UAV lift test platform

Abstract

The present invention discloses a lift test platform for unmanned aerial vehicles, including a scissor table mechanism, a vertical base, a counterweight, an electronic scale, a fixed bracket and a control system. The scissor table mechanism includes an upper platform, a lower platform and two pairs of cross bars, which are arranged between the upper platform and the lower platform, and the upper platform and the lower platform are self-balanced with the center of the cross bars as the fulcrum; two vertical bases are located on both sides of the scissor table mechanism, and the pins in the middle of the cross bars are supported by the vertical bases; the counterweight is arranged on the upper end surface of the lower platform; the lower end surface of the lower platform is pressed on the scale plate of the electronic scale; the electronic scale is electrically connected to the control system; the fixed bracket is arranged on the upper end surface of the upper platform for connecting with the unmanned aerial vehicle. Compared with the prior art, the present invention has the advantages that the lift of the unmanned aerial vehicle in the working state can be easily tested, the test result has a small error, and has good compatibility.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicle flight performance testing, and in particular to an unmanned aerial vehicle lift testing platform. Background Art

[0002] At present, rotary-wing UAVs are used in many fields such as aerial photography, agriculture, and police security. Lift characteristics, as one of the important flight performance parameters of rotary-wing UAVs, directly affect the load weight and work efficiency of the UAV. However, there are few standardized testing methods and evaluation standards for the lift characteristics of rotary-wing UAVs.

[0003] Traditional rotor UAV lift test devices usually use a lever test method, which has disadvantages such as complex structure, large errors caused by lift loss, inability to simulate the vertical take-off and landing of the entire UAV, and poor compatibility. It is difficult to provide support for the evaluation and optimization of the UAV lift characteristics.

[0004] Therefore, it is necessary to improve it. Summary of the invention

[0005] In view of the shortcomings of the prior art, the purpose of the present invention is to provide a UAV lift test platform with simple structure, ease of use, small test result error and good compatibility.

[0006] In order to achieve the above purpose, the following technical solutions are provided:

[0007] An unmanned aerial vehicle lift test platform, characterized by comprising:

[0008] A scissors table mechanism, the scissors table mechanism comprises an upper platform, a lower platform and two pairs of cross rods, each pair of cross rods comprises two rods, the middle parts of the two rods are movably hinged by a pin shaft, the two pairs of cross rods are arranged in parallel and at intervals, the lower end surface of the upper platform is provided with two parallel and spaced upper slide grooves, the upper end surface of the lower platform is correspondingly provided with two parallel and spaced lower slide grooves, the upper end of the cross rod is embedded in the upper slide groove, the lower end of the cross rod is embedded in the lower slide groove, the upper end of the cross rod can slide freely along the length direction of the upper slide groove, and the lower end of the cross rod can slide freely along the length direction of the lower slide groove;

[0009] Two vertical bases, which are located on both sides of the scissor table mechanism, and the pin shaft in the middle of the cross rod is supported by the vertical bases;

[0010] A counterweight block, the counterweight block is arranged on the upper end surface of the lower platform;

[0011] An electronic scale, wherein the lower end surface of the lower platform is pressed against a scale pan of the electronic scale;

[0012] a control system, the electronic scale being electrically connected to the control system; and

[0013] A fixed bracket is arranged on the upper end surface of the upper platform, and the fixed bracket is used to be connected to the drone.

[0014] Optionally, the upper platform and the lower platform are of equal weight.

[0015] Optionally, the weight of the counterweight is adjusted by adding or removing weights. When the weight of the counterweight is equal to the total weight of the fixed bracket and the fixed belt assembly, the test object is the net lift of the drone; when the weight of the counterweight is equal to the total weight of the drone, the fixed bracket and the fixed belt assembly, the test object is the total lift of the drone.

[0016] Optionally, the counterweight block is connected to the lower platform via bolts.

[0017] Optionally, the fixed bracket includes an octagonal frame and a connecting rod extending outward from the center of the frame to its vertex.

[0018] Optionally, it also includes a fixing strap assembly for mounting the UAV on the fixing bracket, the fixing strap assembly including a fixing strap and a belt tightener, the inner end of the fixing strap is fixed to the connecting rod by bolts and nuts, the middle part of the fixing strap presses the UAV onto the fixing bracket, the outer end of the fixing strap is locked by the belt tightener, and the belt tightener is fixed to the connecting rod by bolts and nuts.

