A simulation missile model for testing based on unmanned aerial vehicles

Abstract

The invention discloses a simulation missile model for testing based on an unmanned aerial vehicle, and the technical scheme thereof is as follows: it comprises an unmanned aerial vehicle body, both ends of the bottom of the unmanned aerial vehicle body are provided with limit support components, a simulation missile body is provided at the bottom of the unmanned aerial vehicle body, a detector body is provided at the bottom of the simulation missile body, a limit connection component is provided at the top of the detector body, and a movable connection mechanism is provided at the top of the simulation missile body, and the movable connection mechanism comprises a limit column, an annular support rod and a motor. The beneficial effect of the simulation missile model for testing based on the unmanned aerial vehicle is as follows: it avoids the problem that the current simulation missile model is not stable when fixed at the bottom of the unmanned aerial vehicle, when encountering a situation where the wind is strong at high altitude, the simulation missile model is prone to offset and shake, and when the simulation missile model shakes too much, it is very easy to fall off, resulting in the simulation missile model falling before reaching the required height, causing the result of dynamic data test to be inaccurate, and affecting the test personnel's dynamic data test.

Description

Technical Field

[0001] The invention relates to the technical field of simulated missile models, and in particular to a simulated missile model for testing based on an unmanned aerial vehicle. Background Art

[0002] In the performance test of existing detector electronic components, two methods are generally used for performance testing. The first is to use line testing in a darkroom to simulate air echoes through lines, and to determine whether the specified requirements are met by sending and receiving signals. This test method is a static test. The test space is particularly clean and free of other interference, but it is different from the actual use environment and has an impact on the reliability of the test results. The second is an actual bomb drop test, which collects data through dynamic testing. The test data obtained by this test method is completely based on the actual environment. A drone carries a simulated bomb model to release bombs at high altitudes, and then performs dynamic data testing, while reading the test data.

[0003] The existing technology has the following deficiencies: the simulation missile model used in existing drone tests is generally directly and simply limited. When the drone rises to a high altitude, the simulation missile model is released. However, the current simulation missile model is not stably fixed at the bottom of the drone. When encountering strong winds at high altitudes, the simulation missile model is prone to offset and jitter. When the simulation missile model jitters too much, it is very easy to fall off, causing the simulation missile model to fall before reaching the required height, resulting in inaccurate results of dynamic data testing, which affects the test personnel's testing of dynamic data.

[0004] Therefore, it is necessary to invent a simulation missile model based on unmanned aerial vehicle for testing to solve the above problems. Summary of the invention

[0005] To this end, the present invention provides a simulation missile model for testing based on a drone, which connects the simulation missile model and the drone by setting an active connection mechanism, so that the simulation missile model can be released after the drone flies to a high altitude, so as to solve the problem that the current simulation missile model is not stable when fixed at the bottom of the drone. When encountering strong winds at high altitudes, the simulation missile model is prone to offset and jitter. When the simulation missile model jitters too much, it is very likely to fall off, causing the simulation missile model to fall before reaching the required height, resulting in inaccurate results of dynamic data testing, which affects the test personnel's testing of dynamic data.

[0006] In order to achieve the above-mentioned object, the present invention provides the following technical solutions: a simulation missile model for testing based on a drone, comprising a drone body, both ends of the bottom of the drone body are provided with limit support components, a simulation missile body is provided at the bottom of the drone body, a detector body is provided at the bottom of the simulation missile body, a limit connection component is provided at the top of the detector body, and a movable connection mechanism is provided at the top of the simulation missile body;

