy, the cost of developing and producing drones has been continuously reduced, and the market demand is strong. Drones have been widely used in agriculture, fire rescue, aerial photography, express logistics and military fields. In addition, drones have also shown broad application prospects in many fields such as film and television entertainment, urban management, environmental testing, and distance education. Due to the widespread application of drones and the development and derivation of multiple models of drones, how to speed up the development progress, reduce the development funds, and ensure the success of development have become important tasks in the development stage of drones.

[0003] UAVs mainly use electricity or fuel as their power systems. Fuel-powered UAVs have advantages such as good wind resistance and long flight time, making fuel power the preferred power system for medium and large UAVs. As an important part of the UAV, the fuel system of fuel-powered UAVs has high design requirements, such as ensuring continuous and uninterrupted fuel supply to the engine and being able to effectively cut off the fuel supply.

[0004] The existing technology uses a three-degree-of-freedom platform to carry out fuel system inspection on a drone. The three-degree-of-freedom platform is usually composed of three servo electric cylinders, two 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-degree-of-freedom movement and simulating the motion posture of the drone. However, the roll and pitch angles simulated by the telescopic movement of the servo electric cylinder are small and cannot simulate the complex motion state of the drone. Summary of the invention

[0005] In order to solve the above problems existing in the prior art, the present invention provides a UAV fuel system test platform. The technical problem to be solved by the present invention is achieved through the following technical solutions:

[0006] The present invention provides a UAV fuel system test platform, comprising: a fixed frame, a first rotating frame, a second rotating frame, a driving mechanism and an oil delivery component, wherein:

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

[0008] The second rotating frame is arranged on the inner side of the first rotating frame, and is movably connected to the first rotating frame along two ends of the second axis, and is used to fix the device under test, and can rotate with the second axis as the rotation axis, and can rotate with 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 driving 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 component is arranged inside the first rotating frame and the second rotating frame, and is used to deliver oil to the device to be tested.

[0011] In an achievable manner, the fixing frame includes: a fixing frame, a first stand, a second stand, a first outer fixing ring and a second outer fixing ring, wherein:

[0012] The first stand and the second stand are arranged oppositely at two ends of the fixed frame along the first axis;

[0013] The first outer fixing ring and the second outer fixing ring are respectively arranged on the top ends of the first stand and the second stand.

[0014] In an achievable manner, 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 stand;

[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 stand.

[0017] In an achievable manner, 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 arranged oppositely at two 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 fixing frame;

[0019] The first inner fixing ring and the second inner fixing ring are arranged oppositely at two ends of the first frame along the second axis.

[0020] In an achievable manner, the second rotating frame comprises: a fixing 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 arranged oppositely at two ends of the fixing plate along the second axis, and the first inner connecting ring and the second inner connecting ring are both movably connected to the first rotating frame.

[0023] In one achievable 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 an achievable manner, the inner wall of the first outer connecting ring, the inner wall of the second outer connecting ring, the inner wall of the first inner connecting ring, and the inner wall of the second inner connecting ring are all provided with inner teeth;

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

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

[0030] In one achievable manner, the driving mechanism comprises: a first driving assembly, a second driving assembly, a third driving assembly and a fourth driving assembly, wherein:

[0031] The first driving assembly has a fixed end fixedly connected to the second outer fixing ring, and an output end meshing with the second outer connecting ring;

[0032] The second driving assembly has a fixed end fixedly connected to the second inner fixed ring, and an output end meshing with the second inner connecting ring;

[0033] The third driving assembly has a fixed end fixedly connected to the first inner fixed ring, and an output end meshing with the first inner connecting ring;

[0034] The fourth driving assembly has a fixed end fixedly connected to the first outer fixing ring, and an output end meshing with the first outer connecting ring.

[0035] In an achievable manner, the oil delivery assembly comprises: a first oil delivery pipeline, a second oil delivery pipeline, a first oil delivery rotating head and a second oil delivery rotating head, wherein:

[0036] The first oil transfer rotating head is arranged at the center of the first outer connecting ring, the fixed end is fixedly connected to the first outer fixed ring, the rotating end is fixedly connected to the first outer connecting ring, and the first channel and the second channel are formed inside;

[0037] The second oil delivery rotating head is arranged at the center of the second inner connecting ring, the fixed end is fixedly connected to the second inner fixed ring, the rotating end is fixedly connected to the second inner connecting ring, and the third channel and the fourth channel are provided inside;

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

[0039] The second oil pipeline is connected to the second channel and the fourth channel, and is used for discharging the fuel in the device to be tested.

