Fatigue test device for inner shaft of unmanned aerial vehicle

Abstract

The utility model relates to a fatigue test device for an inner shaft of an unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and is used for solving the problems of complicated structure, high operation difficulty and high manufacturing cost of the fatigue test device for the inner shaft of the unmanned aerial vehicle in the prior art. The fatigue test device for the inner shaft of the unmanned aerial vehicle comprises a fixing assembly, a base, a transmission wheel, a speed reduction support assembly and an inclination assembly, the fixing assembly and the speed reduction support assembly are connected with the two ends of the base respectively, and the fixing assembly and the speed reduction support assembly are connected with the inner shaft of the unmanned aerial vehicle. The transmission wheel is connected with the speed reduction support assembly, and the inclination assembly is connected with the speed reduction support assembly. The fixing assembly comprises a fixing frame, a supporting piece, a waving spring and a fixing disc. The tilting assembly comprises a tilting connecting rod and a tilting disc, and the tilting disc is connected with the speed reduction support assembly through the tilting connecting rod. The device is simple in structure, convenient to operate and low in cost.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a fatigue test device for an inner shaft of a unmanned aerial vehicle. Background Art

[0002] Drones have the advantages of vertical take-off and landing, hovering in the air, constant speed cruising and strong wind resistance. They also have the characteristics of low cost of use, high safety performance and strong environmental adaptability. They perform outstandingly in tasks such as flying and filming.

[0003] The high-speed rotating parts of drones (inner shafts, gears, variable pitch shafts, etc.) are subjected to alternating and combined loads under high temperature and high pressure, which are very prone to low-cycle fatigue damage. Fatigue fracture is a common failure form of metal materials. Conducting fatigue tests on key components of drones is an important means to ensure the flight safety of drones.

[0004] In the prior art, fatigue testing of the inner shaft of a UAV needs to consider the effect of the periodic swinging of the UAV blades on the fatigue strength of the inner shaft. Therefore, fatigue testing devices for the inner shaft of a UAV generally have a complex load-bearing structure. In actual use, they have problems such as complex structure, difficult operation, and high manufacturing cost. Utility Model Content

[0005] In view of the above analysis, the utility model aims to provide a fatigue test device for the inner shaft of a UAV, so as to solve the problems of the fatigue test device for the inner shaft of a UAV in the prior art that the structure is complex, the operation is difficult and the production cost is high.

[0006] The purpose of this utility model is mainly achieved through the following technical solutions:

[0007] A fatigue test device for an inner shaft of a drone, comprising a fixing assembly, a transmission wheel, a reduction bracket assembly and a tilting assembly; the fixing assembly and the reduction bracket assembly are connected to the inner shaft of the drone, the transmission wheel is connected to the reduction bracket assembly, and the tilting assembly is connected to the reduction bracket assembly;

[0008] The fixing assembly includes a fixing frame, a support member, a flapping spring and a fixing plate;

[0009] The tilt assembly includes a tilt link and a tilt plate, and the tilt link connects the tilt plate with the deceleration bracket assembly.

[0010] Furthermore, it also includes a base, the fixing assembly and the deceleration bracket assembly are respectively connected to the two ends of the base; the fixing frame is connected to the base, the fixing plate is connected to the fixing frame, and the support member is connected to the fixing plate through the swinging spring.

[0011] Furthermore, the inner shaft passes through the fixed disk and is connected to the support member, and the support member is perpendicular to the inner shaft and can rotate with the inner shaft.

[0012] Furthermore, the fixed disk includes a disk, a locking piece, a fixing ring and a fixed bearing seat. The disk is an annular hollow groove structure. The disk is connected to the fixing frame. The locking piece, the fixing ring and the fixed bearing seat are arranged in the hollow groove of the disk.

[0013] Furthermore, the locking member includes a locking ring and a locking nut, the locking ring is sleeved with the inner shaft, the locking ring is connected to the swinging spring, the locking nut fixes the inner shaft in the locking ring, and the locking ring can rotate with the inner shaft.

[0014] Furthermore, the fixing ring is connected to the locking ring, the fixing ring rotates with the locking ring, and the inner ring of the fixed bearing seat is connected to the fixing ring and rotates with the fixing ring.

[0015] Furthermore, the fixed disk also includes a sealing plate, the outer ring of the fixed bearing seat is connected to the disc, the outer ring of the fixed bearing seat and the disc remain stationary relative to the fixed frame, the shape of the sealing plate matches the disc, and the sealing plate is connected to the disc.

[0016] Furthermore, the tilting plate includes a bearing seat connecting ring and a connecting rod, the inner ring of the bearing seat connecting ring is connected to the inner shaft and can rotate with the inner shaft, and the outer ring of the bearing seat connecting ring is connected to the connecting rod and remains stationary relative to the reduction bracket assembly.

