CN112285555A

CN112285555A - Fatigue test device of unmanned aerial vehicle power system

Info

Publication number: CN112285555A
Application number: CN202011025152.9A
Authority: CN
Inventors: 周东岳; 马聪; 孙恒盛; 郜奥林; 李振凯; 刘金来; 卢鹏; 闫波; 唐河森; 姜欣宏
Original assignee: Beijing Airlango Technology Co ltd
Current assignee: Beijing Airlango Technology Co ltd
Priority date: 2020-09-25
Filing date: 2020-09-25
Publication date: 2021-01-29
Anticipated expiration: 2040-09-25
Also published as: CN112285555B

Abstract

The utility model relates to a fatigue test device of unmanned aerial vehicle driving system for carry out fatigue test to the driving system who has N paddle, N is more than or equal to 2 natural number, fatigue test device includes reciprocating mechanism and is used for and corresponds N elastic component that sets up respectively with N paddle, reciprocating mechanism is used for making N elastic component all take place periodic deformation in order to exert alternating load to corresponding paddle, wherein satisfy, the phase difference of the periodic deformation of two elastic components that two adjacent paddles correspond is 360/N, in order to exert the alternating load that the phase difference is 360/N and the frequency is all not less than 1Hz to these two adjacent paddles. When flying the high frequency pneumatic load that the driving system received before the state before the simulation unmanned aerial vehicle, this fatigue test device of disclosure can output frequency and be not less than 1Hz alternating load, and test cycle is short, and the simulation is better, and the test accuracy is also higher.

Description

Fatigue test device of unmanned aerial vehicle power system

Technical Field

The utility model relates to an unmanned aerial vehicle tests technical field, specifically relates to a fatigue test device of unmanned aerial vehicle driving system.

Background

The fatigue testing technology is an important work for designing components of an unmanned aerial vehicle power system, mainly comprises testing of blades and power motors driving the blades, and has important significance for reliability of the unmanned aerial vehicle system.

However, the pneumatic load frequency simulated by the existing test bench is low, the pneumatic load of the unmanned aerial vehicle in the forward flying state is high-frequency alternating load, if the same fatigue failure degree is reached by simulation, the test needs a longer time, the period is long, the simulation of the existing test bench is poor, and the test accuracy is not high.

Disclosure of Invention

The purpose of the disclosure is to provide a fatigue test device for an unmanned aerial vehicle power system, which has a short test period and can effectively realize a fatigue test for the unmanned aerial vehicle power system.

In order to achieve the above object, the present disclosure provides a fatigue testing apparatus for an unmanned aerial vehicle power system, configured to perform a fatigue test on a power system having N blades, where N is a natural number greater than or equal to 2, the fatigue testing apparatus includes a reciprocating mechanism and N elastic members, where the N elastic members are arranged corresponding to the N blades, and the reciprocating mechanism is configured to cause the N elastic members to periodically deform so as to apply an alternating load to the corresponding blades, where a phase difference between the periodic deformations of two adjacent blades is 360 °/N, so as to apply an alternating load to the two adjacent blades, where the phase difference is 360 °/N and a frequency of the alternating load is not less than 1 Hz.

Optionally, the reciprocating mechanism includes N reciprocating units corresponding to the N elastic members one to one, the reciprocating frequency output by the N reciprocating units is not less than 1Hz, and the phase difference between two reciprocating units corresponding to every two adjacent paddles is 360 °/N.

Optionally, a power source of the reciprocating mechanism is a variable frequency motor, so that the frequency change of the alternating load is realized by adjusting the frequency conversion of the variable frequency motor.

Optionally, the reciprocating mechanism includes a rotating electrical machine and a slider-crank mechanism, a slider portion of the slider-crank mechanism is configured to correspond to the elastic member, a crank portion of the slider-crank mechanism is formed by a driving wheel, the driving wheel is in transmission connection with an output shaft of the rotating electrical machine, one end of a connecting rod is eccentrically hinged to the driving wheel, and the other end of the connecting rod is hinged to the slider portion.

Optionally, the sliding block portion includes a straight-line cylinder fixedly disposed and a sliding block slidable in the straight-line cylinder, a sliding rod extending from one end of the straight-line cylinder is disposed on the sliding block, the sliding rod is hinged to the connecting rod, and the elastic member is disposed in the straight-line cylinder and extends from the other end to correspond to the blade.

