Simulation test rotary table and simulation test method for unmanned aerial vehicle fuel system

Abstract

The application provides a simulation test rotating table and a simulation test method for a UAV fuel system. The adjusting unit of the rotating table comprises an adjusting assembly, an adapter seat assembly and a rotating frame assembly. In the adjusting assembly, the adjusting nut is fixed to the support of the support unit, the screw rod moves up and down relative to the nut, the rotating adjusting part drives the screw rod to rotate, and the first locking nut is used for locking the screw rod. In the adapter seat assembly, the screw rod can rotate relative to the adapter seat, and the second bearing is installed to the adapter seat via the pin shaft so that the threaded shaft thereof can rotate around the pin shaft. In the rotating frame assembly, the rotating shaft is screwed to the threaded shaft of the second bearing at one end, the crossbar of the rotating frame is rotatably connected to the other end of the rotating shaft, the locking part is used for locking the crossbar and the rotating shaft, and the two legs of the rotating frame are connected to the chuck assembly on both sides of the chuck assembly in parallel with the axis of the chuck assembly to drive the chuck assembly and the test piece to move. The application realizes the simulation test of the multi-pose angle combination change of the test piece with a simple structure and convenient operation.

Description

Technical Field

[0001] This invention belongs to the field of aviation equipment testing technology, specifically relating to a simulation test rotary table for unmanned aerial vehicle (UAV) fuel systems and a simulation test method using the simulation test rotary table. Background Technology

[0002] With the rapid development of unmanned aerial vehicles (UAVs), full-scale testing of various UAV fuel systems has been widely applied and popularized. As an important component of the power system in full-scale testing of UAV fuel systems, the reliability of the fuel system is crucial. Therefore, it is particularly important to conduct full-scale ground model tests on the fuel system before the test flight of the full-scale test of the UAV fuel system. This can directly verify the coordination and reliability of the system and the various finished components, and promptly identify system design defects and unforeseen design problems. It is an important and indispensable link and means to ensure the reliability and safe flight of the UAV fuel system in full-scale testing.

[0003] Existing UAV fuel system simulation test platforms fall into two categories: one is designed for small to medium-sized fuel systems, relying on manual operation to simulate the roll attitude adjustment of the UAV fuel system; the other is designed for large fuel systems, driven by electric motors, and similarly can only achieve roll attitude adjustment. Both types of simulation test platforms have difficulty simulating multi-attitude angle combinations. Furthermore, electric motor-driven simulation test platforms are often complex in design and control, costly, and have long production cycles, hindering their adoption by emerging design companies and timely application in projects. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing UAV fuel system simulation test platforms, which are difficult to simulate multiple attitude angle combinations and have complex structures. This invention provides a simulation test rotary table for UAV fuel systems and a simulation test method using this rotary table. This simulation test rotary table can realize roll adjustment, altitude adjustment, and large-angle pitch adjustment of the UAV fuel system, enabling simulation tests of multiple attitude angle combinations. Furthermore, it has a simple structure, is easy to use, and is particularly suitable for fuel systems of small and medium-sized UAVs.

[0005] To achieve the above objectives, the technical solution provided by this invention is:

[0006] A simulation test rotary table for unmanned aerial vehicle (UAV) fuel systems is characterized in that the simulation test rotary table includes a support unit, two fixed units, and two adjustment units.

[0007] The support unit is used to support and drive the fixed unit and the adjusting unit to move horizontally. The support unit includes a bracket.

[0008] The two fixing units face each other and are used to jointly clamp and fix the test piece, and both include a chuck assembly;

[0009] Two adjustment units are used to adjust the attitude of the test specimen and are vertically symmetrically arranged at both ends of the support. Each unit includes an adjustment component, an adapter component, and a rotating frame component.

[0010] The adjustment assembly includes an adjusting nut, a lead screw, a rotary adjusting member, and a first locking nut. The adjusting nut is fixed to the bracket. The lead screw cooperates with the adjusting nut to move up and down relative to the adjusting nut. The rotary adjusting member is fixed to the lead screw to drive the lead screw to rotate. The first locking nut is fitted on the lead screw to lock the lead screw.

