CN112285555B - Fatigue testing device of unmanned aerial vehicle power system - Google Patents
Fatigue testing device of unmanned aerial vehicle power system Download PDFInfo
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- CN112285555B CN112285555B CN202011025152.9A CN202011025152A CN112285555B CN 112285555 B CN112285555 B CN 112285555B CN 202011025152 A CN202011025152 A CN 202011025152A CN 112285555 B CN112285555 B CN 112285555B
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 48
- 230000007246 mechanism Effects 0.000 claims abstract description 77
- 238000012360 testing method Methods 0.000 claims abstract description 31
- 230000005540 biological transmission Effects 0.000 claims description 21
- 230000001360 synchronised effect Effects 0.000 claims description 13
- 230000033001 locomotion Effects 0.000 claims description 12
- 230000008859 change Effects 0.000 claims description 2
- 230000000737 periodic effect Effects 0.000 abstract description 11
- 238000004088 simulation Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
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- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/04—Housings; Supporting members; Arrangements of terminals
- G01R1/0408—Test fixtures or contact fields; Connectors or connecting adaptors; Test clips; Test sockets
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- General Physics & Mathematics (AREA)
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model relates to a fatigue test device of unmanned aerial vehicle power system for carry out fatigue test to the driving system that has N piece paddle, N is the natural number of more than or equal to 2, fatigue test device includes reciprocating mechanism and is used for the N elastic component that corresponds the setting with N piece paddle respectively, and reciprocating mechanism is used for making N elastic component all take place periodic deformation in order to apply alternating load to corresponding paddle, wherein satisfy, the phase difference of periodic deformation of two elastic components that two adjacent piece paddles correspond is 360/N, in order to apply the alternating load that the phase difference is 360/N and frequency is not less than 1Hz to this two adjacent paddles. When simulating the high-frequency pneumatic load that the power system received under the unmanned aerial vehicle forward flight state, the fatigue testing device of this disclosure can output the alternating load that frequency was not less than 1Hz, and test cycle is short, and the simulativity is better, and the test accuracy is also higher.
Description
Technical Field
The disclosure relates to the technical field of unmanned aerial vehicle testing, in particular to a fatigue testing device of an unmanned aerial vehicle power system.
Background
The fatigue test technology is an important work for the design of power system components of the unmanned aerial vehicle, and mainly comprises the test of the blades and the power motor for driving the blades, so that the fatigue test technology has important significance for the reliability of the unmanned aerial vehicle system.
However, the pneumatic load frequency of the simulation of the existing test bench is low, the pneumatic load of the unmanned aerial vehicle in the forward flight state is high-frequency alternating load, if the simulation is required to reach the same fatigue damage degree, the test is required to be performed for a long 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 fatigue testing device is short in testing period and capable of effectively achieving fatigue testing of the unmanned aerial vehicle power system.
In order to achieve the above-mentioned purpose, the present disclosure provides a fatigue testing device of an unmanned aerial vehicle power system, for performing fatigue testing on a power system having N blades, N being a natural number greater than or equal to 2, the fatigue testing device including a reciprocating mechanism and N elastic members for being respectively and correspondingly disposed with the N blades, the reciprocating mechanism being configured to cause the N elastic members to be periodically deformed to apply an alternating load to the corresponding blades, wherein a phase difference of the periodic deformations of two elastic members corresponding to two adjacent blades is 360 °/N, so as to apply an alternating load to the two adjacent blades, the phase difference of which is 360 °/N, and the frequency of which is not less than 1 Hz.
Optionally, the reciprocating mechanism includes N reciprocating units corresponding to the N elastic pieces one by 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 paddles is 360 °/N.
Optionally, the 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 of the variable frequency motor.
Optionally, the reciprocating mechanism comprises a rotating motor and a crank sliding block mechanism, a sliding block part of the crank sliding block mechanism is used for corresponding to the elastic piece, a crank part of the crank sliding block mechanism is formed by a driving wheel, the driving wheel is in transmission connection with an output shaft of the rotating motor, 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 sliding block part.