[0017] Furthermore, the tilt connecting rod includes a bearing rod, a sleeve and a fixed rod, one end of the bearing rod is connected to the connecting rod through a bearing seat, and the other end is threadedly connected to the sleeve, one end of the fixed rod is connected to the deceleration bracket assembly, and the other end is threadedly connected to the sleeve.

[0018] Furthermore, the deceleration bracket assembly includes a bracket and a reducer, the reducer is connected to the bracket, and the transmission wheel is connected to the reducer.

[0019] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0020] (1) The fatigue test device for the inner shaft of a UAV of the utility model can change the tilt angle of the tilt plate by arranging a flapping spring and a tilting assembly so that the flapping spring is periodically stretched as the inner shaft rotates, thereby simulating the flapping motion generated when the UAV blades rotate. The utility model has a simple structure, is easy to operate, and has a low cost.

[0021] (2) By changing the screwing distance between the fixing rod and / or the bearing rod and the sleeve, the length of the tilting link can be adjusted, thereby adjusting the tilting angle of the tilting plate, thereby changing the stretching length of the flapping spring during stretching, controlling the force of the flapping spring on the inner shaft, and simulating the alternating impact load of the blade on the inner shaft. The simulated sudden impact load can be controlled without complicated operations.

[0022] (3) By setting a reducer, the inner shaft can be kept rotating at the working speed. By adjusting the tension of the swinging spring on the inner shaft, the alternating impact load on the inner shaft caused by the periodic swinging of the blades when the inner shaft is working can be simulated. The swinging motion of the blades can be simulated by the periodic stretching of the swinging spring as the inner shaft rotates. The operation is simple, the actual working condition of the inner shaft can be effectively restored, and the structure is stable.

[0023] (4) The fatigue test device for the inner shaft of a UAV of the utility model can simulate the actual working condition of the inner shaft to measure the fatigue strength of the inner shaft with a simple structure and at a low cost, thereby improving the accuracy of the fatigue test results, and the experimental conclusion has a high credibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The accompanying drawings are only used for the purpose of illustrating specific embodiments and are not to be considered as limiting the present invention. In the entire drawings, the same reference symbols represent the same components.

[0025] Figure 1 This is a schematic diagram of the overall structure of the fatigue test device for the inner shaft of a UAV of the utility model;

[0026] Figure 2 It is a structural schematic diagram of the fixing assembly of the utility model;

[0027] Figure 3 It is an exploded structural diagram of a fixing plate of a fixing assembly of the utility model;

[0028] Figure 4 It is a schematic diagram of the structure of the reduction bracket assembly connected with the transmission wheel and the tilting assembly of the utility model;

[0029] Figure 5 It is a structural schematic diagram of the tilting assembly of the utility model.

[0030] Reference numerals:

[0031] 1-fixed assembly; 11-fixed frame; 12-support rod; 13-swinging spring; 14-fixed plate; 141-disc; 142-locking piece; 1421-locking ring; 1422-locking nut; 143-fixed ring; 144-fixed bearing seat; 2-base; 3-transmission wheel; 4-reduction bracket assembly; 41-bracket; 42-reducer; 5-tilting assembly; 51-tilting connecting rod; 511-bearing rod; 512-sleeve; 513-fixed rod; 52-tilting plate; 521-bearing seat connecting ring; 522-connecting rod; 6-inner shaft. DETAILED DESCRIPTION

[0032] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0033] A specific embodiment of the utility model discloses a fatigue test device for an inner shaft of a drone, such as Figure 1 As shown, it includes a fixing component 1, a base 2, a transmission wheel 3, a reduction bracket component 4 and a tilting component 5. The fixing component 1 and the reduction bracket component 4 are respectively connected to the two ends of the base 2, the fixing component 1 and the reduction bracket component 4 are connected to the inner shaft 6 of the UAV, the transmission wheel 3 is connected to the reduction bracket component 4, the transmission wheel 3 can transmit the rotation of the motor to the reduction bracket component 4, the tilting component 5 is connected to the reduction bracket component 4, and the fatigue test device can simulate the swinging motion of the UAV blade by adjusting the tilting component 5.

[0034] like Figure 1-2 As shown, the fixing assembly 1 includes a fixing frame 11, a supporting member 12, a swinging spring 13 and a fixing plate 14. The fixing frame 11 is connected to the base 2, the fixing plate 14 is connected to the fixing frame 11, there are multiple swinging springs 13, the supporting member 12 is connected to the fixing plate 14 through the swinging spring 13, the inner shaft 6 passes through the fixing plate 14 and is connected to the supporting member 12, and the supporting member 12 is perpendicular to the inner shaft 6 and can rotate with the inner shaft 6.