[0007] The movable connection mechanism includes a limit column, an annular support rod and a motor, the limit column is located at the top of the simulation missile body and is fixedly connected to the simulation missile body, the top of the limit column is provided with a fixed sleeve, the fixed sleeve is fixedly connected to the drone body, the top of the limit column is fixedly connected with a first circular magnetic block, the inner bottom of the fixed sleeve is fixedly connected with a second circular magnetic block, the first circular magnetic block and the second circular magnetic block are magnetically connected, the inner side of the annular support rod is fixedly connected with a T-shaped arc plate, the bottom of the T-shaped arc plate is fixedly connected to the simulation missile body, the annular support rod is located on the outside of the top of the limit column, both ends of the annular support rod are provided with sliding vertical plates, the bottom of the drone body is provided with a fixed square groove, the motor is located at the inner top of the fixed square groove, the top of the motor is fixedly connected with a connecting plate, and the connecting plate is connected to the drone The human-machine body is fixedly connected, and the motor output end is fixedly connected with a spiral rod, and the spiral rod is fixedly connected with a first gear at one end away from the motor, and a second gear is provided at the bottom of the first gear, and the first gear and the second gear are meshed and connected, and threaded cross bars are fixedly connected on both sides of the second gear, and threaded holes are provided on one side surface of the top of the two sliding vertical plates, and the two threaded cross bars respectively penetrate the two threaded holes and are threadedly connected with the threaded holes, and sliding cross grooves are provided on both sides of the bottom of the fixed square groove, and the sliding vertical plates are slidably connected to the sliding cross grooves, and limiting clamping rods are fixedly connected on both sides of the bottom of the sliding vertical plates, and limiting clamping grooves are provided on both sides of the bottom surface of the annular support rod, and the number of the limiting clamping grooves is set to two, and the two limiting clamping grooves are symmetrically distributed, and the limiting clamping rods match the limiting clamping grooves.

[0008] Preferably, the two limit support assemblies each include a support cross bar, the two support cross bars are located at both ends of the bottom of the drone body, both ends of the top of the support cross bar are fixedly connected to the support cross bar, and the top of the support cross bar is fixedly connected to the bottom of the drone body.

[0009] Preferably, a guide vane is fixedly connected to the top of the simulation bullet body, the number of the guide vanes is set to be multiple, and the multiple guide vanes are distributed in a circular array.

[0010] Preferably, the number of the T-shaped arc plates is set to be multiple, and the multiple T-shaped arc plates are distributed in a circular array, and one side of the T-shaped arc plate matches the outer side of the limiting column.

[0011] Preferably, bearings are provided on both sides of the fixed square groove, the bearings are fixedly connected to the drone body, and the end of the threaded cross rod away from the second gear is fixedly connected to the inner side of the bearing.

[0012] Preferably, the limiting connection assembly includes a connecting circular plate and an annular clamping plate, the connecting circular plate is located at the top of the detector body, a limiting thread groove is provided on the bottom surface of the connecting circular plate, a threaded circular plate is fixedly connected to the top of the detector body, the threaded circular plate is threadedly connected to the limiting thread groove, a guide groove is provided on the outer surface of the top of the connecting circular plate, the number of the guide grooves is set to multiple, and the multiple guide grooves are distributed in a circular array.

[0013] Preferably, the annular clamping plate is located at the top of the connecting circular plate and is fixedly connected to the connecting circular plate, an annular groove is provided on the bottom surface of the simulation bullet body, the annular clamping plate matches the annular groove, fixed clamping grooves are provided on both side surfaces of the annular clamping plate, sliding clamping grooves are provided on both sides of the annular groove, the sliding clamping grooves match the fixed clamping grooves, a movable clamping block is provided on the inner side of the fixed clamping groove, and the movable clamping block is slidably connected to the sliding clamping groove.

[0014] Preferably, a movable pull rod is provided on the surface of one side of the movable clamping block, and an arc-shaped pull plate is provided at the end of the movable pull rod away from the movable clamping block. The movable pull rod passes through one side of the simulation bullet body and is fixedly connected with the arc-shaped pull plate. A limit spring is provided on the outer side of the end of the movable pull rod away from the arc-shaped pull plate, one end of the limit spring is fixedly connected to the movable clamping block, and the other end of the limit spring is fixedly connected to the simulation bullet body.

[0015] Preferably, both sides of the top of the annular clamping plate are provided with limiting circular grooves, the inner side of the limiting circular groove is provided with a return spring, and the return spring is fixedly connected to the simulation bullet body.