[0011] The adapter assembly includes an adapter, a first bearing, a second bearing with a threaded shaft, and a pin. The adapter is connected to the lead screw via the first bearing to allow the lead screw to rotate relative to the adapter. The second bearing is mounted to the adapter via the pin so that the threaded shaft of the second bearing can rotate about the pin.

[0012] The rotating frame assembly includes a rotating shaft, a rotating frame, and a locking element. One end of the rotating shaft is threaded to the threaded shaft of the second bearing. The rotating frame is U-shaped and includes a crossbar and two legs extending from both ends of the crossbar. The middle part of the crossbar is rotatably connected to the other end of the rotating shaft. The locking element is used to lock the crossbar and the rotating shaft. The two legs are connected to both sides of the chuck assembly parallel to the axis of the chuck assembly to drive the chuck assembly and the test piece it holds to move.

[0013] Furthermore, the support includes a tube assembly, two crossbeams located at both ends of the tube assembly, and two vertical rods extending vertically upward from the two crossbeams respectively; the tube assembly includes two tubes, a locking bolt and a second locking nut, the two tubes are sleeved together and can move axially relative to each other to adjust the length, each of the two tubes has an axially extending elongated groove, the locking bolt passes through the elongated groove and connects to the second locking nut to lock the two tubes.

[0014] Furthermore, the chuck assembly includes a chuck, multiple adjusting screws with rubber blocks, and a third locking nut corresponding to each adjusting screw; the adjusting screws pass radially through the chuck, the rubber blocks are located at the tips of the adjusting screws for contact with the test piece, and the third locking nut is fitted on the shank of the adjusting screw and located outside the chuck.

[0015] Furthermore, the fixing unit also includes two sliders and set screws that correspond one-to-one with the sliders; the two sliders are fixed to both sides of the chuck, the two legs of the rotating frame pass through the two sliders respectively and can slide along the corresponding sliders, and the set screws pass radially through the sliders to fix the sliders.

[0016] Furthermore, the end of the rotating shaft connected to the crossbar is a smooth shaft; the locking components include a retaining ring, a limiting block, and a locking bolt; a sleeve is provided in the middle of the crossbar, the sleeve is fitted outside the smooth shaft of the rotating shaft and can rotate relative to the rotating shaft, the limiting block includes an axially extending protrusion, the retaining ring and the limiting block are sequentially fitted onto the rotating shaft outside the sleeve and pressed together, so that the protrusion moves into the groove on the sleeve, and the locking bolt is screwed into the hole on the end face of the rotating shaft to press against the limiting block.

[0017] Furthermore, the adapter assembly also includes a locking link, one end of which is detachably connected to the adapter and the other end is detachably connected to the middle of the crossbar of the rotating frame to support the chuck assembly via the rotating frame.

[0018] A simulation test method using the aforementioned rotary table for simulating unmanned aerial vehicle (UAV) fuel systems is characterized by comprising the following steps:

[0019] Step 1: Clamp both ends of the test piece into the two chuck assemblies respectively to fix the test piece;

[0020] Step 2: Push the support unit's bracket to move the test piece horizontally;

[0021] Step 3: Simultaneously rotate the rotating adjustment parts of the two adjustment units to drive the two lead screws to rotate, thereby adjusting the height of the test piece;

[0022] Step 4: Rotate the rotary adjustment component of one of the adjustment units to adjust the pitch of the test piece;

[0023] Step 5: Rotate the rotating frame of the adjustment unit around the rotating axis so that the rotating frame drives the chuck assembly and the test piece it holds to rotate around its rolling axis.

[0024] Furthermore, the simulation test method also includes the following steps:

[0025] When installing the test specimen, adjust the length of the tube assembly of the support;

[0026] When installing the test piece, tighten the adjusting screw and the third locking nut of the chuck assembly.

[0027] Furthermore, the simulation test method also includes the following steps:

[0028] After the test, connect one end of the locking linkage of the adjustment unit to the adapter of the adjustment unit and the other end to the rotating frame of the adjustment unit so as to support the chuck assembly via the rotating frame.