Optionally, the sliding block part comprises a linear cylinder body fixedly arranged and a sliding block capable of sliding in the linear cylinder body, a sliding rod extending from one end of the linear cylinder body is arranged on the sliding block, the sliding rod is hinged with the connecting rod, and the elastic piece is arranged in the linear cylinder body and extends from the other end of the linear cylinder body to correspond to the paddle.
Optionally, the number of the rotating motor is one, the number of the crank block mechanisms is multiple, and the driving wheel in each crank block mechanism is connected through a synchronous transmission mechanism so as to synchronously reciprocate under the drive of one rotating motor.
Optionally, the number of the elastic pieces is two, the number of the crank block mechanisms is two, the driving wheels comprise a first driving wheel and a second driving wheel, the first driving wheel is coaxially connected with an output shaft of the rotating motor, and the second driving wheel and the first driving wheel are configured as a chain wheel, a belt wheel or a gear, so that the synchronous transmission mechanisms which are configured as chain transmission, belt transmission or gear transmission can be synchronously connected.
Optionally, the elastic member includes a coil spring.
Optionally, the fatigue testing device further comprises an adjusting mechanism capable of adjusting a preset elastic force of the elastic piece on the blade.
Optionally, the fatigue testing device further comprises a mounting frame for mounting the power system, the reciprocating mechanism and the power system.
Optionally, the reciprocating mechanism includes a linear cylinder and a slider reciprocating in the linear cylinder, the elastic member is disposed in the linear cylinder and extends from the other end to correspond to the paddle, and the linear cylinder is adjustably mounted on the mounting frame along the movement direction of the slider.
Optionally, the fatigue testing device further comprises a mounting frame, the mounting frame is configured into an L-shaped plate-shaped structure, the L-shaped plate-shaped structure comprises a base and a mounting seat extending vertically upwards from the base, the rotating motor, the driving wheel and the linear cylinder are respectively mounted on the mounting seat, and a power system mounting part of the power system is further arranged on the mounting seat.
Optionally, the mount pad includes first mount pad and follows the slip direction position adjustable connection of slider is in the second mount pad of first mount pad top, the rotating electrical machines with the drive wheel is installed on the first mount pad, the sharp barrel is installed on the second mount pad, still be provided with on this second mount pad and be used for the installation driving system installation department of driving system.
According to the technical scheme, the N elastic pieces which are arranged in one-to-one correspondence with the N blades are periodically deformed through the reciprocating motion of the reciprocating mechanism, so that alternating load is applied to the corresponding blades, the frequency of the alternating load is not less than 1Hz, and when the fatigue damage degree of the power system in the forward flight state of the unmanned aerial vehicle is simulated, the power system does not need to be tested for a long time, 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 blade on one hand, avoid damaging the blade, and the load applied to the blade on the other hand is an alternating load which can be more attached to the blade in an aerodynamic environment, so that the simulation is better, and the testing accuracy is higher.
Additional features and advantages of the present disclosure will be set forth in the detailed description which follows.
Drawings
The accompanying drawings are included to provide a further understanding of the disclosure, and are incorporated in and constitute a part of this specification, illustrate the disclosure and together with the description serve to explain, but do not limit the disclosure. In the drawings:
FIG. 1 is a schematic diagram of a simulation of a pneumatic environment of a single blade of an unmanned aerial vehicle in a forward flight state;
FIG. 2 is a fatigue testing device for a power system of an unmanned aerial vehicle according to an embodiment of the present disclosure, wherein the fatigue testing device has two elastic members for testing a power system having two paddles;
fig. 3 is a schematic structural view of a slider portion and an elastic member of a fatigue testing device of an unmanned aerial vehicle power system according to an embodiment of the present disclosure.