Optionally, the number of the rotating motors is one, the number of the slider-crank mechanisms is multiple, and the driving wheels in each slider-crank mechanism are connected through a synchronous transmission mechanism so as to reciprocate in the same step under the driving of one rotating motor.

Optionally, the number of the elastic members is two for testing a power system having two blades, the number of the slider-crank mechanisms is two, the driving wheels include a first driving wheel and a second driving wheel, the first driving wheel is coaxially connected with an output shaft of the rotating electrical machine, and the second driving wheel and the first driving wheel are configured as a sprocket, a pulley or a gear so as to be synchronously connected through the synchronous transmission mechanism configured as a chain drive, a belt drive or a gear drive.

Optionally, the resilient member comprises a coil spring.

Optionally, the fatigue testing device further comprises an adjusting mechanism capable of adjusting the preset elastic force of the elastic member on the blade.

Optionally, the fatigue testing apparatus further comprises a mounting bracket for mounting the power system, the reciprocating mechanism and the power system.

Optionally, the reciprocating mechanism comprises a linear cylinder and a sliding block reciprocating in the linear cylinder, the elastic part is arranged in the linear cylinder and extends out from the other end to correspond to the blade, and the linear cylinder is adjustably mounted on the mounting frame along the moving direction of the sliding block.

Optionally, the fatigue test device further comprises a mounting bracket, wherein the mounting bracket is constructed into an L-shaped plate structure, the L-shaped plate structure comprises a base and a mounting seat extending upwards from the base, the rotating motor, the driving wheel and the linear cylinder are respectively mounted on the mounting seat, and the mounting seat is further provided with a power system mounting part of the power system.

Optionally, the mounting seat includes a first mounting seat and a second mounting seat connected to the first mounting seat in a position-adjustable manner along a sliding direction of the slider, the rotating electrical machine and the driving wheel are mounted on the first mounting seat, the linear cylinder is mounted on the second mounting seat, and a power system mounting portion for mounting the power system is further provided on the second mounting seat.

In the technical scheme, the reciprocating motion of the reciprocating mechanism enables the N elastic pieces which are arranged in one-to-one correspondence with the N blades to generate periodic deformation, so that alternating load is applied to the corresponding blades, the frequency of the alternating load is not less than 1Hz, when the fatigue damage degree of a power system under the forward flying state of the unmanned aerial vehicle is simulated, a longer time does not need to be tested, and the test period is short; in addition, the elastic periodic deformation of the elastic piece can buffer the direct impact of the reciprocating mechanism on the paddle on one hand, so that the damage to the paddle is avoided, and the load applied to the paddle on the other hand is the alternating load of the paddle in the aerodynamic environment, so that the simulation is better, and the test accuracy is higher.

Additional features and advantages of the disclosure will be set forth in the detailed description which follows.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description serve to explain the disclosure without limiting the disclosure. In the drawings:

fig. 1 is a schematic view of a pneumatic environment simulation of an unmanned aerial vehicle with a single blade in a forward flight state;

FIG. 2 is a fatigue testing device for an unmanned aerial vehicle powertrain according to an embodiment of the present disclosure, wherein the fatigue testing device has two springs for testing a powertrain having two blades;

fig. 3 is a schematic structural diagram of a slider portion and an elastic member of a fatigue testing apparatus of an unmanned aerial vehicle power system according to an embodiment of the present disclosure.

Description of the reference numerals

1 reciprocating mechanism

121 slider portion 1211 linear cylinder

1212 slider 1213 slide bar

1214 flange 1215 slider body

1216 connecting block 1217 hinge hole

122 crank part 1221 first driving wheel

1222 second driving wheel 123 link

13 synchronous transmission mechanism 2 elastic element

21 helical spring 22 lug

211 small end 212 large end

3 mounting frame 31 base

32 mount 10 power motor

20 blade 100 power system

Detailed Description

The following detailed description of specific embodiments of the present disclosure is provided in connection with the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present disclosure, are given by way of illustration and explanation only, not limitation.

In the present disclosure, unless otherwise specified, the use of the directional terms such as "inside and outside" refers to the inside and outside of the specific structural profile, and the use of the directional terms such as "upper and lower" refers to the upper and lower defined in the use state of the fatigue testing device of the present disclosure, as specifically described with reference to fig. 2; the use of terms such as "first" and "second" is intended only to distinguish one element from another, and is not intended to be sequential or important.