[0040] In one achievable manner, it further includes a conductive slip ring and a cable, wherein:

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

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

[0043] Compared with the prior art, the present invention has the following beneficial effects:

[0044] The UAV fuel system test platform of the present invention drives the equipment to be tested on the second rotating frame to rotate with the first axis as the rotation axis by the first rotating frame rotating with the first axis as the rotation axis, thereby simulating the pitch motion of the UAV; the second rotating frame rotates with the second axis as the rotation axis, thereby simulating the rolling 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 postures. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a structural schematic diagram of a UAV fuel system test platform provided by an embodiment of the present invention;

[0046] Figure 2 is a schematic structural diagram of a fixing frame provided by an embodiment of the present invention;

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

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

[0049] Figure 5is a top view of a UAV fuel system test platform provided by an embodiment of the present invention;

[0050] Figure 6 is a schematic diagram of 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 It 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] Reference numerals:

[0053] 1: fixed frame; 11: fixed frame; 12: first vertical frame; 13: second vertical frame; 14: first outer fixed ring; 15: second outer fixed ring; 16: first reinforcing rod; 17: second reinforcing rod; 2: first rotating frame; 21: first frame; 22: first outer connecting ring; 23: second outer connecting ring; 24: first inner fixed ring; 25: second inner fixed ring; 3: second rotating frame; 31: fixed plate; 32: first inner connecting ring; 33: second inner connecting ring; 4: driving mechanism; 41: first driving assembly; 42: second driving assembly; 43: third driving assembly; 44: fourth driving assembly; 441: driving 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 DESCRIPTION

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

[0055] Embodiment 1

[0056] See also Figure 1 , Figure 1 It is a structural schematic diagram of a UAV fuel system test platform provided by an embodiment of the present invention.

[0057] The present embodiment provides a test platform for the fuel system of an unmanned aerial vehicle, comprising: a fixed frame 1, a first rotating frame 2, a second rotating frame 3, a driving mechanism 4 and an oil delivery assembly 5. The first rotating frame 2 is arranged on the inner side of the fixed frame 1, and the first rotating frame 2 is movably connected to the fixed frame 1 at both ends along the first axis, and can rotate with the first axis as the rotation axis. The second rotating frame 3 is arranged on the inner side of the first rotating frame 2, and the second rotating frame 3 is movably connected to the first rotating frame 2 at both ends along the second axis, and is used to fix the device to be tested, and can rotate with the second axis as the rotation axis, and rotate with the first axis as the rotation axis under the drive of the first rotating frame 2. The first axis and the second axis are perpendicular to each other. The output end of the driving mechanism 4 is movably connected to the first rotating frame 2 and the second rotating frame 3, and is used to drive the first rotating frame 2 and the second rotating frame 3 to rotate. The oil delivery assembly 5 is arranged inside the first rotating frame 2 and the second rotating frame 3, and is used to deliver oil to the device to be tested.

[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° with the first axis as the rotation axis, and the second rotating frame 3 can rotate 360° with the second axis as the rotation axis. The device to be tested is fixed on the second rotating frame 3, and fuel is input through the oil delivery component 5. The first rotating frame 2 rotates with the first axis as the rotation axis, driving the device to be tested on the second rotating frame 3 to rotate with the first axis as the rotation axis, simulating the pitch motion of the drone. The second rotating frame 3 rotates with the second axis as the rotation axis, simulating the rolling motion of the drone, realizing the simulation of the complex motion state of the drone, and meeting the fuel consumption simulation of the drone under various flight postures.

[0059] Specifically, see Figure 2 The fixed frame 1 includes: a fixed frame 11, a first frame 12, a second frame 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 frame 12 and the second frame 13 are relatively arranged at two 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 arranged at the top of the first frame 12 and the second frame 13. One end of the first reinforcing rod 16 is fixedly connected to the fixed frame 11, and the other end of the first reinforcing rod 16 is fixedly connected to the first frame 12. One end of the second reinforcing rod 17 is fixedly connected to the fixed frame 11, and the other end of the second reinforcing rod 17 is fixedly connected to the second frame 13.

[0060] Specifically, 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 relatively arranged at two ends of the first frame body 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 relatively arranged at two ends of the first frame body 21 along the second axis.