Description of the reference numerals
1. Reciprocating mechanism
121. Linear cylinder of slider portion 1211
1212. Slide 1213 slide bar
1214. Flange 1215 slider body
1216. Hinge hole of connecting block 1217
122. Crank portion 1221 first drive wheel
1222. Second driving wheel 123 connecting rod
13. Elastic piece of synchronous transmission mechanism 2
21. Coil spring 22 bump
211. Small end 212 large end
3. Mounting rack 31 base
32. Mounting base 10 power motor
20. Blade 100 power system
Detailed Description
Specific embodiments of the present disclosure are described in detail below with reference to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating and illustrating the disclosure, are not intended to limit the disclosure.
In the present disclosure, unless otherwise specified, terms such as "inner and outer" are used to refer to the inner and outer of a particular structural profile, terms such as "upper and lower" are used to refer to the upper and lower directions defined by the fatigue testing device of the present disclosure in the use state, and reference is made specifically to fig. 2; the terms such as "first and second" are used merely to distinguish one element from another element and do not have order or importance.
In the actual flight state of the unmanned aerial vehicle, the pneumatic environments suffered by the blades 20 of the power system 100 and the motor shaft of the power motor 10 are complex, so that in order to obtain more accurate fatigue test results, the fatigue test device is required to simulate the pneumatic environments in the flight process of the unmanned aerial vehicle as much as possible.
The inventor of the present application found that, in the process of flying the unmanned aerial vehicle forward, the aerodynamic environment may refer to the simulation schematic diagram shown in fig. 1, and in the process of rotating the paddle 20 in the counterclockwise direction (only a single paddle 20 is schematically shown in fig. 1), the unmanned aerial vehicle (not shown) may move towards the left side of the drawing plane under the driving of the paddle 20; taking azimuth angles of 90 ° and 270 ° as an example, the average airspeeds of the blade 20 in the forward flight state at azimuth angles of 90 ° and 270 ° are respectively: And Wherein V is the forward flight speed, ω is the rotational speed,/>The average airspeed of individual blade 20 varies periodically along the azimuth angle for an aerodynamic average radius. If the induced velocity is not considered, aerodynamic force is proportional to the square of airspeed. In the forward flight condition, for two blades, aerodynamic lift will form 2-fold rotation fluctuation, which forms a 1-fold rotation moment to the heel of the blade, and a 2-fold rotation moment to the motor shaft.
In other words, the aerodynamic load during forward flight is characterized by high frequency (2 times of rotation frequency, about 150Hz for a 6kg class unmanned aerial vehicle), and large amplitude variation. The pneumatic load frequency simulated by the existing test bench is below 0.5Hz, so that the test bench is required to test 300 times of flight duration to achieve the same fatigue damage degree, and the test bench has long period and high cost; in addition, the existing test bench increases and reduces the pneumatic load to perform fatigue aging test on the blades and the motor of the power system by periodically adding and subtracting the accelerator, so that the simulation is poor and the test accuracy is low.
Based on this, as shown in fig. 2, the present disclosure provides a fatigue testing device for an unmanned aerial vehicle power system, which is used for performing fatigue testing on a power 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 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, the phase difference of the periodic deformation of the two elastic pieces 2 corresponding to two adjacent blades 20 is 360 degrees/N, and the alternating load with the phase difference of 360 degrees/N and the frequency of not less than 1Hz is applied to the two adjacent blades 20.
It should be noted that, the power system 100 of the unmanned aerial vehicle mainly includes the power motor 10 and the paddles 20, the number of the power motors 10 is generally set to 1, and the number of the paddles 20 is generally set to 2, 3, 4, 5, and so on. In order to simulate as much as possible the aerodynamic load to which the power system 100 is subjected in the flight state, in particular in the forward flight state, since the plurality of blades 20 are generally equally spaced in the circumferential direction, it is necessary to ensure that: each adjacent two of the blades 20 are subjected to an alternating load with a phase difference of 360/N, where N is the number of blades 20.