Under the actual flight state of unmanned aerial vehicle, the pneumatic environment that blade 20 of driving system 100 and motor shaft of driving motor 10 received is complicated, consequently wants the result of fatigue test more accurate, needs the pneumatic environment that fatigue test device can simulate unmanned aerial vehicle flight in-process as far as possible.

The inventor of the present application finds that, in a forward flight process of the unmanned aerial vehicle, the pneumatic environment can refer to the simulation diagram shown in fig. 1, and during the process that the blade 20 rotates in the counterclockwise direction (only a single blade 20 is illustrated in fig. 1), the unmanned aerial vehicle (not shown) moves towards the left direction of the drawing plane under the driving of the blade 20; in the case of azimuth angles 90 °, 270 °, irrespective of the induced speed, the blades 20 in forward flight are at azimuth angles 90 ° and 270 °The average airspeeds are respectively:

and

wherein V is the forward flying speed, omega is the rotating speed,

the average airspeed of the individual blades 20 varies periodically along the azimuth angle for the aerodynamic mean radius. Aerodynamic force is proportional to the square of the space velocity, without taking into account the induced velocity. In the forward flight state, for the two-blade paddle, the aerodynamic lift force forms 2 times of frequency-conversion fluctuation, the bending moment of the paddle heel forms 1 time of frequency-conversion large-scale change, and the bending moment of the motor shaft forms 2 times of frequency-conversion bending moment.

In other words, the aerodynamic load in the forward flight process has the characteristics of high frequency (2 times of frequency conversion, about 150Hz for 6 kg-class unmanned aerial vehicles) and large value change. The pneumatic load frequency simulated by the conventional test board is below 0.5Hz, and the test board is required to test the flight time by 300 times to achieve the same fatigue failure degree, so that the period is long and the cost is high; in addition, the conventional test bench increases and reduces the fatigue aging test of the blades and the motor of the power system by periodically increasing and decreasing the accelerator, and the mode has poor simulation and low test accuracy.

Based on this, as shown in fig. 2, the present disclosure provides a fatigue testing device for an unmanned aerial vehicle propulsion system, which is used for performing a fatigue test on a propulsion system 100 having N blades 20, where N is a natural number greater than or equal to 2. The fatigue testing device comprises a reciprocating mechanism 1 and N elastic pieces 2 which are used for being respectively and correspondingly arranged with N blades 20, wherein the reciprocating mechanism 1 is used for enabling the N elastic pieces 2 to be periodically deformed so as to apply alternating load to the corresponding blades 20, and the phase difference of the periodic deformation of the two elastic pieces 2 corresponding to two adjacent blades 20 is 360 degrees/N so as to apply the alternating load with the phase difference of 360 degrees/N and the frequency of not less than 1Hz to the two adjacent blades 20.

It should be noted that the power system 100 of the unmanned aerial vehicle mainly includes power motors 10 and blades 20, the number of the power motors 10 is generally set to 1, and the number of the blades 20 is generally set to 2, 3, 4, 5, etc. In order to simulate as much as possible the aerodynamic load that the power system 100 receives in the flight state, especially in the forward flight state of the unmanned aerial vehicle, since a plurality of blades 20 are usually arranged at equal intervals in the circumferential direction, what needs to be ensured is that: the phase difference of the alternating load suffered by every two adjacent blades 20 is 360/N, wherein N is the number of the blades 20.

In the technical scheme, the reciprocating motion of the reciprocating mechanism 1 enables the N elastic parts 2 which are arranged corresponding to the N blades 20 one by one to generate periodic deformation, so that alternating load is applied to the corresponding blades 20, the frequency of the alternating load is not less than 1Hz, and compared with the conventional test bench, when the equivalent fatigue failure degree is simulated, the test bench can output the alternating load with higher frequency, effectively shorten the test period and improve the test efficiency; and the elastic periodic deformation of the elastic piece can buffer the direct impact of the reciprocating mechanism on the paddle on one hand, so that the damage to the paddle is avoided, and the load applied to the paddle on the other hand can be more suitable for the alternating load of the paddle in the aerodynamic environment, so that the simulation is better, and the test accuracy is higher.

