Vertical unmanned aerial vehicle test platform

Abstract

A vertical unmanned aerial vehicle test platform disclosed by the present invention comprises an upper platform and a lower platform, the upper platform is installed on the lower platform, the upper platform comprises a vehicle body fixing table, a fixing hole is formed in the vehicle body fixing table, the bottom of the vehicle body fixing table is connected with a ball seat through a fixing piece, and the lower platform comprises a hemispherical seat. The two hemisphere seats are oppositely installed at the top of the sliding shaft, the lower ends of the hemisphere seats are installed in the two hemisphere seats, a buffer block is installed in the middle of the sliding shaft, the lower end of the sliding shaft is installed in the supporting frame in a sliding mode, a spring supporting arm is installed at the bottom of the sliding shaft, and a spring is installed between the spring supporting arm and the supporting frame. And the spring is sleeved on the sliding shaft. The test platform is high in universality: under the allowable maximum weight of the test platform, for airplanes with different weights, the airplanes with different weights and sizes can be tested only by replacing the springs and changing the springs with different rigidities to meet different counterweight requirements, and the test platform is high in universality.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle testing equipment, and in particular to a vertical take-off unmanned aerial vehicle testing platform. Background Art

[0002] VTOL drones do not require a specific runway and can take off and land vertically on the ground. They are widely used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, and creating romance.

[0003] During the development process of VTOL drones, they need to go through the processes of research and development, manufacturing, ground testing, test flights, and operation. In the ground test before the test flight, it is necessary to complete the adjustment of various parameters of the aircraft, simulate the flight posture in the air on the ground, and reduce the risk of test flights. Only by completing the flight parameter test as much as possible on the ground can the risk of crashing the aircraft in the test flight in the sky be reduced. Therefore, VTOL drones need to be tested on the ground test platform. The existing test platforms for VTOL drones mostly use metal frames, on which the motors are fixed to drive the vertical take-off and landing of the metal frames. However, the use of metal frames cannot test aircraft of different weights and sizes, and the versatility is poor. Summary of the invention

[0004] The purpose of the present invention is to provide a vertical unmanned aerial vehicle test platform to solve the problems mentioned in the background technology. To achieve the above purpose, the present invention provides the following technical solutions: a vertical unmanned aerial vehicle test platform, including an upper platform and a lower platform, the upper platform is installed on the lower platform, the upper platform includes a body fixing platform, the body fixing platform is provided with a fixing hole, the bottom of the body fixing platform is connected to the ball seat through a fixing member, the lower platform includes a hemispherical seat, the hemispherical seat is provided with two, relatively installed on the top of the sliding shaft, the lower end of the ball seat is installed in the two hemispherical seats, a buffer block is installed in the middle of the sliding shaft, the lower end of the sliding shaft is slidably installed inside the support frame, a spring support arm is installed at the bottom of the sliding shaft, a spring is installed between the spring support arm and the support frame, and the spring is sleeved on the sliding shaft.

[0005] Preferably, the ball seat comprises a ball shaft, and a limiting platform is provided on the ball shaft.

[0006] Preferably, there are a plurality of fixing holes arranged vertically and horizontally on the machine body fixing platform.

[0007] Preferably, a hemispherical groove is opened on the hemispherical seat, and the two hemispherical grooves are relatively distributed. The two hemispherical seats are connected by bolts, and the ball shaft is located inside the two hemispherical grooves. A small gap is provided between the hemispherical groove and the ball shaft, and the inside is coated with grease. A vertical edge is provided on the side of the hemispherical seat, and a chamfer is provided on the end of the vertical edge. The extension line of the limit platform of the ball seat and the extension line of the vertical edge of the hemispherical seat pass through the center of the ball.

[0008] Preferably, the support frame comprises a sliding sleeve, a support arm is installed on the side of the sliding sleeve, the sliding shaft is slidably installed inside the sliding sleeve, and the spring is installed between the bottom end of the sliding sleeve and the spring support arm.

[0009] Preferably, a flange edge is provided in the middle of the sliding shaft, and the buffer block is installed at the bottom of the flange edge.

[0010] Preferably, a through hole is formed at the bottom of the sliding shaft, and the spring arm passes through the through hole and is fixed by a locking pin.

[0011] Preferably, the fixing members are bolts and nuts.

[0012] The technical effects and advantages of the present invention are as follows: the test platform has high versatility: under the maximum weight allowed by the test platform, for aircrafts of different weights, only the springs need to be replaced, and the springs are replaced with different stiffnesses to meet different counterweight requirements, so that aircrafts of different weights and sizes can be tested, and the versatility is high;

[0013] Accurate test data: Using real aircraft for testing, its weight, size, rotational inertia, aerodynamics, and power characteristics are consistent with the subsequent air test aircraft data, which can better ensure the accuracy of test data and better determine the control rate of the aircraft;

[0014] Small ground effect: The test platform lifts the aircraft to a high altitude above the ground. When the propeller rotates, the ground has little impact on the airflow of the propeller, which can effectively reduce the ground effect and ensure the performance of the propeller.