In the above technical solution, the reciprocating motion of the reciprocating mechanism 1 is used to make the N elastic members 2 arranged in one-to-one correspondence with the N blades 20 periodically deform, so that an alternating load is applied to the corresponding blades 20, and the frequency of the alternating load is not less than 1Hz, compared with the existing test bench, when simulating the same fatigue failure degree, the test bench can output an alternating load with a higher frequency, effectively shorten the test period, and improve the test efficiency; moreover, the elastic periodic deformation of the elastic piece can buffer the direct impact of the reciprocating mechanism on the blade on one hand, avoid damaging the blade, and the load applied to the blade on the other hand is an alternating load which can be more attached to the blade in an aerodynamic environment, so that the simulation is better, and the testing 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 by one, wherein 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. The N reciprocating units can be mutually independent reciprocating units, each reciprocating unit is provided with an independent driving source, and when one reciprocating unit fails, the reciprocating units can be maintained; or the N reciprocating units can share the driving source, and synchronously reciprocate by sharing one or a plurality of driving sources, and the phase difference of two corresponding reciprocating units of every two adjacent paddles 20 is 360 degrees/N. The reciprocation unit may be of any appropriate shape and structure, and may be configured to effectively deform the elastic member 2 periodically.
Alternatively, the power source of the reciprocating mechanism 1 may be a variable frequency motor having a higher frequency to achieve a frequency variation of the alternating load by adjusting the frequency of the variable frequency motor. In the embodiment, the characteristic of high frequency conversion of the variable frequency motor is utilized, and the high frequency alternating load which is the same as the frequency conversion of the variable frequency motor can be output by adjusting the frequency conversion of the variable frequency motor. The adjusting mode is simple and the cost is low. The variable frequency motor may be configured as either a variable frequency rotating motor or a variable frequency linear motor, as this disclosure is not limited in this respect.
For example, in the fatigue testing device of the present disclosure, when performing fatigue testing on a 6 kg-class unmanned aerial vehicle, a rotating motor is selected as the power source of the reciprocating mechanism 1. The frequency of the pneumatic load of the 6 kg-level unmanned aerial vehicle in the forward flying process is about 150Hz, and when simulation is carried out, an operator can adjust the reciprocating motion frequency of the reciprocating mechanism 1 to 150Hz by adjusting the rotating frequency of the rotating motor of the reciprocating mechanism 1 to 150Hz, the periodic deformation of the elastic piece 2 is also 150Hz, and then the alternating load with the frequency of 150Hz can be applied to the blade 20.
As shown in fig. 2, the reciprocating mechanism 1 may include a rotary motor and a slider-crank mechanism, a slider portion 121 of which is adapted to correspond to the elastic member 2, a crank portion 122 of which 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 the fatigue test is carried out, the output shaft of the rotating motor drives the driving wheel to periodically rotate, the periodic rotation of the driving wheel is converted into periodic reciprocating motion of the sliding block part 121 through the conversion of the connecting rod 123 eccentrically connected with the driving wheel, the sliding block part 121 in the reciprocating motion drives the elastic piece 2 to periodically deform, and the elastic piece 2 subjected to the periodic deformation applies alternating load to the blade. By providing the reciprocating mechanism 1 in a combined form of a rotary motor and a crank block mechanism, while improving the accuracy and stability of the reciprocating motion, the manufacturing cost can be reduced, and in other embodiments, the reciprocating mechanism 1 may also be configured as a linear motor (not shown) whose telescopic rod is used to apply an alternating load to the elastic member 2, and the specific type of the reciprocating mechanism 1 is not limited in the present disclosure.