[0029] The advantages of this invention are:

[0030] 1. According to the present invention, a rotary table for simulating the fuel system of an unmanned aerial vehicle (UAV) includes a translational support unit, two fixing units for clamping and fixing the test piece, and two adjustment units for adjusting the attitude of the test piece. When the support unit's bracket is pushed, the test piece can be translated along the X and Y axes; when the rotary adjustment component of one of the adjustment units is rotated, the test piece can be pitched around the Y axis; when the rotary adjustment components of both adjustment units are rotated simultaneously, the height of the test piece on the Z axis can be adjusted; when the rotating frame of the adjustment unit is rotated around its axis, the test piece can be rolled around the X axis. Therefore, the present invention achieves simulation testing of multiple attitude angle combinations of the test piece with a simple structure and convenient operation.

[0031] 2. The present invention allows for adjustment of the length of the support, and the chuck assembly has an adjusting screw, enabling the clamping of drone fuel systems of different lengths and cross-sectional dimensions for full-scale testing.

[0032] 3. When the test is completed, the chuck assembly can be supported by the locking linkage to prevent the chuck assembly from tilting down and colliding with the bracket. At the same time, it facilitates the installation operation when installing the test piece. Attached Figure Description

[0033] The features and advantages of the invention will become more readily apparent from the following description with reference to the accompanying drawings, which are not drawn to scale and some features are enlarged or reduced to show details of specific parts.

[0034] Figure 1 This is a schematic perspective view of the rotating test platform for the simulation test of the fuel system of an unmanned aerial vehicle (UAV) according to the present invention;

[0035] Figure 2 This is a schematic perspective view of the support unit in the rotary table for simulating the fuel system of an unmanned aerial vehicle (UAV) according to the present invention.

[0036] Figure 3 This is a schematic perspective view of an adjustment unit in a rotating test platform for a drone fuel system according to the present invention.

[0037] Figure 4 yes Figure 3 A magnified view of detail A in the image;

[0038] Figure 5 This is a schematic perspective view of the adapter included in the adjustment unit of the rotary table for the simulation test of the fuel system of an unmanned aerial vehicle (UAV) according to the present invention.

[0039] Figure 6 This is a schematic perspective view of another adjustment unit in the rotary table for simulating the fuel system of an unmanned aerial vehicle (UAV) according to the present invention;

[0040] Figure 7 yes Figure 5 A magnified view of detail B in the image;

[0041] Figure 8 yes Figure 3 A magnified view of detail C in the image.

[0042] In the picture:

[0043] 1-Bracket, 101-Pipe assembly, 1011-Pipe, 1012-Locking bolt, 1013-Second locking nut, 102-Crossbeam, 103-Vertical rod, 104-Reinforcing rib, 13-Directional wheel, 14-Universal wheel;

[0044] 2-Chuck assembly, 201-Chuck, 202-Adjusting screw, 203-Third locking nut, 204-Rubber block, 21-Slider, 22-Set screw;

[0045] 3-Adjusting assembly, 301-Adjusting nut, 302-Lead screw, 303-Rotary adjusting component, 304-First locking nut;

[0046] 4-Adapter assembly, 401-Adapter, 4011-Lug, 402-First bearing, 403-Second bearing, 404-Pin, 405-Retaining ring, 406-Locking linkage;

[0047] 5-Swivel frame assembly, 501-Swivel shaft, 502-Swivel frame, 503-Locking component, 504-Retaining ring, 505-Limiting block, 506-Locking bolt, 507-Extension rod. Detailed Implementation

[0048] The present invention will now be described in detail with reference to the accompanying drawings and exemplary embodiments thereof. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to limit the scope of the invention.

[0049] Reference Figure 1 As an exemplary embodiment of the present invention, a rotary table for simulating a drone fuel system may include a support unit, two fixing units, and two adjusting units. The support unit is disposed on a support surface and is used to support and drive the fixing units and adjusting units to translate. It is the main support part of the rotary table and includes a bracket 1. The two fixing units face each other and are used to jointly clamp and fix the test piece, and each includes a chuck assembly 2. The two adjusting units are used to adjust the attitude of the test piece and are vertically symmetrically disposed at both ends of the bracket 1.