[0035] like Figure 3As shown, the fixed disk 14 includes a disk 141, a locking member 142, a fixing ring 143, a fixing bearing seat 144 and a sealing plate 145. The disk 141 is an annular hollow groove structure. The disk 141 is connected to the fixing frame 11. The locking member 142, the fixing ring 143 and the fixing bearing seat 144 are arranged in the hollow groove of the disk 141. The locking member 142 includes a locking ring 1421 and a locking nut 1422. The locking ring 1421 is sleeved with the inner shaft 6. The locking ring 1421 is connected to the swing spring 13. The locking nut 1422 fixes the inner shaft 6 in the locking position. Inside the ring 1421, the locking ring 1421 can rotate with the inner shaft 6, the fixing ring 143 is connected to the locking ring 1421, the fixing ring 143 rotates with the locking ring 1421, the inner ring of the fixed bearing seat 144 is connected to the fixing ring 143 and rotates with the fixing ring 143, the outer ring of the fixed bearing seat 144 is connected to the disc 141, the outer ring of the fixed bearing seat 144 and the disc 141 remain stationary relative to the fixed frame 11, the shape of the sealing plate 145 matches the disc 141, the sealing plate 145 is connected to the disc 141, and is used to close the cavity of the disc 141.

[0036] like Figure 4 As shown, the reduction bracket assembly 4 includes a bracket 41 and a reducer 42, the bracket 41 is connected to the base 2, the reducer 42 is connected to the bracket 41, the transmission wheel 3 is connected to the reducer 42, the transmission wheel 3 can transmit the rotational motion of the motor to the reducer 42, the reducer 42 can adjust the speed transmitted by the transmission wheel 3, and transmit it to the inner shaft 6, so that the inner shaft 6 rotates according to the actual working speed. It should be noted that the transmission wheel 3 transmits the rotational motion of the motor to the reducer 42, and the speed of the transmission wheel 3 is adjusted by the reducer 42 and transmitted to the inner shaft 6 is a prior art, which will not be repeated here.

[0037] like Figure 4-5 When the tilt assembly 5 is in the state of being rotated, the tilt assembly 5 includes a tilt link 51 and a tilt plate 52. The tilt link 51 connects the tilt plate 52 to the reduction bracket assembly 4. There are multiple tilt links 51. The tilt link 51 includes a bearing rod 511, a sleeve 512 and a fixing rod 513. One end of the bearing rod 511 is connected to the tilt plate 52, and the other end is threadedly connected to the sleeve 512. One end of the fixing rod 513 is connected to the reducer 42, and the other end is threadedly connected to the sleeve 512. The length of the tilt link 51 can be adjusted by changing the screwing distance between the fixing rod 513 and / or the bearing rod 511 and the sleeve 512. The tilt plate 52 can be tilted by adjusting multiple tilt links 51 to different lengths.

[0038] The tilting plate 52 includes a bearing seat connecting ring 521 and a connecting rod 522. The inner ring of the bearing seat connecting ring 521 is connected to the inner shaft 6 and can rotate with the inner shaft. The outer ring of the bearing seat connecting ring 521 is connected to the connecting rod 522 and remains stationary relative to the reduction bracket assembly 4. The connecting rod 522 is connected to the bearing rod 511 through the bearing seat. The tilting angle of the bearing seat connecting ring 521 can be adjusted by adjusting the length of the tilting connecting rod 51.

[0039] When fatigue testing of the inner shaft 6 is required, the screwing distance between the fixing rod 513 and / or the bearing rod 511 and the sleeve 512 is adjusted to change the length of the tilting link 51, thereby changing the tilting angle of the bearing seat connecting ring 521, thereby adjusting the force of the swinging spring 13 on the inner shaft 6, starting the motor, making the transmission wheel 3 rotate with the motor and driving the inner shaft 6 to rotate at the working speed of the inner shaft 6 through the reducer 42, and the rotation of the inner shaft 6 causes the swinging spring 13 to stretch periodically, thereby simulating the swinging motion generated when the drone blades rotate, and simulating the working state of the inner shaft 6. By changing the length of multiple tilting links 51, the tilting angle of the bearing seat connecting ring 521 can be adjusted, thereby changing the stretching length of the swinging spring 13 when stretched, and controlling the force of the swinging spring 13 on the inner shaft 6.