Specifically, as shown in fig. 2, the slider portion 121 may include a linear cylinder 1211 fixedly provided and a slider 1212 slidable in the linear cylinder 1211, the slider 1212 being provided with a slide bar 1213 extending from one end of the linear cylinder 1211, the slide bar 1213 being hinged to one end of the link 123 remote from the driving wheel, and an elastic member 2 being provided in the linear cylinder 1211 and extending from the other end to correspond to the paddle 20. Optionally, the radial dimension of the slide rod 1213 is smaller than the radial dimension of the connecting rod 123, so that friction with the inner wall of the linear cylinder 1211 during the reciprocating motion is avoided to influence the stability of the reciprocating motion. Alternatively, the slider 1212 may include a slider body 1215 for abutting against the elastic member 2 and a connection block 1216 for connecting with the slide rod 1213, the connection block 1216 being provided with a hinge hole 1217 for hinge-connecting with the slide rod 1213.
In particular, when the mounting is performed, one end of the elastic member 2 is used to abut against the blade 20 of the power system 100, and it should be noted here that the abutting position may be located from an intermediate position of the blade 20 in the length direction to a tip of the blade 20, so as to simulate as much as possible the load condition to which the blade 20 is subjected in the actual flight state. The other end of the elastic element 2 extends into the linear cylinder 1211 for abutting against the sliding block 1212, and the elastic element 2 is always in a compressed state, when the sliding block 1212 is at a position farthest from the blade 20, the compression amount of the elastic element 2 is the minimum base compression amount, and at the moment, the load applied by the elastic element 2 to the blade 20 is the minimum base load; the compression of the elastic member 2 is maximized when the slider 1212 is positioned closest to the paddle 20, and the load applied to the paddle 20 by the elastic member 2 is maximized.
The elastic member 2 may be configured in any suitable shape and structure, and the present disclosure is not limited thereto, and may be configured as a coil spring 21, for example, the elastic member 2 may be configured as an elastic block or an elastic metal sheet, etc., so as to ensure that the elastic member is not broken or lost during the periodic deformation, and furthermore, the elastic member 2 of the present disclosure is not limited to include only an elastic body, but may include a transition member for conveniently interfacing with other components, for example, a transition member assembled at an end of the elastic body, so as to be in 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 at an end of the coil spring 21. The coil spring 21 is inside the linear cylinder 1211, and the protrusion 22 may be exposed outside the linear cylinder 1211 to be in contact with the paddle 20. Specifically, the small end 211 of the boss 22 exposes the linear cylinder 1211 to contact the paddle 20, and the large end 212 of the boss 22 is configured to abut the flange 1214 of the end of the linear cylinder 1211 remote from the slider 1212 to prevent the boss 22 and the coil spring 21 from being disengaged from the linear cylinder 1211. The tab 22 may be made of any suitable material, such as an elastomeric rubber, to which the present disclosure is not limited.
In one embodiment, the rotating motor may be configured as one, the crank block mechanism may be configured as a plurality of crank block mechanisms, and the driving wheels in each crank block mechanism are connected through the synchronous transmission mechanism 13 to synchronously reciprocate under the drive of one rotating motor. In the embodiment, the driving source of the reciprocating mechanism 1 is only constructed as a rotary motor, and the plurality of crank block 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. The problem of the phase difference of the plurality of slider-crank mechanisms may be achieved by connecting the connecting rod 123 of the plurality of slider-crank mechanisms to the driving wheel eccentrically along the circumferential direction of the driving wheel with a certain arc difference. For example, when the number of slider-crank mechanisms is 3, the number of the elastic members 2 is also 3, and the phase difference between the adjacent two slider-crank mechanisms is 120 °, the two connecting rods 123 in each of the adjacent two slider-crank mechanisms may be eccentrically arranged on the two driving wheels of the adjacent slider-crank 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, and the crank block mechanism may be correspondingly provided as two, and the driving wheels may include a first driving wheel 1221 and a second driving wheel 1222, the first driving wheel 1221 being coaxially connected to the output shaft of the rotary electric machine, the second driving wheel 1222 being configured as a sprocket, a pulley or a gear with the first driving wheel 1221 so as to be synchronously connected by a synchronous transmission mechanism 13 configured as a chain transmission, a belt transmission or a gear transmission. When the power system 100 with two paddles 20 is subjected to fatigue test, 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 sliding block 1212 to reciprocate, and the first elastic element 2 is periodically deformed to apply a first alternating load to the first paddles 20; in addition, during the rotation of the first driving wheel 1221, the second driving wheel 1222 and the first driving wheel 1221 are synchronously rotated by the synchronous transmission mechanism 13, so that the second connecting rod 123 connected to the second driving wheel 1222 drives the second slider 1212 to reciprocate, and the second elastic element 2 is periodically deformed to apply a second alternating load to the second blade 20. In addition, it is also required that the phase difference of the two slider-crank mechanisms is 180 °, and the two connecting rods 123 in the two slider-crank mechanisms may be arranged eccentrically by 180 ° on the first drive wheel 1221 and the second drive wheel 1222, respectively. The drive wheel is not limited to the sprocket, pulley or gear described above; the synchronous drive 13 is also not limited to a chain drive, belt drive or gear drive; the present disclosure is not limited in this regard.