[0015] High safety: The aircraft is restricted from leaving the test platform. When the power fails or the attitude is out of control during the test, the aircraft is restrained on the test platform and there is no fall, which will not damage the aircraft or cause damage to the fuselage.

[0016] Low cost: The test platform has a metal frame structure and does not use electronic and electrical components, so the processing cost is low. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is an axonometric diagram of the vertical take-off UAV of the present invention fixed on a test platform;

[0018] Figure 2 is an axonometric view of the present invention;

[0019] Figure 3 An exploded view of the present invention;

[0020] Figure 4 An exploded view of the upper platform of the present invention;

[0021] Figure 5 An exploded view of the lower platform of the present invention;

[0022] Figure 6 is an axonometric view of the ball seat of the present invention;

[0023] Figure 7 It is an axonometric view of the hemispherical seat of the present invention;

[0024] Figure 8 It is an axonometric view of the machine body fixing platform of the present invention;

[0025] Fig. 9 is an axonometric view of the support frame of the present invention;

[0026] Fig.10 The upper part of the cross-sectional view of the present invention at the ball seat;

[0027] Fig.11 The lower part of the cross-sectional view of the present invention at the ball seat;

[0028] Fig.12 It is a cross-sectional view of the connection between the ball seat and the machine body fixing platform of the present invention;

[0029] Fig.13 It is a cross-sectional view of the connection between the hemispherical seat and the sliding shaft of the present invention;

[0030] Fig.14 This is an axonometric view of the spring and the spring support arm of the present invention connected at the lower part of the sliding shaft.

[0031] In the figure, 1. test platform; 11. upper platform; 111. fuselage fixing platform; 1111. fixing hole; 112. ball seat; 1121. limit platform; 1122. ball shaft; 12. lower platform; 121. hemispherical seat; 1211. vertical edge; 1212. hemispherical groove; 1213. chamfer; 122. sliding shaft; 123. buffer block; 124. support frame; 1241. sliding shaft sleeve; 1242. support arm; 125. spring; 126. spring support arm; 127. locking pin; 13. bolt; 14. nut; 2. vertical drone. DETAILED DESCRIPTION

[0032] In order to make the technical means for realizing the present invention, the creative features, the objectives and effects to be achieved easy to understand, the present invention is further explained below in conjunction with specific diagrams. In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two components.

[0033] Example

[0034] like Figure 1As shown, the vertical drone 2 is fixed on the test platform 1, and a large number of fixing holes 1111 are designed on the fuselage fixing platform 111. Depending on the type of vertical drone, it can be fixed on different parts of the vertical drone. In this example, it is fixed on the landing gear. The number of fixing points is not less than 3, and it is necessary to meet the requirement that when the vertical drone 2 is in a horizontal state, the center of gravity of the aircraft falls on the area surrounded by the fixing points to prevent eccentricity. The height of the test platform 1 must meet the requirement that when the vertical drone 2 is in extreme deflection, there is a certain safety distance between any structure on the vertical drone 2 and the ground. In this example, it is set to 1 meter.

[0035] like Figure 2 and Figure 3 As shown, the test platform 1 includes an upper platform 11 and a lower platform 12. The upper platform 11 is installed on the lower platform 12. The connection position between the upper platform 11 and the lower platform 12 is located directly below the center of gravity when the vertical drone 2 is in a horizontal state, ensuring that the impact of the center of gravity shift is minimized during the flight test of the vertical drone 2.

[0036] like Figure 4 As shown, the upper platform 11 includes a body fixing platform 111 and a ball seat 112. The body fixing platform 111 is provided with a fixing hole 1111. According to different forms of the vertical UAV 2, different holders are designed to fix the vertical UAV 2 on the body fixing platform 111. The connection method between the body fixing platform 111 and the ball seat 112 is as follows: Fig.12 As shown, the ball seat 112 and the fuselage fixing platform 111 are connected together by bolts 13 and nuts 14. When the fuselage fixing platform 111 and the ball seat 112 are tested on the vertical UAV 2, they need to be driven by the propeller. In order to minimize the impact on the vertical UAV 2, a lightweight design needs to be considered. The fuselage fixing platform is made of aluminum alloy material, because the vertical UAV 2 needs to make a circular motion around the ball seat 112. Considering the wear resistance, the ball seat 112 is made of steel.

[0037] like Figure 6 As shown, the ball seat 112 includes a limit platform 1121 and a ball shaft 1122. The limit platform 1121 is arranged on the ball shaft 1122. The limit platform 1121 is determined according to the test requirements. According to the deflection angle requirement when testing the vertical drone 2, the deflection of the vertical drone 2 does not exceed the required angle. Because when the deflection angle of the vertical drone 2 is large, it will collide with the test platform 1, or the aircraft's blades, structure, tail wing, etc. will collide with the ground, causing damage to the vertical drone 2.