[0061] Specifically, see Figure 4 The second rotating frame 3 includes: a fixing plate 31, a first inner connecting ring 32 and a second inner connecting ring 33. 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 relatively arranged at two ends of the fixing plate 31 along the second axis, and the first inner connecting ring 32 and the second inner connecting ring 33 are both 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 wall of the first outer connecting ring 22, the inner wall of the second outer connecting ring 23, the inner wall of the first inner connecting ring 32, and the inner wall of the second inner connecting ring 33 are all provided with inner teeth. The outer end surface of the first outer fixing ring 14, the outer end surface of the second outer fixing ring 15, the outer end surface of the first inner fixing ring 24, and the outer end surface of the second inner fixing ring 25 are all provided with outer end covers. The inner end surface of the first outer connecting ring 22, the inner end surface of the second outer connecting ring 23, the inner end surface of the first inner connecting ring 32, and the inner end surface of the second inner connecting ring 33 are all provided with inner end covers. It should be understood that 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 end faces away from the center of the UAV fuel system test platform, and 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 end faces facing the center of the UAV fuel system test platform.

[0064] In this embodiment, the driving mechanism 4 includes: a first driving assembly 41, a second driving assembly 42, a third driving assembly 43 and a fourth driving assembly 44. Among them, the fixed end of the first driving assembly 41 is fixedly connected to the second outer fixing ring 15, and the output end of the first driving assembly 41 is meshed with the second outer connecting ring 23. The fixed end of the second driving assembly 42 is fixedly connected to the second inner fixing ring 25, and the output end of the second driving assembly 42 is meshed with the second inner connecting ring 33. The fixed end of the third driving assembly 43 is fixedly connected to the first inner fixing ring 24, and the output end of the third driving assembly 43 is meshed with the first inner connecting ring 32. The fixed end of the fourth driving assembly 44 is fixedly connected to the first outer fixing ring 14, and the output end of the fourth driving assembly 44 is meshed with the 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, the first driving assembly 41, the second driving assembly 42, the third driving assembly 43 and the fourth driving assembly 44 have the same structure, and all include servo motors and gears. The connection method between each driving assembly, fixing ring and connecting ring is also the same. The first outer fixing ring 14, the first outer connecting ring 22 and the fourth driving assembly 44 are used as examples for explanation, see Figure 7 The fourth driving assembly 44 includes a driving motor 441 and a gear 442. The first outer fixing ring 14 is a fixed end, and the first outer connecting ring 22 is a rotating end. The first outer fixing 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 fixing ring 14 through a ball. The driving motor 441 is eccentrically arranged in the first outer fixing ring 14. The outer shell of the driving motor 441 and the first outer fixing ring 14 are fixedly connected through a flange. The output shaft of the driving motor 441 is fixedly connected to the gear 442. The gear 442 and the inner teeth of the first outer connecting ring 22 are meshed. The driving motor 441 drives the gear 442 to rotate, and the gear 442 and the first outer connecting ring 22 are driven, so that the first outer connecting ring 22 rotates relative to the first outer fixing ring 14. The first outer connecting ring 22 and the second outer connecting ring 23 rotate synchronously, so that the first rotating frame 2 can be rotated with the first axis as the rotating 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 oil delivery assembly 5 includes: a first oil delivery pipeline 51, a second oil delivery pipeline 52, a first oil delivery rotating head 53 and a second oil delivery rotating head 54. The first oil delivery rotating head 53 is arranged at the center of the first outer connecting ring 22, the fixed end of the first oil delivery rotating head 53 is fixedly connected to the first outer fixed ring 14, the rotating end of the first oil delivery rotating head 53 is fixedly connected to the first outer connecting ring 22, and the first oil delivery rotating head 53 has a first channel and a second channel inside. The second oil delivery rotating head 54 is arranged at the center of the second inner connecting ring 33, the fixed end of the second oil delivery rotating head 54 is fixedly connected to the second inner fixed ring 25, the rotating end of the second oil delivery rotating head 54 is fixedly connected to the second inner connecting ring 33, and the second oil delivery rotating head 54 has a third channel and a fourth channel inside. The first oil delivery pipeline 51 connects the first channel and the third channel, and the first oil delivery pipeline 51 is used to deliver fuel to the device to be tested. The second oil delivery pipeline 52 connects the second channel and the fourth channel, and the second oil delivery pipeline 52 is used to discharge the fuel in the device to be tested.