In one embodiment, the reciprocating mechanism 1 may include N reciprocating units (not shown) corresponding to the N elastic members 2 one to one, the reciprocating frequencies output by the N reciprocating units are not less than 1Hz, and the phase difference between two reciprocating units corresponding to every two adjacent blades 20 is 360 °/N. The N reciprocating units can be mutually independent reciprocating units, each reciprocating unit is provided with an independent driving source, and when a certain reciprocating unit breaks down, the certain reciprocating unit is maintained; or, the N reciprocating units may share a driving source, and perform synchronous reciprocating motion by sharing one or several driving sources, and the phase difference between two reciprocating units corresponding to every two adjacent paddles 20 is 360 °/N. In addition, the reciprocating unit may be constructed in any suitable shape and structure that is effective to periodically deform the elastic member 2.

Alternatively, the power source of the reciprocating mechanism 1 may be an inverter motor with a relatively high frequency conversion so as to realize frequency variation of the alternating load by adjusting the frequency conversion of the inverter motor. In the embodiment, the frequency conversion motor has the characteristic of high frequency conversion, and the frequency conversion of the frequency-modulated frequency-converted motor can output the high-frequency alternating load which is the same as the frequency conversion of the frequency-converted motor. The adjusting mode is simple and the cost is low. The variable frequency motor may be configured as a variable frequency rotating motor or a variable frequency linear motor, which is not limited in the present disclosure.

For example, this fatigue test device of disclosure is when carrying out fatigue test to 6kg grades of unmanned aerial vehicle, and rotating electrical machines is chooseed for use to reciprocating mechanism 1's power supply. The frequency of the pneumatic load of the 6 kg-level unmanned aerial vehicle in the forward flying process is about 150Hz, when simulation is carried out, an operator adjusts the frequency of the rotating motor of the reciprocating mechanism 1 to 150Hz, namely the reciprocating motion frequency of the reciprocating mechanism 1 is adjusted to 150Hz, the periodic deformation of the elastic part 2 is also 150Hz, and then the alternating load with the frequency of 150Hz can be applied to the blades 20.

As shown in fig. 2, the reciprocating mechanism 1 may include a rotary motor and a slider-crank mechanism having a slider portion 121 for corresponding to the elastic member 2, a crank portion 122 of the slider-crank mechanism may be formed of a driving wheel drivingly connected to an output shaft of the rotary motor, and a connecting rod 123 having one end eccentrically hinged to the driving wheel and the other end hinged to the slider portion 121. When a fatigue test is performed, the output shaft of the rotating motor drives the driving wheel to periodically rotate, the periodic rotation of the driving wheel is converted into the periodic reciprocating motion of the slider part 121 through the conversion of the connecting rod 123 eccentrically connected with the driving wheel, the slider part 121 which reciprocates drives the elastic part 2 to periodically deform, and the elastic part 2 which periodically deforms applies alternating load to the blade. By providing the reciprocating mechanism 1 as a combination of a rotary motor and a slider-crank mechanism, the reciprocating mechanism 1 can improve the precision and the stability of the reciprocating motion, and can reduce the manufacturing cost, and in other embodiments, the reciprocating mechanism 1 can be configured as a linear motor (not shown) with a telescopic rod for applying an alternating load to the elastic member 2, and the present disclosure does not limit the specific type of the reciprocating mechanism 1.

Specifically, as shown in fig. 2, the slider portion 121 may include a straight cylinder 1211 fixedly disposed and a slider 1212 slidable in the straight cylinder 1211, the slider 1212 is provided with a sliding rod 1213 extending from one end of the straight cylinder 1211, the sliding rod 1213 is hinged to one end of the connecting rod 123 remote from the driving wheel, and the elastic member 2 is disposed in the straight cylinder 1211 and extends from the other end to correspond to the blade 20. Optionally, the radial dimension of the sliding rod 1213 is smaller than that of the connecting rod 123, so as to avoid friction with the inner wall of the linear cylinder 1211 during the reciprocating motion to affect the smoothness of the reciprocating motion. Alternatively, the slider 1212 may include a slider body 1215 for abutting against the elastic member 2, and a connecting block 1216 for connecting with the sliding bar 1213, the connecting block 1216 being provided with a hinge hole 1217 for hinge-connecting with the sliding bar 1213.

In particular, when mounted, one end of the elastic element 2 is intended to abut against the blade 20 of the power system 100, it being noted here that this abutment position may be situated from a position intermediate the blade 20 in the longitudinal direction to the tip of the blade 20, in order to simulate as far as possible the load conditions to which the blade 20 is subjected in the actual flight conditions. The other end of the elastic member 2 is inserted into the linear cylinder 1211 to abut against the slider 1212, and the elastic member 2 is always in a compressed state, and when the slider 1212 is located at a position farthest from the blade 20, the compression amount of the elastic member 2 is the minimum base compression amount, and at this time, the load applied to the blade 20 by the elastic member 2 is the minimum base load; when the slider 1212 is located closest to the blade 20, the compression amount of the elastic member 2 is maximized, and the load applied to the blade 20 by the elastic member 2 is maximized.