[0016] The beneficial effects of the present invention are:

[0017] 1. The present invention connects the simulation missile model and the unmanned aerial vehicle by setting a movable connection mechanism, so that the unmanned aerial vehicle can release the simulation missile model after flying to a high altitude. When the unmanned aerial vehicle body flies to a high altitude, the starting motor drives the spiral rod and the first gear to rotate, the first gear drives the second gear to rotate, the second gear drives the threaded cross bar to rotate, and the threaded cross bar drives the sliding vertical rod to move while rotating, and the sliding vertical rod drives the limit clamping rod to move, and the limit clamping rod is away from the limit clamping slot. The gravity of the simulation missile body is greater than the magnetic force between the first circular magnetic block and the second circular magnetic block. The simulation missile body falls and performs dynamic testing. The simulation missile body is limited and supported by matching the two limit clamping rods and the two limit clamping slots. The present invention has a reasonable structure and clear logic, improves the stability of the simulation missile model at the bottom of the unmanned aerial vehicle, and avoids the current simulation missile model being fixed at the bottom of the unmanned aerial vehicle. The unstable state, when encountering a high wind in the sky, the simulation missile model is prone to offset and jitter, and the simulation missile model is very likely to fall off when the jitter is too large, resulting in the simulation missile model falling before reaching the required height, causing the result of the dynamic data test to be inaccurate, which affects the test of the dynamic data by the tester.

[0018] 2. The present invention provides a limit connection component to detachably connect the detector body to the bottom of the simulation bullet body. During the installation of the detector body, the threaded circular plate on the top of the detector body is first fixed to the limit thread groove at the bottom of the connecting circular plate through threaded connection. Then, the annular clamping plate on the top of the connecting circular plate is inserted into the annular groove at the bottom of the simulation bullet body. The annular clamping plate pushes the movable clamping block to move, and the movable clamping block squeezes the limit spring. The limit spring is elastically deformed and compressed, and the movable clamping block moves to the inside of the sliding clamping groove. The annular clamping plate continues to move until it contacts the reset spring. The annular clamping plate squeezes the reset spring, and the reset spring is deformed and compressed into the limit circular groove. At the same time, the movable clamping block coincides with the fixed clamping groove, and the limit spring restores the elastic deformation, pushing the movable clamping block to move to the inside of the fixed clamping groove to clamp the annular clamping plate, thereby fixing the connecting circular plate and the detector body at the bottom of the simulation bullet body, which is convenient for the detector body to test dynamic data during the falling process of the simulation bullet body, thereby improving the convenience of the detector body during installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of the overall structure provided by the present invention;

[0020] Figure 2 A schematic diagram of the explosion structure of the movable connection mechanism is provided for the present invention;

[0021] Figure 3 A schematic diagram of the explosion structure of the position limiting connection assembly is provided for the present invention;

[0022] Figure 4 A front cross-sectional view provided for the present invention;

[0023] Figure 5 The present invention provides Figure 3 The enlarged structure diagram of the middle A part;

[0024] Figure 6 The present invention provides Figure 4 The enlarged structural diagram of the middle B part;

[0025] Figure 7 The present invention provides Figure 4 Enlarged structural diagram of the middle C part;

[0026] In the figure: 1 UAV body, 2 simulation missile body, 3 detector body, 4 limit column, 5 annular support rod, 6 motor, 7 fixed sleeve, 8 first circular magnetic block, 9 second circular magnetic block, 10 T-shaped arc plate, 11 sliding vertical plate, 12 fixed square groove, 13 screw rod, 14 first gear, 15 second gear, 16 threaded cross bar, 17 threaded hole, 18 sliding cross groove, 19 limit clamping rod, 20 limit clamping groove, 21 support cross bar, 22 support vertical rod, 23 guide plate, 24 connecting circular plate, 25 annular clamping plate, 26 threaded circular plate, 27 guide groove, 28 annular groove, 29 sliding clamping groove, 30 fixed clamping groove, 31 movable clamping block, 32 movable pull rod, 33 arc pull plate, 34 limit spring, 35 limit circular groove, 36 reset spring. DETAILED DESCRIPTION