[0050] like Figure 2As shown, in some embodiments, the support 1 is length-adjustable. The support 1 includes a pipe assembly 101, two crossbeams 102 located at both ends of the pipe assembly 101, and two vertical rods 103 extending vertically upward from the two crossbeams 102 respectively. The pipe assembly 101 includes two pipes 1011, a locking bolt 1012, and a second locking nut 1013. The two pipes 1011 are sleeved together and can move axially relative to each other to adjust their length, thereby clamping UAV fuel systems of different lengths to accommodate full-scale testing of UAV fuel systems of different lengths. Each of the two pipes 1011 has an axially extending elongated groove. The locking bolt 1012 passes through the elongated groove and connects to the second locking nut 1013 to lock the two pipes 1011. In particular, the pipes 1011 can be rectangular pipes, the crossbeams 102 can be channel steel, the vertical rods 103 can be seamless steel pipes, and the locking bolts 1012 can be welded to the pipes 1011 to form a transmission support, serving as a guide and transmission function. In addition, two sets of locking bolts 1012 and second locking nuts 1013 can preferably be provided.

[0051] The support 1 may also include reinforcing ribs 104 that are obliquely connected to the crossbeam 102 and the vertical rod 103 to improve the strength of the support. Two reinforcing ribs 104 may be provided at each end of the support 1, and they are arranged symmetrically about the vertical axis of the vertical rod 103.

[0052] In a specific embodiment of the present invention, the support unit further includes two directional wheels 13 disposed at the bottom of one end of the crossbeam 102 and two universal wheels 14 disposed at the bottom of the other end of the crossbeam 102, so as to facilitate the test rotary table to move along the X and Y directions on the support platform to adjust the azimuth angle.

[0053] Return to reference Figure 1 Two adjustment units are located at both ends of the bracket 1, each including an adjustment component 3, an adapter component 4, and a rotating frame component 5. The adjustment component 3 mainly adjusts the height dimension; the adapter component 4 mainly converts the rotation direction, enabling independent and non-interfering rotational degrees of freedom in the horizontal and vertical directions, and is a key component in the rotational configuration; the rotating frame component 5 supports the chuck assembly 2 to rotate around the X direction.

[0054] Combination Figure 1 and Figure 3The adjusting assembly 3 includes an adjusting nut 301, a lead screw 302, a rotary adjusting member 303, and a first locking nut 304. The adjusting nut 301 is fixed to, and in particular welded to, the vertical rod 103 of the support 1. The lead screw 302 engages with the adjusting nut 301 to move up and down relative to the adjusting nut 301. The rotary adjusting member 303 is fixed to the lead screw 302 to rotate the lead screw 302. Optionally, the rotary adjusting member 303 is a handle, with its rod portion radially passing through the lead screw 302 and its end for the operator to grip and rotate. The first locking nut 304 is fitted onto the lead screw 302 to lock it in place. When adjusting the height and rotating the lead screw 302 is required, the first locking nut 304 is loosened first, and then the rotary adjusting member 303 is operated. After the height is adjusted to the desired position, the first locking nut 304 is tightened to lock it in place.

[0055] Next, refer to Figure 4 The adapter assembly 4 includes an adapter 401, a first bearing 402, a second bearing 403 with a threaded shaft, and a pin 404. The structure of the adapter 401 is as follows: Figure 5 As shown, it is connected to the lead screw 302 via a first bearing 402 to allow the lead screw 302 to rotate relative to the adapter 401. The adapter 401 can be fitted over the lead screw 302. The first bearing 402 can be a needle roller thrust bearing, which serves to bear axial force and release the rotational freedom of the lead screw 302. The second bearing 403 is mounted to the top of the adapter 401 via a pin 404, so that the threaded shaft of the second bearing 403 can rotate around the pin 404. The second bearing 403 can be a spherical plain bearing, mounted on the pin 404, which passes through two radial holes in the top of the adapter 401 and is limited at both ends by retaining rings 405.