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 base load testing requirements of different sizes. The adjustment mechanism may be configured in any suitable structure or shape, which is not limited by the present disclosure.
In addition, as shown in fig. 2, the fatigue testing device may further include a mounting frame 3 for mounting the power system 100, the reciprocating mechanism 1 and the unmanned power system 100, so as to perform a supporting and stabilizing function. The mounting 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 devices having different numbers of paddles 20, the mounting frame 3 also needs to be adapted or redesigned to the structure to meet the mounting requirements for different numbers of paddles 20. In addition, the material of the mounting frame 3 may be made of a rigid material which meets requirements, which is not limited in the present disclosure. The mount 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 by a power motor mounting groove (not shown) for mounting the power motor 10.
Further, in another modification, the linear cylinder 1211 may be mounted on the mounting frame 3 so as to be position-adjustable 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, unlike the manner in which the linear cylinder 1211 is fixedly provided. The coil spring 21 is within the linear cylinder 1211, the small end 211 of the tab 22 exposes the linear cylinder 1211 to contact the paddle 20, and the large end 212 of the tab 22 is configured to abut the flange 1214 of the end of the linear cylinder 1211 remote from the slider 1212 to prevent the tab 22 and the coil spring 21 from being disengaged from the linear cylinder 1211.
Based on the above-mentioned deformation mode, 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 test requirement, the adjustment of the basic compression amount of the coil spring 21 can be achieved by adjusting the position of the linear cylinder 1211 mounted on the mounting frame 3 in the moving direction of the slide 1212, which specifically is described as follows:
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 frame 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 bump 22 and drives the bump 22 to move downward, thereby compressing the coil spring 21 disposed under the bump 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 adjusted downward by the same adjustment amount as the linear cylinder 1211. Or 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 may be adjusted upward synchronously, and detailed description is omitted herein.
In one embodiment, as shown in FIG. 2, the fatigue testing apparatus shown is used to perform a fatigue test on a power system 100 having two blades 20. The mounting frame 3 may be constructed in an L-shaped plate-like structure, which may include a base 31 and a mounting seat 32 extending vertically upward from the base 31, and the rotary motor, the driving wheel, and the linear cylinder 1211 may be respectively mounted on the mounting seat 32. In the mounting, a motor mounting groove (not shown) may be formed in the mounting base 32 for fixedly mounting the rotating motor, the first driving wheel 1221 is connected to a motor shaft of the rotating motor, the second driving wheel 1222 may be rotatably mounted on the mounting base 32 through a bearing (not shown), and the second driving wheel 1222 may be synchronously coupled to the first driving wheel 1221 through the synchronous transmission mechanism 13; the link 123 is disposed in the up-down direction, and the linear cylinder 1211 may be fixed to the mount 32 or may be movably mounted to the mount 32 in the up-down direction, which is not limited in this disclosure.