[0027] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0028] Embodiment 1:

[0029] Refer to the attached Figure 1-7 The present invention provides a simulated missile model for testing based on a drone, comprising a drone body 1, wherein both ends of the bottom of the drone body 1 are provided with limit support components, a simulated missile body 2 is provided at the bottom of the drone body 1, a detector body 3 is provided at the bottom of the simulated missile body 2, a limit connection component is provided at the top of the detector body 3, and a movable connection mechanism is provided at the top of the simulated missile body 2;

[0030] The movable connection mechanism includes a limit column 4, an annular support rod 5 and a motor 6. The limit column 4 is located at the top of the simulation missile body 2 and is fixedly connected to the simulation missile body 2. A fixed sleeve 7 is provided on the top of the limit column 4, and the fixed sleeve 7 is fixedly connected to the drone body 1. A first circular magnetic block 8 is fixedly connected to the top of the limit column 4, and a second circular magnetic block 9 is fixedly connected to the bottom of the inner side of the fixed sleeve 7. The first circular magnetic block 8 and the second circular magnetic block 9 are magnetically connected. A T-shaped arc plate 10 is fixedly connected to the inner side of the annular support rod 5, and the bottom of the T-shaped arc plate 10 is fixedly connected to the simulation missile body 2. The annular support rod 5 is located on the outside of the top of the limit column 4. Sliding vertical plates 11 are provided at both ends of the annular support rod 5. A fixed square groove 12 is opened at the bottom of the drone body 1. The motor 6 is located at the top of the inner side of the fixed square groove 12. A connecting plate is fixedly connected to the top of the motor 6, and the connecting plate is fixedly connected to the drone body 1. A screw rod 13 is fixedly connected to the output end of the motor 6, and a first gear 14 is fixedly connected to the end of the screw rod 13 away from the motor 6. A second gear 15 is provided at the bottom of the first gear 14, and the first gear 14 and the second gear 15 are meshed and connected. Threaded cross bars 16 are fixedly connected on both sides of the second gear 15. Threaded holes 17 are provided on the top side surfaces of the two sliding vertical plates 11, and the two threaded cross bars 16 respectively penetrate the two threaded holes 17 and are threadedly connected with the threaded holes 17. Sliding transverse grooves 18 are provided on both sides of the bottom of the fixed square groove 12, and the sliding vertical plates 11 are slidably connected to the sliding transverse grooves 18. Limiting clamping rods 19 are fixedly connected on both sides of the bottom of the sliding vertical plates 11, and limiting clamping grooves 20 are provided on both side surfaces of the bottom of the annular support rod 5. The number of the limiting clamping grooves 20 is set to two, and the two limiting clamping grooves 20 are symmetrically distributed, and the limiting clamping rods 19 match the limiting clamping grooves 20.

[0031] Furthermore, the two limit support assemblies each include a support cross bar 21, and the two support cross bars 21 are located at the two ends of the bottom of the drone body 1. The two ends of the top of the support cross bar 21 are fixedly connected with support vertical bars 22, and the top of the support vertical bar 22 is fixedly connected to the bottom of the drone body 1. By arranging the limit support assemblies at the two ends of the bottom of the drone body 1, the drone body 1 is supported when it is parked.

[0032] Furthermore, a guide plate 23 is fixedly connected to the top of the simulated missile body 2, and the number of the guide plates 23 is set to be multiple, and the multiple guide plates 23 are distributed in a circular array. By arranging multiple guide plates 23 distributed in a circular array on the outer side of the top of the simulated missile body 2, during the falling process of the simulated missile body 2, the guide plates 23 guide the air when the simulated missile body 2 falls, so that the simulated missile body 2 is more stable when falling.