[0019] Optionally, the pin shaft is a stud bolt, which includes a middle plain rod portion and threaded portions at both ends of the plain rod portion. The plain rod portion of the stud bolt is inserted into the cross rod, and the threaded portions at both ends of the stud bolt are provided with nuts for limiting the cross rod.

[0020] After adopting the above structure, the advantages of the present invention compared with the prior art are: the upper platform and the lower platform of the present invention are self-balanced with the center of the cross rod as the fulcrum, the weight of the counterweight block is balanced with the total weight of the fixed bracket and the fixed belt assembly, the lift of the drone will be directly reflected as the pressure acting on the electronic scale, the test result has a small error, and has good compatibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a structural schematic diagram of the UAV lift test platform of the present invention;

[0022] Figure 2 It is an exploded schematic diagram of the UAV lift test platform of the present invention;

[0023] Figure 3 The figure is an exploded schematic diagram of the fixing bracket of the UAV lift test platform and the UAV of the present invention. DETAILED DESCRIPTION

[0024] The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0025] Embodiment 1, refer to Figures 1 to 3 The UAV lift test platform provided by the present invention includes a vertical base 7, a scissor table mechanism 3, an electronic scale 5, a fixed bracket 4 and a control system 1.

[0026] The scissors table mechanism 3 includes an upper platform 31, a lower platform 32 and two pairs of cross rods 33, each pair of cross rods 33 includes two rods, the middle parts of the two rods are movably hinged by a pin shaft 71, and the two rods of the cross rod 33 can rotate around the pin shaft 71 in the middle. The two pairs of cross rods 33 are arranged in parallel and at intervals. The lower end surface of the upper platform 31 is provided with two parallel and spaced upper slide grooves 310, and the upper end surface of the lower platform 32 is correspondingly provided with two parallel and spaced lower slide grooves 320. The upper end of the cross rod 33 is embedded in the upper slide groove 310, and the lower end of the cross rod 33 is embedded in the lower slide groove 320. The upper end of the cross rod 33 can slide freely along the length direction of the upper slide groove 310, and the lower end of the cross rod 33 can slide freely along the length direction of the lower slide groove 320.

[0027] There are two vertical bases 7, which are located on both sides of the scissor table mechanism. The pin 71 in the middle of the cross bar 33 is supported by the vertical base 7.

[0028] The lower end surface of the lower platform 32 is pressed against the scale plate of the electronic scale 2. The electronic scale 2 can continuously record data. The electronic scale 2 is electrically connected to the control system 1 to record the pressure of the electronic scale. When the drone takes off and drives the fixed bracket 4 and the upper platform 31 to move upward, the two rods of the cross rod 33 rotate around the pin 71 in the middle, and the upper ends of the two rods of the cross rod 33 slide along the length direction of the upper slide groove 310 and approach each other. The lower ends of the two rods of the cross rod 33 slide along the length direction of the lower slide groove 320 and approach each other. The upper platform 31 and the lower platform 32 are self-balanced with the center of the cross rod 33 as the fulcrum. The lift of the drone 6 will be directly reflected as the pressure acting on the electronic scale 2.

[0029] The fixing bracket 4 is installed on the upper end surface of the upper platform 31 , and the fixing bracket 4 is used to be connected to the drone 6 .

[0030] The pin 71 is a stud bolt. The stud bolt includes a middle polished rod portion and threaded portions at both ends of the polished rod portion. The polished rod portion of the stud bolt is inserted into the cross rod 33. The threaded portions at both ends of the stud bolt are sleeved with nuts to limit the cross rod 33.

[0031] The weight of the upper platform 31 and the lower platform 32 of the scissor table mechanism is equal, and the upper platform 31 and the lower platform 32 are self-balanced with the center of the cross bar 33 as the fulcrum, and a counterweight block 5 is arranged on the lower platform 32. The weight of the counterweight block can be adjusted by adding or removing weights according to actual conditions.

[0032] The center of the upper platform 31 of the scissor table mechanism is provided with a threaded hole, and the center of the fixed bracket 4 is connected to the upper platform 31 by bolts. The fixed bracket 4 includes an octagonal frame 41 and a connecting rod 42 extending outward from the center of the frame 41 to its vertex. The drone 6 is mounted on the fixed bracket 4 through a fixing belt assembly.