The mount 32 may be provided with a power system mounting portion (not shown) for mounting the power system 100, which may fix the power system 100 to the mount 32 or may mount the power system 100 to the mount 32 so as to be movable in the up-down direction. In the manner in which the power system 100 is fixedly disposed, for example, the power system mounting portion may be configured as a power motor mounting groove (not shown) for fixedly disposing the power motor 10 therein. In the manner in which the power system 100 is movably mounted to the mount 32, for example, the power system mounting portion may be formed as a slide rail structure (not shown) arranged in the up-down direction, and a slider structure (not shown) for forming a sliding fit with the slide rail structure (not shown) to slide the power system 100 in the up-down direction may be provided on the power motor 10 of the power system 100.
Specifically, the mounting base 32 may include a first mounting base (not shown) on which the rotating electric machine and the driving wheel may be mounted, and a second mounting base (not shown) on which the linear cylinder 1211 and the power system 100 may be mounted, which are position-adjustably connected in a sliding direction of the slider 1212. For example, the first mount and the second mount may be connected by a screw-nut assembly (not shown), a nut (not shown) may be fixedly disposed on the first mount, a screw (not shown) may be connected to the second mount through the nut, a distance between the second mount and the first mount may be adjusted by rotating the screw, and at the same time, the second mount 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 base load acting on the blade 20, and an explanation process for adjusting the base load of the elastic member 2 by the linear cylinder 1211 may be described above.
Alternatively, in other embodiments, both the linear cylinder 1211 and the power system 100 are movably disposed on the mount 32 in the up-down direction. For example, a first slide rail (not shown) and a second slide rail (not shown) that are disposed along an up-down direction may be disposed on the mounting base 32, a first slide block (not shown) that mates with the first slide rail may be disposed on the linear cylinder 1211, a second slide block (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 used to synchronously drive the first slide block and the second slide block to move on the first slide rail and the second slide rail, respectively, so as to compress and release the elastic member 2, and adjust a magnitude of a base load that the elastic member 2 acts on the blade. The drive mechanism may be configured as a linear motor, a screw nut mechanism, a pneumatic cylinder, a hydraulic cylinder, or the like, which is not limited by the present disclosure.
In other embodiments, adjustment of the base load on the blade 20 may also be accomplished by merely adjusting the sliding direction of the power system 100 along the slider 1212. For example, the rotating 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 may be adjustably connected to the first mounting seat along a direction of up-and-down movement of the slider 1212, the first mounting seat and the second mounting seat may be 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) may be connected to the second mounting seat through the nut, a distance between the second mounting seat and the first mounting seat may be adjusted by rotating the screw, 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, thereby adjusting a magnitude of a base load applied to the blade by the elastic member 2.
When in test use, the base 31 of the mounting frame 3 is used for being horizontally placed on a test platform (not shown) so as to ensure that the fatigue test device is in a stable state and avoid the conditions of shaking and the like in the test process.
The preferred embodiments of the present disclosure have been described in detail above with reference to the accompanying drawings, but the present disclosure is not limited to the specific details of the embodiments described above, and various simple modifications may be made to the technical solutions of the present disclosure within the scope of the technical concept of the present disclosure, and all the simple modifications belong to the protection scope of the present disclosure.
In addition, the specific features described in the foregoing embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, the present disclosure does not further describe various possible combinations.
Moreover, any combination between the various embodiments of the present disclosure is possible as long as it does not depart from the spirit of the present disclosure, which should also be construed as the disclosure of the present disclosure.