[0033] Furthermore, the number of the T-shaped arc plates 10 is set to be multiple, and the multiple T-shaped arc plates 10 are distributed in a circular array, one side of the T-shaped arc plate 10 matches the outer side of the limit column 4, and the top side of the T-shaped arc plate 10 matches the outer side of the fixed sleeve 7 at the bottom of the drone body 1, and the first circular magnetic block 8 and the second circular magnetic block 9 are fixed by magnetic connection, so that the connection of the drone body 1 is more stable.

[0034] Furthermore, bearings are provided on both sides of the fixed square groove 12, and the bearings are fixedly connected to the drone body 1. The end of the threaded cross bar 16 away from the second gear 15 is fixedly connected to the inner side of the bearing. Bearings are provided at the ends of the two threaded cross bars 16 away from the second gear 15, so that the second gear 15 can drive the two threaded cross bars 16 to rotate more stably at the same time, and the two threaded cross bars 16 are integrally formed with opposite screw threads, and the threaded holes 17 on the top side of the two sliding vertical plates 11 are integrally formed with opposite screw threads, so that when the two threaded cross bars 16 rotate at the same time, the two sliding vertical plates 11 move in opposite directions.

[0035] The use process of the present invention is as follows: in the process of using the present invention to test the performance of the detector electronic components, the tester starts the drone body 1, the drone body 1 drives the simulation missile body 2 to fly to the required height in the sky, and then starts the motor 6, the output end of the motor 6 drives the screw rod 13 to rotate, the screw rod 13 drives the first gear 14 to rotate, the first gear 14 drives the second gear 15 to rotate, and the second gear 15 simultaneously drives the two threaded cross bars 16 to rotate, and the two threaded cross bars 16 rotate while driving the two sliding vertical bars to move in opposite directions, the two sliding vertical bars slide on the inner sides of the two sliding horizontal grooves 18 respectively, and the two sliding vertical bars simultaneously drive the limit card rods 19 on both sides of the bottom thereof to move in opposite directions, the limit card rod 19 is away from the limit card groove 20 at the bottom of the annular support rod 5, the annular support rod 5 at the top of the simulation missile body 2 lacks the support of the limit card rod 19, the gravity of the simulation missile body 2 is greater than the magnetic force between the first circular magnetic block 8 and the second circular magnetic block 9, the simulation missile body 2 falls, and the simulation missile body 2 drives the detector body 3 to move downward, and the dynamic data of the detector body 3 is tested.

[0036] Embodiment 2:

[0037] Refer to the attached Figure 3 and Figure 6The present invention provides a simulation missile model based on a drone for testing, wherein the limiting connection component includes a connecting circular plate 24 and an annular clamping plate 25, wherein the connecting circular plate 24 is located at the top of the detector body 3, and a limiting thread groove is provided on the bottom surface of the connecting circular plate 24, and a threaded circular plate 26 is fixedly connected to the top of the detector body 3, and the threaded circular plate 26 is threadedly connected to the limiting thread groove, and a guide groove 27 is provided on the outer surface of the top of the connecting circular plate 24, and the number of the guide grooves 27 is set to be multiple, and the multiple guide grooves 27 are distributed in a circular array, the annular clamping plate 25 is located at the top of the connecting circular plate 24 and is fixedly connected to the connecting circular plate 24, and an annular groove 28 is provided on the bottom surface of the simulation missile body 2, and the annular clamping plate 25 matches the annular groove 28, and fixed clamping grooves 30 are provided on both side surfaces of the annular clamping plate 25, and the annular groove 28 Sliding slots 29 are provided on both sides of the interior, and the sliding slots 29 match the fixed slots 30. A movable block 31 is provided on the inner side of the fixed slot 30, and the movable block 31 is slidably connected to the sliding slot 29. A movable pull rod 32 is provided on one side surface of the movable pull rod 31, and an arc-shaped pull plate 33 is provided on the end of the movable pull rod 32 away from the movable block 31. The movable pull rod 32 passes through one side of the simulation bullet body 2 and is fixedly connected to the arc-shaped pull plate 33. A limiting spring 34 is provided on the outer side of the end of the movable pull rod 32 away from the arc-shaped pull plate 33, one end of the limiting spring 34 is fixedly connected to the movable block 31, and the other end of the limiting spring 34 is fixedly connected to the simulation bullet body 2. Limiting circular grooves 35 are provided on both sides of the top of the annular clamping plate 25, and a reset spring 36 is provided on the inner side of the limiting circular groove 35, and the reset spring 36 is fixedly connected to the simulation bullet body 2.