The elastic member 2 may be configured in any suitable shape and structure, which is not limited in the present disclosure, for example, it may be configured as a coil spring 21, and the elastic member 2 may also be configured as an elastic block or an elastic metal sheet, which can ensure that the elastic member does not break or lose elasticity during the periodic deformation, and moreover, the elastic member 2 of the present disclosure is not limited to include only an elastic body, but also may include a transition piece for conveniently abutting with other components, such as a transition piece assembled at the end of the elastic body, so as to contact with the blade 20 of the power system 100.

For example, in the present embodiment, as shown in fig. 2 and 3, the elastic member 2 may include a coil spring 21 and a projection 22 mounted on an end of the coil spring 21. The coil spring 21 is inside the linear cylinder 1211, and the projection 22 may be exposed outside the linear cylinder 1211 to contact the paddle 20. Specifically, the small end 211 of the projection 22 is exposed out of the linear cylinder 1211 to contact the paddle 20, and the large end 212 of the projection 22 is used to abut against the flange 1214 of the end of the linear cylinder 1211 away from the slider 1212, so as to prevent the projection 22 and the coil spring 21 from being removed from the linear cylinder 1211. The bump 22 may be made of any suitable material, such as an elastic rubber, for example, and the disclosure is not limited thereto.

In one embodiment, the rotary electric machine may be configured as one, and the slider-crank mechanism may be configured as a plurality of ones, and the drive wheels in each slider-crank mechanism are connected through the synchronous transmission mechanism 13 to reciprocate in steps by one rotary electric machine. In this embodiment, the driving source of the reciprocating mechanism 1 is only configured as a rotating electrical machine, and the plurality of slider-crank mechanisms realize synchronous reciprocating motion through the synchronous transmission mechanism 13, so that the structure is simple, the synchronous precision is high, and the control is convenient; in addition, the arrangement mode can effectively avoid arranging a plurality of rotating motors, and effectively saves the design cost. However, the problem of the phase difference of the plurality of crank slider mechanisms may be solved by connecting the links 123 of the plurality of driving slider mechanisms 12 to the driving wheel eccentrically at a constant arc in the circumferential direction of the driving wheel. For example, when the number of the crank-slider mechanisms is 3, the elastic member 2 is also configured to be 3, and the phase difference between two adjacent crank-slider mechanisms is 120 °, and the two connecting rods 123 in each two adjacent driving-slider mechanisms 12 can be eccentrically arranged on two driving wheels of the adjacent crank-slider mechanisms by 120 °.

Further, as shown in fig. 2, the elastic member 2 may be two for testing the power system 100 having two blades 20, the crank-slider mechanism is also correspondingly provided in two, the driving wheels may include a first driving wheel 1221 and a second driving wheel 1222, the first driving wheel 1221 is coaxially connected with the output shaft of the rotating electrical machine, the second driving wheel 1222 and the first driving wheel 1221 are configured as a sprocket, a pulley or a gear so as to be capable of being synchronously connected through the synchronous transmission mechanism 13 configured as a chain drive, a belt drive or a gear drive. When the fatigue test is performed on the power system 100 with two blades 20, the rotating motor drives the first driving wheel 1221 to rotate, so that the first connecting rod 123 connected with the first driving wheel 1221 drives the first slider 1212 to reciprocate, and the first elastic element 2 is periodically deformed to apply a first alternating load to the first blade 20; in addition, during the rotation of the first driving wheel 1221, under the driving of the synchronous transmission mechanism 13, the second driving wheel 1222 and the first driving wheel 1221 rotate synchronously, so that the second connecting rod 123 connected to the second driving wheel 1222 drives the second sliding block 1212 to reciprocate, and the second elastic element 2 deforms periodically to apply a second alternating load to the second blade 20. It is also desirable that the two crank-slider mechanisms are 180 ° out of phase, and that they can be eccentrically arranged by 180 ° by the two connecting rods 123 of the two crank-slider mechanisms on the first drive wheel 1221 and the second drive wheel 1222, respectively. The drive wheel is not limited to the above-described sprocket, pulley, or gear; the synchronous transmission 13 is also not limited to chain, belt or gear drives; the present disclosure is not limited thereto.