[0067] Specifically, please combine Figure 5 , Figure 6 and Figure 7 The first oil delivery rotating head 53 and the second oil delivery rotating head 54 have the same structure and connection mode. The first oil delivery rotating head 53 is used as an example for explanation. The fixed end of the first oil delivery rotating head 53 is fixedly connected to the fixed flange of the driving motor 441, and the rotating end of the first oil delivery rotating 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 rotating head 53 rotates synchronously with the first outer connecting ring 22. The first channel and the second channel are located at the side of the fixed end of the first oil delivery rotating head 53 and the end face of the rotating end of the first oil delivery rotating head 53. The first oil delivery pipeline 51 is connected to the external oil delivery station, the first channel, and the third channel in sequence, and finally connected to the device to be tested. The second oil delivery rotating 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 to be tested. Under the action of the first oil delivery rotating head 53 and the second oil delivery rotating head 54, when the first rotating frame 2 and the second rotating frame 3 rotate, the first oil delivery pipeline 51 and the second oil delivery pipeline 52 can still continuously deliver oil to the device to be tested. The first oil pipeline 51 and the second oil pipeline 52 are located between the first oil rotating head 53 and the second oil rotating head 54 and are arranged inside the first frame 21. In this embodiment, the first oil pipeline 51 and the second oil pipeline 52 are both hoses, and the first oil rotating head 53 and the second oil rotating head 54 have a diameter of 25 mm, a pressure resistance of 2 MPa, and a maximum rotation speed of 0.4 m / s.

[0068] In this embodiment, the UAV fuel system test platform further includes a conductive slip ring 6 and a cable 7. The conductive slip ring 6 is arranged 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 fixing 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 driving mechanism 4.

[0069] Specifically, the conductive slip ring 6 is used to realize power transmission and signal transmission when the first rotating frame 2 and the second rotating frame 3 rotate, so as to avoid the cable 7 from being entangled when the first rotating frame 2 and the second rotating frame 3 rotate. In this embodiment, since the fourth drive assembly 44 and the first drive assembly 41 are respectively located at the top of the first stand 12 and the second stand 13, the fourth drive assembly 44 is directly electrically connected to the cable 7 fixed on the first stand 12, and the first drive assembly 41 is directly electrically connected to the cable 7 fixed on the second stand 13, and the cable 7 fixed on the second stand 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, and accordingly, a conductive slip ring 6 is also provided at the center of the first inner connecting ring 32, and the gas pipeline is connected to the device to be tested 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 in sequence, forming an engine bleed air boost simulation system.

[0070] In this embodiment, angle sensors are provided on the first axis and the second axis to collect the angles 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 to be tested, 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 move synchronously, and the first drive assembly 41 and the fourth drive assembly 44 to move synchronously to ensure the stability of the rotation of the first rotating frame 2 and the second rotating frame 3.

[0071] This embodiment provides a UAV fuel system test platform, which drives the equipment to be tested on the second rotating frame 3 to rotate with the first axis as the rotation axis by rotating the first rotating frame 2 with the first axis as the rotation axis, simulating the pitch motion of the UAV, and the second rotating frame 3 rotates with the second axis as the rotation axis to simulate the roll motion of the UAV, so as to simulate the complex motion state of the UAV and meet the fuel consumption simulation of the UAV under various flight postures. The large maneuverable test bench of the UAV fuel system test platform has a high load capacity and a wide range of adaptability, which can meet the principle verification of the existing medium-sized UAV fuel system, can continuously perform pitch and roll motions, and can continuously supply oil during pitch and roll motions.

[0072] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A UAV fuel system test platform, characterized in that: include: A fixed frame (1), a first rotating frame (2), a second rotating frame (3), a driving mechanism (4) and an oil delivery assembly (5), wherein: The first rotating frame (2) is arranged on the inner side of the fixed frame (1), is movably connected to the fixed frame (1) along both ends of the first axis, and can rotate with the first axis as the rotation axis; The second rotating frame (3) is arranged on the inner side of the first rotating frame (2), and is movably connected to the first rotating frame (2) along two ends of the second axis, and is used to fix the device to be tested, and can rotate with the second axis as the rotation axis, and can rotate with the first axis as the rotation axis under the drive of the first rotating frame (2); the first axis and the second axis are perpendicular to each other; The output end of the driving mechanism (4) is movably connected to the first rotating frame (2) and the second rotating frame (3), and is used to drive the first rotating frame (2) and the second rotating frame (3) to rotate; The oil delivery component (5) is arranged inside the first rotating frame (2) and the second rotating frame (3) and is used to deliver oil to the device to be tested.