Claims (11)
1. The fatigue test device of the unmanned aerial vehicle power system is used for carrying out fatigue test on a power system (100) with N blades (20), N is a natural number greater than or equal to 2, and is characterized by comprising a reciprocating mechanism (1) and N elastic pieces (2) which are respectively and correspondingly arranged with the 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), the reciprocating mechanism (1) comprises a rotary motor and a plurality of crank slider mechanisms, a slider part (121) of each crank slider mechanism is used for being corresponding to the elastic pieces (2), a crank part (122) of each crank slider mechanism is formed by a driving wheel, the driving wheel is in transmission connection with an output shaft of the rotary motor, one end of a connecting rod (123) is eccentrically hinged with the driving wheel, the other end of each driving wheel in the crank slider mechanism is hinged with the slider part (121) through a synchronous transmission mechanism (13) so as to enable the driving wheels in the crank slider mechanisms to be connected with the rotary motor to carry out circumferential phase difference between the two adjacent crank slider parts (20) in a certain phase difference of the two adjacent crank slider parts (360 degrees, so as to apply an alternating load to the adjacent two blades (20) with a phase difference of 360 DEG/N and a frequency of not less than 1 Hz.
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 pieces (2) one by one, the reciprocating frequency output by the N reciprocating units is not less than 1Hz, and the phase difference of two reciprocating units corresponding to every two adjacent paddles (20) is 360 °/N.
3. The fatigue testing device of the unmanned aerial vehicle power system according to claim 1, wherein the power source of the reciprocating mechanism (1) is a variable frequency motor, so that the frequency change of the alternating load is realized by adjusting the frequency of the variable frequency motor.
4. The fatigue testing device of an unmanned aerial vehicle power system according to claim 1, wherein the slider portion (121) includes a straight cylinder (1211) fixedly provided and a slider (1212) slidable in the straight cylinder (1211), a slide bar (1213) extending from one end of the straight cylinder (1211) is provided on the slider (1212), the slide bar (1213) is hinged to the link (123), and the elastic member (2) is provided in the straight cylinder (1211) and extends from the other end to correspond to the paddle (20).
5. The fatigue testing device of an unmanned aerial vehicle power system according to claim 4, wherein the number of the elastic members (2) is two for testing the power system (100) having two paddles (20), the number of 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 to the output shaft of the rotating electric machine, and the second driving wheel (1222) is configured as a sprocket, a pulley or a gear to be synchronously connected to the first driving wheel (1221) by the synchronous transmission mechanism (13) configured as a chain transmission, a belt transmission or a gear transmission.
6. The fatigue testing device of an unmanned aerial vehicle power system according to claim 1, wherein the elastic member (2) comprises a coil spring (21) and a projection (22) mounted at an end of the coil spring (21), the projection (22) being adapted to be in contact with the blade (20) of the power system (100).
7. The fatigue testing device of an unmanned aerial vehicle power system according to claim 1 or 6, further comprising an adjusting mechanism capable of adjusting a preset elastic force of the elastic member (2) to the blade (20).
8. Fatigue testing device of an unmanned aerial vehicle power system according to any of claims 1-6, further comprising a mounting frame (3) for mounting the power system (100), the reciprocator (1) and the power system (100).
9. The fatigue testing device of an unmanned aerial vehicle power system according to claim 8, wherein the reciprocation mechanism comprises a linear cylinder (1211) and a slider (1212) that reciprocates in the linear cylinder (1211), the elastic member (2) is provided in the linear cylinder (1211) and protrudes from the other end to correspond to the paddle (20), and the linear cylinder (1211) is position-adjustably mounted on the mounting frame (3) along a movement direction of the slider (1212).
10. The fatigue testing device of an unmanned aerial vehicle power system according to claim 5, further comprising a mounting frame (3), the mounting frame (3) being configured as an L-shaped plate-like structure comprising a base (31) and a mounting seat (32) extending vertically upwards from the base (31), the rotating electric machine, the driving wheel and the linear cylinder (1211) being mounted on the mounting seat (32) respectively, the mounting seat (32) being further provided with a power system mounting portion of the power system (100).
11. The fatigue testing device of an unmanned aerial vehicle power system according to claim 10, wherein the mount (32) comprises a first mount and a second mount position-adjustably connected above the first mount in a sliding direction of the slider (1212), the rotary electric machine and the drive wheel being mounted on the first mount, the linear cylinder (1211) being mounted on the second mount, the second mount being further provided with a power system mounting portion for mounting the power system (100).
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