[0056] Preferably, the adapter assembly 4 further includes a locking link 406, one end of which is connected to the adapter 401, particularly detachably connected to a lug 4011 provided on the adapter 401, and the other end is detachably connected to the middle of the crossbar of the rotating frame 502, so as to support the chuck assembly 2 via the rotating frame 502. The locking link 406 can be used when the test bench is idle to support the chuck assembly, preventing the chuck assembly from tilting down and colliding with components such as the bracket 1. At the same time, supporting the chuck assembly when installing the test piece facilitates the installation operation of the test piece on the chuck assembly.

[0057] With the above structure, after the test piece is installed in place, when the operator rotates the rotating adjustment component 303 on one side, the corresponding lead screw 302 on that side can move up and down, thereby realizing the pitch adjustment of the test piece around the Y-axis. When the two adjustment components 303 on both sides are rotated at the same time, the height of the test piece in the Z-axis direction can be adjusted.

[0058] Combination Figure 3 and Figure 6The rotating frame assembly 5 includes a rotating shaft 501, a rotating frame 502, and a locking member 503. One end of the rotating shaft 501 is threaded to the threaded shaft of the second bearing 403. The rotating frame 502 is generally U-shaped and includes a crossbar and two legs extending from both ends of the crossbar. The middle part of the crossbar is rotatably connected to the other end of the rotating shaft 501. The locking member 503 is used to lock the crossbar and the rotating shaft 501. The two legs are connected to both sides of the chuck assembly 2 parallel to the axis of the chuck assembly 2 to drive the chuck assembly 2 and the test piece it holds to move. The rotating shaft 501 and the rotating frame 502 cooperate to form a sliding bearing pair to achieve free roll in the X direction. The locking member 503 is used to lock the rotation angle of the test piece.

[0059] See now Figure 7 In some embodiments, the end of the rotating shaft 501 connected to the crossbar is a linear shaft. The locking member 503 includes a retaining ring 504, a limiting block 505, and a locking bolt 506. A sleeve is provided in the middle of the crossbar, which is sleeved outside the linear shaft of the rotating shaft 501 and can rotate relative to the rotating shaft 501. The limiting block 505 includes an axially extending protrusion. The retaining ring 504 and the limiting block 505 are sequentially sleeved on the rotating shaft 501 outside the sleeve and pressed tightly, so that the protrusion moves into a groove on the sleeve. The locking bolt 506 is screwed into a hole on the end face of the rotating shaft 501 to press against the limiting block 505. It should be understood that a groove for installing the retaining ring 504 is provided at an appropriate position on the rotating shaft 501.

[0060] Refer to Figure 3 and Figure 8 In an optional embodiment, the chuck assembly 2 includes a chuck 201, a plurality of adjusting screws 202, and a third locking nut 203 corresponding to each adjusting screw 202. Each adjusting screw 202 has a rubber block 204 at its tip. The adjusting screws 202 pass radially through the chuck 201, and the rubber blocks 204 are located at the ends of the adjusting screws 202 located radially inside the chuck 201 for contacting the test piece. The third locking nut 203 is fitted onto the shank of the adjusting screw 202 and located outside the chuck 201 for locking and fixing. It should be noted that the number of adjusting screws 202 is not limited, specifically three, but other numbers are also possible. With this structure of the chuck assembly 2, the radial dimension can be adjusted while protecting the test piece to clamp UAV fuel systems of different cross-sectional dimensions, thereby adapting to full-scale testing of UAV fuel systems of different cross-sectional dimensions.

[0061] Return to reference Figure 3 and Figure 6The fixing unit may also include two sliders 21 and set screws 22 corresponding to each slider 21. The two sliders 21 are symmetrically fixed to both sides of the chuck 201. The two legs of the rotating frame 502 pass through the two sliders 21 respectively and can slide along the corresponding sliders 21. The set screws 22 pass radially through the sliders 21 to fix the sliders 21. The sliders 21 and set screws 22 are used together to limit the position of the test piece and prevent it from falling off during the test. By setting the sliders 21 on the chuck 201, they cooperate with the rotating frame 502 that constitutes the raceway to form a slide rail, which is used to compensate for the movement displacement of the test piece during large-angle pitching, reduce friction, and adapt to the adaptive adjustment capability of the test piece on the guide rail during the test.