Optionally, the fatigue testing device of the present disclosure may further include an adjusting mechanism (not shown) capable of adjusting the preset elastic force of the elastic member 2 on the blade 20 to meet the requirements of the foundation load tests of different sizes. The adjustment mechanism may be configured in any suitable configuration or shape and is not limited by the present disclosure.

In addition, as shown in fig. 2, the fatigue testing apparatus may further include a mounting bracket 3 for mounting the power system 100, the reciprocating mechanism 1 and the unmanned aerial vehicle power system 100 for supporting and stabilizing. The mounting bracket 3 of the present disclosure may be configured in any suitable shape and configuration, without limitation. It should be noted that for different fatigue testing apparatuses with different numbers of blades 20, the mounting frame 3 also needs to be adapted or redesigned to meet the mounting requirements for different numbers of blades 20. In addition, the material of the mounting bracket 3 may be made of a rigid material meeting requirements, which is not limited in this disclosure. The mount bracket 3 may be provided with a power system mounting portion (not shown) for mounting the power system 100, and the power system mounting portion may be configured to have a power motor mounting groove (not shown) for mounting the power motor 10.

Further, unlike the fixed arrangement of the linear cylinder 1211, in another modification, the linear cylinder 1211 may be adjustably mounted on the mounting bracket 3 along the moving direction of the slider 1212, and the elastic member 2 may include a coil spring 21 and a protrusion 22 mounted on an end of the coil spring 21. The coil spring 21 is inside the linear cylinder 1211, the small end 211 of the projection 22 is exposed out of the linear cylinder 1211 to contact the paddle 20, and the large end 212 of the projection 22 is used to abut against the flange 1214 of the end of the linear cylinder 1211 remote from the slider 1212 to prevent the projection 22 and the coil spring 21 from being removed from the linear cylinder 1211.

Based on the above-mentioned modification, if the basic load of the elastic member 2 acting on the blade 20, that is, the basic compression amount of the coil spring 21, is to be adjusted according to the requirement of the test, the basic compression amount of the coil spring 21 can be adjusted by adjusting the position of the linear cylinder 1211 mounted on the mounting frame 3 in the moving direction of the slider 1212, and the following specific description is made:

for example, referring to fig. 2 and 3, when the base load of the elastic member 2 needs to be increased, that is, when the coil spring 21 needs to be compressed, the position of the linear cylinder 1211 on the mounting bracket 3 may be adjusted downward so that the flange 1214 at the upper end of the linear cylinder 1211 abuts against the large end 212 of the projection 22 and drives the projection 22 to move downward, thereby compressing the coil spring 21 disposed below the projection 22 to increase the base load acting on the blade 20. Correspondingly, the power system 100 provided on the mounting frame 3 should also be downwardly adjusted by the same amount as the linear cylinder 1211. Alternatively, when the base load of the elastic member 2 needs to be reduced, the positions of the linear cylinder 1211 and the power system 100 on the mounting frame 3 can be synchronously adjusted upward, and the detailed description is omitted here.

In one embodiment, as shown in FIG. 2, the fatigue testing apparatus shown is used to fatigue test a power system 100 having two blades 20. The mounting bracket 3 may be constructed in an L-shaped plate structure, which may include a base 31 and a mount 32 extending vertically upward from the base 31, and the rotary motor, the driving wheel, and the linear cylinder 1211 may be mounted on the mount 32, respectively. When the driving device is installed, a motor installation groove (not shown) may be formed on the installation base 32 for fixedly installing the above-mentioned rotating motor, the first driving wheel 1221 is connected with a motor shaft of the rotating motor, the second driving wheel 1222 may be rotatably installed on the installation base 32 through a bearing (not shown), and the second driving wheel 1222 may be synchronously connected with the first driving wheel 1221 through the above-mentioned synchronous transmission mechanism 13; the connecting rod 123 is disposed along the up-down direction, and the linear cylinder 1211 may be fixed on the mounting seat 32 or movably mounted on the mounting seat 32 along the up-down direction, which is not limited in the present disclosure.