[0038] The usage process is as follows: before using the present invention, the detector body 3 needs to be installed on the simulation bullet body 2, and the threaded circular plate 26 on the top of the detector body 3 is fixed with the limiting thread groove at the bottom of the connecting circular plate 24 by threaded connection, and then the annular clamping plate 25 on the top of the connecting circular plate 24 is inserted into the annular groove 28 at the bottom of the simulation bullet body 2, and the annular clamping plate 25 pushes the movable clamping block 31 to move, and the movable clamping block 31 squeezes the limiting spring 34, and the limiting spring 34 produces elastic deformation and is compressed, and the movable clamping block 31 moves into the sliding clamping groove 29 On the side, the annular clamping plate 25 continues to move until it contacts the bottom of the reset spring 36, and the annular clamping plate 25 squeezes the reset spring 36. The reset spring 36 is deformed and compressed to the inside of the limiting circular groove 35. At the same time, the movable clamping block 31 coincides with the position of the fixed clamping groove 30, and the limiting spring 34 restores the elastic deformation. The limiting spring 34 pushes the movable clamping block 31 to move, and the movable clamping block 31 moves to the inside of the fixed clamping groove 30. The movable clamping block 31 clamps the annular clamping plate 25, so that the connecting circular plate 24 and the detector body 3 are fixed at the bottom of the simulation bullet body 2.

[0039] The above is only a preferred embodiment of the present invention. Any person skilled in the art may modify the present invention by using the above technical solution or modify it into an equivalent technical solution. Therefore, any simple modification or equivalent replacement made according to the technical solution of the present invention shall fall within the scope of protection claimed by the present invention.

Claims

1. A simulated missile model for conducting tests based on an unmanned aerial vehicle, comprising an unmanned aerial vehicle body (1), characterized in that: Both ends of the bottom of the drone body (1) are provided with limit support components, the bottom of the drone body (1) is provided with a simulation missile body (2), the bottom of the simulation missile body (2) is provided with a detector body (3), the top of the detector body (3) is provided with a limit connection component, and the top of the simulation missile body (2) is provided with a movable connection mechanism; the movable connection mechanism comprises a limit column (4), an annular support rod (5) and a motor (6), the limit column (4) is located at the top of the simulation missile body (2) and is fixedly connected to the simulation missile body (2), the top of the limit column (4) is provided with a fixed sleeve (7), and the fixed sleeve (7) is connected to the drone body (1). The drone body (1) is fixedly connected, the top of the limiting column (4) is fixedly connected with a first circular magnetic block (8), the inner bottom of the fixing sleeve (7) is fixedly connected with a second circular magnetic block (9), the first circular magnetic block (8) and the second circular magnetic block (9) are magnetically connected, the inner side of the annular support rod (5) is fixedly connected with a T-shaped arc plate (10), the bottom of the T-shaped arc plate (10) is fixedly connected with the simulation missile body (2), the annular support rod (5) is located on the outer side of the top of the limiting column (4), and sliding vertical plates (11) are provided at both ends of the annular support rod (5), and a fixed square groove (12) is provided at the bottom of the drone body (1). The motor (6) is located at the top of the inner side of the fixed square groove (12); a connecting plate is fixedly connected to the top of the motor (6); the connecting plate is fixedly connected to the drone body (1); a screw rod (13) is fixedly connected to the output end of the motor (6); the end of the screw rod (13) away from the motor (6) is fixedly connected to a first gear (14); a second gear (15) is provided at the bottom of the first gear (14); the first gear (14) and the second gear (15) are meshed and connected; threaded cross bars (16) are fixedly connected to both sides of the second gear (15); and threaded holes are provided on one side surface of the top of the two sliding vertical plates (11). (17), the two threaded cross bars (16) respectively penetrate the two threaded holes (17) and are threadedly connected to the threaded holes (17), both sides of the bottom of the fixed square groove (12) are provided with sliding cross grooves (18), the sliding vertical plate (11) is slidably connected to the sliding cross grooves (18), both sides of the bottom of the sliding vertical plate (11) are fixedly connected with limiting clamping rods (19), and both sides of the bottom surface of the annular support rod (5) are provided with limiting clamping grooves (20), the number of the limiting clamping grooves (20) is set to two, the two limiting clamping grooves (20) are symmetrically distributed, and the limiting clamping rod (19) matches the limiting clamping groove (20).

2. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 1, characterized in that: The two position-limiting support assemblies each comprise a support cross bar (21), the two support cross bars (21) being located at two ends of the bottom of the drone body (1), the top ends of the support cross bars (21) being fixedly connected to support vertical bars (22), the tops of the support vertical bars (22) being fixedly connected to the bottom of the drone body (1).

3. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 1, characterized in that: A guide plate (23) is fixedly connected to the top of the simulation bullet body (2), the number of the guide plates (23) is set to be multiple, and the multiple guide plates (23) are distributed in a circular array.

4. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 1, characterized in that: The number of the T-shaped arc plates (10) is set to be multiple, and the multiple T-shaped arc plates (10) are distributed in a circular array, and one side of the T-shaped arc plate (10) matches the outer side of the limiting column (4).

5. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 1, characterized in that: Bearings are provided on both sides of the fixed square groove (12), the bearings are fixedly connected to the drone body (1), and the end of the threaded cross bar (16) away from the second gear (15) is fixedly connected to the inner side of the bearing.

6. The simulated missile model for testing based on an unmanned aerial vehicle according to claim 1, characterized in that: The limiting connection assembly comprises a connecting circular plate (24) and an annular clamping plate (25); the connecting circular plate (24) is located at the top of the detector body (3); a limiting thread groove is provided on the bottom surface of the connecting circular plate (24); a threaded circular plate (26) is fixedly connected to the top of the detector body (3); the threaded circular plate (26) is threadedly connected to the limiting thread groove; a guide groove (27) is provided on the outer surface of the top of the connecting circular plate (24); the number of the guide grooves (27) is set to be multiple, and the multiple guide grooves (27) are distributed in a circular array.

7. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 6, characterized in that: The annular clamping plate (25) is located at the top of the connecting circular plate (24) and is fixedly connected to the connecting circular plate (24); an annular groove (28) is provided on the bottom surface of the simulation bullet body (2); the annular clamping plate (25) matches the annular groove (28); fixed clamping grooves (30) are provided on both side surfaces of the annular clamping plate (25); sliding clamping grooves (29) are provided on both sides of the annular groove (28); the sliding clamping grooves (29) match the fixed clamping grooves (30); a movable clamping block (31) is provided inside the fixed clamping groove (30); and the movable clamping block (31) is slidably connected to the sliding clamping groove (29).

8. The simulation missile model for testing based on an unmanned aerial vehicle according to claim 7, characterized in that: A movable pull rod (32) is provided on the surface of one side of the movable clamping block (31); an arc-shaped pull plate (33) is provided at one end of the movable pull rod (32) away from the movable clamping block (31); the movable pull rod (32) passes through one side of the simulation bullet body (2) and is fixedly connected to the arc-shaped pull plate (33); a limit spring (34) is provided on the outer side of one end of the movable pull rod (32) away from the arc-shaped pull plate (33); one end of the limit spring (34) is fixedly connected to the movable clamping block (31); and the other end of the limit spring (34) is fixedly connected to the simulation bullet body (2).

9. The simulated missile model for testing based on an unmanned aerial vehicle according to claim 6, characterized in that: Both sides of the top of the annular clamping plate (25) are provided with limiting circular grooves (35), the inner side of the limiting circular grooves (35) is provided with a return spring (36), and the return spring (36) is fixedly connected to the simulation bullet body (2).

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