[0062] In addition, the rotating frame assembly 5 may also include extension rods 507 located on the axial extension lines of the two legs of the rotating frame 502. The extension rods 507 can be installed to the rotating frame 502 by means of threaded connection. When installing the test piece, the extension rods 507 can be removed to make room for installation. After the test piece is installed in place, the extension rods 507 are installed, and the slider 21 can slide on the extension rods 507. Thus, the extension rods 507 form a raceway to accommodate the adaptive adjustment capability of the test piece on the guide rail.

[0063] Now refer to Figure 1 The simulation test method using the above-described rotary table for a simulated test of an unmanned aerial vehicle (UAV) fuel system, as an exemplary embodiment of the present invention, is described below. The method includes the following steps:

[0064] Step 1: Clamp both ends of the test piece into the two chuck assemblies 2 respectively to fix the test piece;

[0065] Step 2: Push the support unit bracket 1 to move the test piece along the X and Y directions;

[0066] Step 3: Simultaneously rotate the rotating adjustment parts 303 of the two adjustment units to drive the two lead screws 302 to rotate, thereby adjusting the height of the test piece;

[0067] Step 4: Rotate the rotary adjustment component 303 of one of the adjustment units to adjust the pitch of the test piece;

[0068] Step 5: Rotate the rotating frame 502 of the adjustment unit around the rotating shaft 501 so that the rotating frame 502 drives the chuck assembly 2 and the test piece it holds to rotate around its rolling axis.

[0069] The simulation test method of the present invention further includes the following steps: when installing the test piece, adjusting the length of the tube assembly 101 of the support 1; when installing the test piece, tightening the adjusting screw 202 and the third locking nut 203 of the chuck assembly 2.

[0070] Optionally, the simulation test method of the present invention further includes the following steps: after the test, one end of the locking link 406 of the adjustment unit is connected to the adapter of the adjustment unit, and the other end is connected to the rotating frame 502 of the adjustment unit, so as to support the chuck assembly 2 via the rotating frame 502.

[0071] As described above, according to the present invention, when the support unit's bracket is pushed, the test specimen can be translated along the X and Y axes; when the rotary adjustment component of one of the adjustment units is rotated, the test specimen can be pitched around the Y axis; when the rotary adjustment components of both adjustment units are rotated simultaneously, the height of the test specimen on the Z axis can be adjusted; and when the rotating frame of the adjustment unit is rotated around the axis of rotation, the test specimen can be rolled around the X axis. Therefore, the present invention achieves simulation tests of multiple attitude angle combinations of the test specimen with a simple structure and convenient operation.

[0072] The features mentioned and / or shown in the foregoing description of exemplary embodiments of the present invention may be combined in the same or similar manner with one or more other embodiments, combined with features in other embodiments, or substituted for corresponding features in other embodiments. Such combinations or substitutions should also be considered as including within the scope of protection of the present invention.

Claims

1. A rotary table for simulating and testing fuel systems of unmanned aerial vehicles (UAVs), characterized in that: The simulated test rotary table includes a support unit, two fixed units, and two adjustment units; The support unit is used to support and drive the fixing unit and the adjusting unit to translate, and the support unit includes a bracket; The two fixing units face each other for jointly clamping and fixing the test piece, and each includes a chuck assembly; The two adjustment units are used to adjust the attitude of the test piece and are vertically symmetrically arranged at both ends of the support. Each unit includes an adjustment component, an adapter component, and a rotating frame component. The adjustment assembly includes an adjusting nut, a lead screw, a rotary adjusting member, and a first locking nut. The adjusting nut is fixed to the bracket. The lead screw cooperates with the adjusting nut to move up and down relative to the adjusting nut. The rotary adjusting member is fixed to the lead screw to drive the lead screw to rotate. The first locking nut is sleeved on the lead screw to lock the lead screw. The adapter assembly includes an adapter, a first bearing, a second bearing with a threaded shaft, and a pin. The adapter is connected to the lead screw via the first bearing to allow the lead screw to rotate relative to the adapter. The second bearing is mounted to the adapter via the pin so that the threaded shaft of the second bearing can rotate about the pin. The rotating frame assembly includes a rotating shaft, a rotating frame, and a locking member. One end of the rotating shaft is threaded to the threaded shaft of the second bearing. The rotating frame is U-shaped and includes a crossbar and two legs extending from both ends of the crossbar. The middle part of the crossbar is rotatably connected to the other end of the rotating shaft. The locking member is used to lock the crossbar and the rotating shaft. The two legs are connected to both sides of the chuck assembly parallel to the axis of the chuck assembly to drive the chuck assembly and the test piece it holds to move.