Further, a power system mounting portion (not shown) for mounting power system 100 may be formed on mounting base 32, and power system 100 may be fixedly disposed on mounting base 32 or power system 100 may be movably mounted on mounting base 32 in the vertical direction. In the manner in which power system 100 is fixedly disposed, for example, the power system mounting portion may be configured as a power motor mounting slot (not shown) for fixedly disposing power motor 10 therein. In a manner that the power system 100 is movably mounted on the mounting seat 32, for example, the power system mounting portion may be formed as a slide rail structure (not shown) arranged along the up-down direction, and the power motor 10 of the power system 100 may be provided with a slider structure (not shown) for forming a sliding fit with the slide rail structure (not shown) so as to slide the power system 100 in the up-down direction.

Specifically, the mount 32 may include a first mount (not shown) on which the rotary motor and the driving wheel may be mounted, and a second mount (not shown) that is position-adjustably coupled above the first mount in the sliding direction of the slider 1212, on which the linear cylinder 1211 and the power system 100 may be mounted. For example, the first mounting seat and the second mounting seat may be connected by a lead screw nut assembly (not shown), a nut (not shown) may be fixedly disposed on the first mounting seat, a lead screw (not shown) penetrates through the nut to be connected with the second mounting seat, and a distance between the second mounting seat and the first mounting seat may be adjusted by rotating the lead screw, and at the same time, the second mounting seat may drive the linear cylinder 1211 and the power system 100 to compress or release the elastic member 2, so as to adjust a magnitude of a basic load acting on the blade 20, and the description process of adjusting the basic load of the elastic member 2 by the linear cylinder 1211 may refer to the above description.

Alternatively, in other embodiments, the linear cylinder 1211 and the power system 100 are both movably disposed on the mounting seat 32 in the vertical direction. For example, a first slide rail (not shown) and a second slide rail (not shown) may be disposed on the mounting seat 32 in the up-down direction, a first slider (not shown) engaged with the first slide rail may be disposed on the linear cylinder 1211, a second slider (not shown) may be disposed on a motor housing of the power motor 10 of the power system 100, and a driving mechanism (not shown) is configured to synchronously drive the first slider and the second slider to move on the first slide rail and the second slide rail, respectively, so as to compress and release the elastic element 2, and adjust the magnitude of the base load applied to the blade by the elastic element 2. The driving mechanism may be configured as a linear motor, a lead screw nut mechanism, a pneumatic cylinder, a hydraulic cylinder, etc., to which the present disclosure does not limit.

In other embodiments, adjustment of the base load on blade 20 may be achieved by adjusting only the sliding direction of power system 100 along slide block 1212. For example, the rotary motor, the driving wheel, and the linear cylinder 1211 may be mounted on a first mounting seat, the power system 100 may be mounted on a second mounting seat through a power system mounting portion, the second mounting seat is adjustably connected to the first mounting seat along a direction in which the slider 1212 moves up and down, the first mounting seat and the second mounting seat are connected through a screw nut assembly (not shown), a nut (not shown) may be fixedly disposed on the first mounting seat, a screw (not shown) passes through the nut and is connected to the second mounting seat, and a distance between the second mounting seat and the first mounting seat may be adjusted by rotating the screw nut, and at the same time, the second mounting seat drives the blade 20 on the power system 100 to compress or release the elastic member 2, so that a magnitude of a base load applied to the blade by the elastic member 2 may be adjusted.

When testing the use, base 31 of mounting bracket 3 is used for keeping flat to test platform (not shown) on to guarantee that fatigue test device is in stable state, avoid appearing rocking the condition such as in the test procedure.

The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.

It should be noted that, in the foregoing embodiments, various features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various combinations that are possible in the present disclosure are not described again.

In addition, any combination of various embodiments of the present disclosure may be made, and the same should be considered as the disclosure of the present disclosure, as long as it does not depart from the spirit of the present disclosure.

Claims

1. The fatigue testing device of the unmanned aerial vehicle power system is used for carrying out fatigue testing on a power system (100) with N blades (20), wherein N is a natural number which is more than or equal to 2, and is characterized by comprising a reciprocating mechanism (1) and N elastic pieces (2) which are used for being respectively and correspondingly arranged with the N blades (20), wherein the reciprocating mechanism (1) is used for enabling the N elastic pieces (2) to periodically deform so as to apply alternating load to the corresponding blades (20), and the phase difference of the periodic deformation of the two elastic pieces (2) corresponding to two adjacent blades (20) is 360 degrees/N so as to apply the alternating load with the phase difference of 360 degrees/N and the frequency of not less than 1Hz to the two adjacent blades (20).