[0033] The fixing belt assembly includes a fixing belt 101, a belt tightener 103, bolts and nuts. The inner end of the fixing belt 101 is fixed to the connecting rod 42 by bolts and nuts, the middle part of the fixing belt 101 passes around the fuselage of the UAV and presses the UAV onto the fixing bracket 4, and the outer end of the fixing belt 101 is locked by the belt tightener 103, and the belt tightener 103 is fixed to the connecting rod 42 by bolts and nuts.

[0034] Before the test, the weight of the entire UAV and the weight of the components such as the fixed bracket 4, the fixed belt 101, and the belt tightener 103 are measured to determine the weight of the counterweight 5. When the weight of the counterweight 5 is equal to the total weight of the fixed bracket 4 and the fixed belt assembly, the test object is the net lift of the UAV; when the weight of the counterweight 5 is equal to the total weight of the UAV, the fixed bracket 4 and the fixed belt assembly, the test object is the total lift of the UAV.

[0035] During the test, the drone is started, and the lift of the drone drives the fixing belt assembly, the fixing bracket 4 and the upper platform 31 to move upward. The upper platform 31 and the lower platform 32 are self-balanced with the center of the cross bar 33 as the fulcrum, and the lift of the drone will be directly reflected as the pressure acting on the electronic scale 2. The lift of the drone is controlled by the drone controller, and when the lift of the drone reaches the maximum value and remains for a period of time, the maximum lift of the drone can be determined by the data recorded by the control system 1.

[0036] The above contents are only preferred embodiments of the present invention. For ordinary technicians in this field, according to the concept of the present invention, there will be changes in the specific implementation methods and application scopes. The content of this specification should not be understood as limiting the present invention.

Claims

1. An unmanned aerial vehicle lift test platform, characterized in that: include: A scissors table mechanism, the scissors table mechanism comprises an upper platform, a lower platform and two pairs of cross rods, each pair of cross rods comprises two rods, the middle parts of the two rods are movably hinged by a pin shaft, the two pairs of cross rods are arranged in parallel and at intervals, the lower end surface of the upper platform is provided with two parallel and spaced upper slide grooves, the upper end surface of the lower platform is correspondingly provided with two parallel and spaced lower slide grooves, the upper end of the cross rod is embedded in the upper slide groove, the lower end of the cross rod is embedded in the lower slide groove, the upper end of the cross rod can slide freely along the length direction of the upper slide groove, and the lower end of the cross rod can slide freely along the length direction of the lower slide groove; Two vertical bases, which are located on both sides of the scissor table mechanism, and the pin shaft in the middle of the cross rod is supported by the vertical bases; A counterweight block, the counterweight block is arranged on the upper end surface of the lower platform; An electronic scale, wherein the lower end surface of the lower platform is pressed against a scale pan of the electronic scale; a control system, the electronic scale being electrically connected to the control system; and A fixed bracket is arranged on the upper end surface of the upper platform, and the fixed bracket is used to be connected to the drone.

2. The UAV lift test platform according to claim 1, characterized in that: The upper platform and the lower platform have the same weight.

3. The UAV lift test platform according to claim 1, characterized in that: The weight of the counterweight block is adjusted by adding or reducing weights.

4. The UAV lift test platform according to claim 1, characterized in that: The counterweight block is connected to the lower platform via bolts.

5. The UAV lift test platform according to claim 1, characterized in that: The fixing bracket includes an octagonal frame and a connecting rod extending outward from the center of the frame to its apex.

6. The UAV lift test platform according to claim 5, characterized in that: It also includes a fixing belt assembly for mounting the UAV on the fixing bracket, the fixing belt assembly includes a fixing belt and a belt tightener, the inner end of the fixing belt is fixed to the connecting rod by bolts and nuts, the middle part of the fixing belt presses the UAV onto the fixing bracket, the outer end of the fixing belt is locked by the belt tightener, and the belt tightener is fixed to the connecting rod by bolts and nuts.

7. The UAV lift test platform according to any one of claims 1 to 6, characterized in that: The pin shaft is a stud bolt, which includes a middle plain rod portion and threaded portions at both ends of the plain rod portion. The plain rod portion of the stud bolt is inserted into the cross rod, and the threaded portions at both ends of the stud bolt are sleeved with nuts for limiting the cross rod.

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