[0038] like Figure 8As shown, a large number of fixing holes 1111 arranged vertically and horizontally are designed on the fuselage fixing platform 111. Taking into account the applicability of the test platform 1, vertical take-off drones 2 of different types and sizes can be connected to different fixing holes 1111. At the same time, the position where the middle part is connected to the ball seat 112 transfers the weight of the entire aircraft and the test load to the ball seat 112.

[0039] like Figure 5 As shown, the lower platform 12 includes a hemispherical seat 121, a sliding shaft 122, a buffer block 123, a support frame 124, a spring 125, a spring arm 126, and a locking pin 127. There are two hemispherical seats 121, which are relatively installed on the top of the sliding shaft 122. The lower end of the ball seat 112 is installed in the two hemispherical seats 121. A buffer block 123 is installed in the middle of the sliding shaft 122. The lower end of the sliding shaft 122 is slidably installed in the support frame 124. A spring arm 126 is installed at the bottom of the sliding shaft 122. A spring 125 is installed between the spring arm 126 and the support frame 124. The spring 125 is sleeved on the sliding shaft 122 to fix the support frame 124 to the ground or other rigid structures to ensure the force requirements of the lower platform 12. The two hemispherical seats 121 are relatively assembled together and connected together by bolts. A hemispherical groove 1212 is opened on the hemispherical seat 121, and the ball shaft 1122 of the ball seat 112 is wrapped inside the hemispherical groove 1212. The hemispherical groove 1212 area needs to be larger than the volume of half a ball. In this way, after the assembly is completed, the ball shaft 1122 of the ball seat 112 will not fall out due to the action of tension, causing damage.

[0040] The sliding shaft 122 moves with the vertical drone 2 and is made of aluminum alloy. A flange is designed in the middle, and a buffer block 123 is installed under it. When the vertical drone 2 descends, the flange presses the buffer block 123 for buffering, reducing the overload of the vertical drone 2. The shaft in the middle can be a square shaft or a round shaft. A round shaft is preferably used, which can effectively reduce the friction of the up and down movement. At the same time, it can also rotate in the ring direction with the vertical drone, further releasing the freedom of movement of the vertical drone 2. The spring 125 needs to be designed according to the mass of the counterweight added to the vertical drone 2 during the test to ensure that it can meet the counterweight requirements within the design stroke.

[0041] like Figure 7As shown, the periphery of the hemispherical seat 121 is designed with a vertical edge 1211, and the end of the vertical edge 1211 is provided with a chamfer 1213 to avoid sharp edges at the free end, prevent wear with the ball shaft 1122 of the ball seat 112, and improve the service life. The vertical edge 1211 is used in conjunction with the limit platform 1121 of the ball seat 1122. When the vertical drone 2 deflects to the limit, the limit platform 1121 contacts the vertical edge 1211 to prevent the vertical drone 2 from continuing to increase in deflection. The ball shaft 1122 cooperates with the hemispherical groove 1212 of the hemispherical seat 121 to meet the rotation of the vertical drone 2 in the left and right, front and back, up and down, and circumferential directions. In order to improve the service life of the hemispherical seat 121, its material is steel. At the same time, there is a certain gap between the hemispherical groove 1212 and the ball shaft 1122 of the ball seat 112, and the interior is coated with grease, which is conducive to the movement of the ball shaft 1122 and reduces wear. The preferred gap is 0.3mm.

[0042] like Fig. 9 As shown, the support frame 124 includes a sliding sleeve 1241 and a support arm 1242. The support arm 1242 is installed on the side of the sliding sleeve 1241. The sliding shaft 122 is slidably installed inside the sliding sleeve 1241. The upper end of the support arm 1242 is welded to the sliding sleeve 1241, and the lower end is connected to the ground or a rigid structure to bear the force of the entire test process. Since the support frame 124 does not move with the vertical drone 2, it is made of a low-cost steel structure. The angle between the support arm 1242 and the ground or the rigid structure should be less than 90° minus the vertical drone limit deflection angle to prevent the vertical drone 2 from colliding with the support arm 1242 when deflecting, thereby damaging the vertical drone. At the same time, there are at least 3 support arms 1242 to ensure the stability of the support arms 1242. Preferably, 6 support arms are used, which are arranged at intervals of 60° and surround a circle. In this way, when the vertical drone 2 deflects in any direction, the force will be evenly dispersed by the support arm 1242. The force deviation of each support arm 1242 is too large when the vertical take-off drone 2 is in different states.