2. The fatigue testing device of the unmanned aerial vehicle power system according to claim 1, wherein the reciprocating mechanism (1) comprises N reciprocating units corresponding to the N elastic members (2) one by one, the reciprocating frequency output by the N reciprocating units is not less than 1Hz, and the phase difference between two reciprocating units corresponding to every two adjacent blades (20) is 360 °/N.

3. The fatigue testing device of the unmanned aerial vehicle power system as claimed in claim 1, wherein the power source of the reciprocating mechanism (1) is a variable frequency motor, so as to realize the frequency change of the alternating load by adjusting the rotation frequency of the variable frequency motor.

4. The fatigue testing device of the unmanned aerial vehicle power system as claimed in claim 1, wherein the reciprocating mechanism (1) comprises a rotating electric machine and a slider-crank mechanism, a slider portion (121) of the slider-crank mechanism is adapted to correspond to the elastic member (2), a crank portion (122) of the slider-crank mechanism is formed by a driving wheel, the driving wheel is drivingly connected to an output shaft of the rotating electric machine, and a connecting rod (123) is eccentrically hinged to the driving wheel at one end and is hinged to the slider portion (121) at the other end.

5. The fatigue testing device of the unmanned aerial vehicle power system as claimed in claim 4, wherein the slider portion (121) comprises a fixedly disposed linear cylinder (1211) and a slider (1212) slidable in the linear cylinder (1211), the slider (1212) is provided with a sliding rod (1213) extending from one end of the linear cylinder (1211), the sliding rod (1213) is hinged to the link (123), and the elastic member (2) is disposed in the linear cylinder (1211) and extends from the other end to correspond to the blade (20).

6. The fatigue testing device for the unmanned aerial vehicle power system as claimed in claim 5, wherein the number of the rotating electric machines is one, the number of the slider-crank mechanisms is plural, and the driving wheels in each slider-crank mechanism are connected through a synchronous transmission mechanism (13) to reciprocate in steps under the driving of one of the rotating electric machines.

7. The fatigue testing device of the unmanned aerial vehicle power system as claimed in claim 6, wherein the elastic member (2) is two for testing a power system (100) having two blades (20), the crank block mechanism is two, the driving wheels include a first driving wheel (1221) and a second driving wheel (1222), the first driving wheel (1221) is coaxially connected with an output shaft of the rotating electrical machine, and the second driving wheel (1222) and the first driving wheel (1221) are configured as a sprocket, a pulley or a gear so as to be synchronously connected with the synchronous transmission mechanism (13) configured as a chain drive, a belt drive or a gear drive.

8. The fatigue testing device of the unmanned aerial vehicle power system as claimed in claim 1, wherein the elastic member (2) comprises a coil spring (21) and a projection (22) mounted on an end of the coil spring (21), the projection (22) being adapted to contact the blade (20) of the power system (100).

9. The fatigue testing device of the unmanned aerial vehicle power system according to claim 1 or 8, further comprising an adjusting mechanism capable of adjusting a preset elastic force of the elastic member (2) to the blade (20).

10. The fatigue testing device of the unmanned aerial vehicle power system according to any one of claims 1-8, further comprising a mounting bracket (3) for mounting the power system (100), the reciprocating mechanism (1) and the power system (100).

11. The fatigue testing apparatus of the unmanned aerial vehicle power system according to claim 10, wherein the reciprocating mechanism comprises a linear cylinder (1211) and a slider (1212) reciprocating in a linear motion in the linear cylinder (1211), the elastic member (2) is provided in the linear cylinder (1211) and extends from the other end to correspond to the blade (20), and the linear cylinder (1211) is position-adjustably mounted on the mounting bracket (3) along a moving direction of the slider (1212).

12. The fatigue testing device of the unmanned aerial vehicle power system of claim 7, further comprising a mounting bracket (3), wherein the mounting bracket (3) is configured as an L-shaped plate structure, the L-shaped plate structure comprises a base (31) and a mounting seat (32) extending vertically upwards from the base (31), the rotating motor, the driving wheel and the linear cylinder (1211) are respectively mounted on the mounting seat (32), and a power system mounting part of the power system (100) is further arranged on the mounting seat (32).

13. The fatigue testing apparatus for the unmanned aerial vehicle power system as claimed in claim 12, wherein the mount (32) comprises a first mount on which the rotating electrical machine and the driving wheel are mounted, and a second mount which is connected above the first mount in a position adjustable manner along a sliding direction of the slider (1212), and the linear cylinder (1211) is mounted on the second mount which is further provided with a power system mounting portion for mounting the power system (100).