2. The rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to claim 1, characterized in that: The support includes a tube assembly, two crossbeams located at both ends of the tube assembly, and two vertical rods extending vertically upward from the two crossbeams respectively; The tube assembly includes two tubes, a locking bolt, and a second locking nut. The two tubes are sleeved together and can move axially relative to each other to adjust their length. Each of the two tubes has an axially extending elongated groove. The locking bolt passes through the elongated groove and connects to the second locking nut to lock the two tubes in place.

3. The rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to claim 1 or 2, characterized in that: The chuck assembly includes a chuck, multiple adjusting screws with rubber blocks, and a third locking nut that corresponds to each of the adjusting screws. The adjusting screw passes radially through the chuck, the rubber block is located at the tip of the adjusting screw and is used to contact the test piece, and the third locking nut is fitted on the rod of the adjusting screw and located outside the chuck.

4. The rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to claim 3, characterized in that: The fixing unit also includes two sliders and set screws that correspond one-to-one with the sliders; The two sliders are fixed to both sides of the chuck, the two legs of the rotating frame pass through the two sliders respectively and can slide along the corresponding sliders, and the set screw passes radially through the sliders to fix the sliders.

5. The rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to claim 1 or 2, characterized in that: The end of the rotating shaft that is connected to the crossbar is an optical axis; The locking component includes a retaining ring, a limiting block, and a locking bolt; A sleeve is provided in the middle of the crossbar. The sleeve is fitted outside the optical axis of the rotating shaft and can rotate relative to the rotating shaft. The limiting block includes an axially extending protrusion. The retaining ring and the limiting block are sequentially fitted onto the rotating shaft outside the sleeve and pressed together, so that the protrusion moves into the groove on the sleeve. The locking bolt is screwed into the hole on the end face of the rotating shaft to press on the limiting block.

6. The rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to claim 1 or 2, characterized in that: The adapter assembly also includes a locking link, one end of which is detachably connected to the adapter and the other end is detachably connected to the middle of the crossbar of the rotating frame, so as to support the chuck assembly via the rotating frame.

7. A simulation test method using a rotary table for simulating unmanned aerial vehicle (UAV) fuel systems according to any one of claims 1 to 6, characterized in that, Includes the following steps: Step 1: Clamp both ends of the test piece into the two chuck assemblies respectively to fix the test piece; Step 2: Push the support unit's bracket to move the test piece horizontally; Step 3: Simultaneously rotate the rotating adjustment parts of the two adjustment units to drive the two lead screws to rotate, thereby adjusting the height of the test piece; Step 4: Rotate the rotary adjustment component of one of the adjustment units to adjust the pitch of the test piece; Step 5: Rotate the rotating frame of the adjustment unit around the rotating axis so that the rotating frame drives the chuck assembly and the test piece it holds to rotate around its rolling axis.

8. The simulation test method according to claim 7, characterized in that, It also includes the following steps: When installing the test specimen, adjust the length of the tube assembly of the support; When installing the test piece, tighten the adjusting screw and the third locking nut of the chuck assembly.

9. The simulation test method according to claim 7 or 8, characterized in that, It also includes the following steps: After the test, one end of the locking linkage of the adjustment unit is connected to the adapter of the adjustment unit, and the other end is connected to the rotating frame of the adjustment unit, so as to support the chuck assembly via the rotating frame.

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