[0043] like Fig.10 and Fig.11 As shown, the hemispherical seat 121 wraps the ball seat 112 inside to prevent the ball seat 112 from falling out, wherein the extension line of the limit platform 1121 of the ball seat 112 and the extension line of the vertical edge 1211 of the hemispherical seat 121 pass through the center of the ball, and there is an angle between the two, which is the angle required for the test, and is 30° in this example. The advantage of the extension line passing through the center of the ball is that when the vertical drone deflects to the extreme angle, the limit platform 1121 and the vertical edge 1211 are in surface contact, with a large force-bearing area, thereby reducing the stress at the limit platform 1121 and the vertical edge 1211 to ensure that they are not damaged.

[0044] The sliding shaft 122 can move up and down in the sliding shaft sleeve 1241 of the support frame 124, and a gap is designed therebetween for its movement, and lubricating oil is applied thereto, and the preferred gap is 0.3 mm. A buffer block 123 is installed between the flange edge of the sliding shaft 122 and the sliding shaft sleeve 1241 to provide buffering when the vertically-lifted drone 2 falls, and the material of the buffer block 123 is selected from rubber.

[0045] A through hole with a spring arm 126 is provided at the lower part of the sliding shaft 122, and the spring arm 126 is installed inside the through hole. The spring 125 is installed between the lower part of the sliding shaft sleeve 1241 and the upper part of the spring arm 126. When the sliding shaft 122 moves upward, the spring 125 is compressed, and the spring 125 generates a compression force to achieve the purpose of balancing weight.

[0046] like Fig.12 , 13 As shown, the ball seat 112 and the machine body fixing platform 111, the hemispherical seat 1212 and the sliding shaft 122 are connected together by bolts 13 and nuts 14, which meet the function of being detachable during installation and can be easily replaced during maintenance.

[0047] like Fig.14 As shown, the spring support arm 126 can be in a square, round or other shape, preferably a square shape, so that the supporting surface for the spring 125 is a plane with a certain width, and the supporting effect is better. When the spring support arm 126 is installed in the sliding shaft 122, it is prevented from moving along the axial direction, causing the spring 125 to detach. A locking pin 127 is specially designed, and holes are opened on the other direction of the sliding shaft 122 and the spring support arm 126. The locking pin 127 is inserted into the hole to prevent the spring support arm 126 from moving.

[0048] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A vertical take-off unmanned aerial vehicle test platform, comprising an upper platform and a lower platform, characterized in that: The upper platform is installed on the lower platform, and the upper platform includes a body fixing platform, a fixing hole is opened on the body fixing platform, and the bottom of the body fixing platform is connected to the ball seat through a fixing piece, and the lower platform includes a hemispherical seat, and the hemispherical seat is provided with two, which are relatively installed on the top of the sliding shaft, and the lower end of the ball seat is installed in the two hemispherical seats, and a buffer block is installed in the middle of the sliding shaft, and the lower end of the sliding shaft is slidably installed inside the support frame, and a spring support arm is installed at the bottom of the sliding shaft, and a spring is installed between the spring support arm and the support frame, and the spring is sleeved on the sliding shaft.

2. A vertical take-off unmanned aerial vehicle test platform according to claim 1, characterized in that: The ball seat comprises a ball shaft, and a limiting platform is arranged on the ball shaft.

3. The vertical take-off unmanned aerial vehicle test platform according to claim 1, characterized in that: There are a plurality of fixing holes arranged vertically and horizontally on the machine body fixing platform.

4. The vertical take-off unmanned aerial vehicle test platform according to claim 2, characterized in that: A hemispherical groove is provided on the hemispherical seat, and the two hemispherical grooves are relatively distributed. The two hemispherical seats are connected by bolts, and the ball shaft is located inside the two hemispherical grooves. A small gap is provided between the hemispherical groove and the ball shaft, and the inside is coated with grease. A vertical edge is provided on the side of the hemispherical seat, and a chamfer is provided at the end of the vertical edge. The extension line of the limit platform of the ball seat and the extension line of the vertical edge of the hemispherical seat pass through the center of the ball.

5. The vertical take-off unmanned aerial vehicle test platform according to claim 1, characterized in that: The support frame comprises a sliding sleeve, a support arm is installed on the side of the sliding sleeve, the sliding shaft is slidably installed inside the sliding sleeve, and the spring is installed between the bottom end of the sliding sleeve and the spring support arm.

6. The vertical take-off unmanned aerial vehicle test platform according to claim 5, characterized in that: A flange edge is provided in the middle of the sliding shaft, and the buffer block is installed at the bottom of the flange edge.

7. The vertical take-off unmanned aerial vehicle test platform according to claim 5, characterized in that: A through hole is formed at the bottom of the sliding shaft, and the spring arm passes through the through hole and is fixed by a locking pin.

8. The vertical take-off unmanned aerial vehicle test platform according to claim 1, characterized in that: The fixing parts are bolts and nuts.

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