2. The UAV fuel system test platform according to claim 1, characterized in that: The fixing frame (1) comprises: a fixing frame (11), a first vertical frame (12), a second vertical frame (13), a first outer fixing ring (14) and a second outer fixing ring (15), wherein: The first stand (12) and the second stand (13) are arranged oppositely at two ends of the fixed frame (11) along a first axis; The first outer fixing ring (14) and the second outer fixing ring (15) are respectively arranged at the top ends of the first stand (12) and the second stand (13).

3. The UAV fuel system test platform according to claim 2, characterized in that: The fixing frame (1) further comprises: 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 stand (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 stand (13).

4. The UAV fuel system test platform according to claim 2, characterized in that: The first rotating frame (2) comprises: 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 arranged oppositely at two ends of the first frame body (21) along the first axis, and the first outer connecting ring (22) and the second outer connecting ring (23) are movably connected to the fixing frame (1); The first inner fixing ring (24) and the second inner fixing ring (25) are arranged opposite to each other at two ends of the first frame (21) along the second axis.

5. The UAV fuel system test platform according to claim 4, characterized in that: The second rotating frame (3) comprises: a fixing 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 to be tested; The first inner connecting ring (32) and the second inner connecting ring (33) are arranged oppositely at two ends of the fixing plate (31) along the second axis, and the first inner connecting ring (32) and the second inner connecting ring (33) are both movably connected to the first rotating frame (2).

6. The UAV fuel system test platform according to claim 5, 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).

7. The UAV fuel system test platform according to claim 5, characterized in that: The inner wall of the first outer connecting ring (22), the inner wall of the second outer connecting ring (23), the inner wall of the first inner connecting ring (32) and the inner wall of the second inner connecting ring (33) are all provided with inner teeth; The outer end surface of the first outer fixing ring (14), the outer end surface of the second outer fixing ring (15), the outer end surface of the first inner fixing ring (24) and the outer end surface of the second inner fixing ring (25) are all provided with outer end covers; The inner end surface of the first outer connecting ring (22), the inner end surface of the second outer connecting ring (23), the inner end surface of the first inner connecting ring (32) and the inner end surface of the second inner connecting ring (33) are all provided with inner end covers.

8. The UAV fuel system test platform according to claim 5, characterized in that: The driving mechanism (4) comprises: a first driving assembly (41), a second driving assembly (42), a third driving assembly (43) and a fourth driving assembly (44), wherein: The first driving component (41) has a fixed end fixedly connected to the second outer fixing ring (15), and an output end meshing with the second outer connecting ring (23); The second driving component (42) has a fixed end fixedly connected to the second inner fixed ring (25), and an output end meshing with the second inner connecting ring (33); The third driving component (43) has a fixed end fixedly connected to the first inner fixed ring (24), and an output end meshing with the first inner connecting ring (32); The fourth driving assembly (44) has a fixed end fixedly connected to the first outer fixing ring (14), and an output end meshing with the first outer connecting ring (22).

9. The UAV fuel system test platform according to claim 5, characterized in that: The oil delivery assembly (5) comprises: a first oil delivery pipeline (51), a second oil delivery pipeline (52), a first oil delivery rotating head (53) and a second oil delivery rotating head (54), wherein: The first oil transfer rotating head (53) is arranged at the center of the first outer connecting ring (22), the fixed end is fixedly connected to the first outer fixed ring (14), the rotating end is fixedly connected to the first outer connecting ring (22), and has a first channel and a second channel inside; The second oil transfer rotating head (54) is arranged at the center of the second inner connecting ring (33), the fixed end is fixedly connected to the second inner fixed ring (25), the rotating end is fixedly connected to the second inner connecting ring (33), and has a third channel and a fourth channel inside; The first oil delivery pipeline (51) is connected to the first channel and the third channel, and is used to deliver fuel to the device to be tested; The second oil delivery pipeline (52) is connected to the second channel and the fourth channel and is used to discharge the fuel in the device to be tested.

10. The 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 arranged at the center of the second outer connecting ring (23), the fixed end is fixedly connected to the second outer fixing ring (15), and the rotating end is fixedly connected to the second outer connecting ring (23); The cable (7) electrically connects the conductive slip ring (6) and the driving mechanism (4).

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