[0040] Compared with the prior art, the fatigue test device for the inner shaft of a drone of the present invention can periodically stretch the swing spring 13 as the inner shaft 6 rotates by changing the tilt angle of the tilt plate 52 by setting the swing spring 13 and the tilt assembly 5, thereby simulating the swinging motion generated when the drone blades rotate, and has a simple structure, convenient operation and low cost; the length of the tilt link 51 can be adjusted by changing the screwing distance between the fixing rod 513 and / or the bearing rod 511 and the sleeve 512, and the tilt plate 52 can be tilted by making the lengths of the multiple tilt links 51 different; the tilt angle of the tilt plate 52 can be adjusted by adjusting the length of the tilt link 51 , thereby changing the stretching length of the swinging spring 13 when stretched, and controlling the force of the swinging spring 13 on the inner shaft 6; by setting the reducer 42, the inner shaft 6 can be kept rotating at the working speed to simulate the actual working condition of the inner shaft 6; the utility model can simulate the load effect of the blades on the inner shaft 6 when the inner shaft 6 is working by adjusting the pulling force of the swinging spring 13 on the inner shaft 6, and can simulate the swinging motion of the blades by the periodic stretching of the swinging spring 13 rotating with the inner shaft. The operation is simple, the actual working condition of the inner shaft 6 can be effectively restored, the structure is stable, and the accuracy of the fatigue test results can be improved by simulating the actual working condition of the inner shaft 6, and it has high credibility.

[0041] The above is only a preferred specific implementation of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. A fatigue test device for an inner shaft of a drone, characterized in that: The invention comprises a fixing assembly (1), a transmission wheel (3), a deceleration bracket assembly (4) and a tilting assembly (5); the fixing assembly (1) and the deceleration bracket assembly (4) are connected to an inner shaft (6) of a drone, the transmission wheel (3) is connected to the deceleration bracket assembly (4), and the tilting assembly (5) is connected to the deceleration bracket assembly (4); The fixing assembly (1) comprises a fixing frame (11), a supporting member (12), a swinging spring (13) and a fixing plate (14); The tilting assembly (5) comprises a tilting link (51) and a tilting plate (52), wherein the tilting link (51) connects the tilting plate (52) to the deceleration bracket assembly (4).

2. The fatigue test device for the inner shaft of a drone according to claim 1, characterized in that: It also includes a base (2), the fixing assembly (1) and the deceleration bracket assembly (4) are respectively connected to the two ends of the base (2); the fixing frame (11) is connected to the base (2), the fixing plate (14) is connected to the fixing frame (11), and the support member (12) is connected to the fixing plate (14) via the swinging spring (13).

3. The fatigue test device for the inner shaft of a drone according to claim 2, characterized in that: The inner shaft (6) passes through the fixed disk (14) and is connected to the support member (12); the support member (12) is perpendicular to the inner shaft (6) and can rotate with the inner shaft (6).

4. The fatigue test device for the inner shaft of a drone according to claim 2, characterized in that: The fixed disk (14) comprises a disk (141), a locking piece (142), a fixing ring (143) and a fixing bearing seat (144); the disk (141) is an annular hollow groove structure; the disk (141) is connected to the fixing frame (11); the locking piece (142), the fixing ring (143) and the fixing bearing seat (144) are arranged in the hollow groove of the disk (141).

5. The fatigue test device for the inner shaft of a drone according to claim 4, characterized in that: The locking member (142) comprises a locking ring (1421) and a locking nut (1422); the locking ring (1421) is sleeved with the inner shaft (6); the locking ring (1421) is connected to the swing spring (13); the locking nut (1422) fixes the inner shaft (6) in the locking ring (1421); and the locking ring (1421) can rotate with the inner shaft (6).

6. The fatigue test device for the inner shaft of a drone according to claim 5, characterized in that: The fixing ring (143) is connected to the locking ring (1421), and the fixing ring (143) rotates with the locking ring (1421); the inner ring of the fixed bearing seat (144) is connected to the fixing ring (143) and rotates with the fixing ring (143).

7. The fatigue test device for the inner shaft of a drone according to claim 6, characterized in that: The fixed disk (14) further comprises a sealing plate (145), the outer ring of the fixed bearing seat (144) is connected to the circular disk (141), the outer ring of the fixed bearing seat (144) and the circular disk (141) remain stationary relative to the fixed frame (11), the shape of the sealing plate (145) matches the circular disk (141), and the sealing plate (145) is connected to the circular disk (141).

8. The fatigue test device for the inner shaft of a drone according to claim 1, characterized in that: The tilting plate (52) comprises a bearing seat connecting ring (521) and a connecting rod (522), wherein the inner ring of the bearing seat connecting ring (521) is connected to the inner shaft (6) and can rotate with the inner shaft (6), and the outer ring of the bearing seat connecting ring (521) is connected to the connecting rod (522) and remains stationary relative to the reduction bracket assembly (4).

9. The fatigue test device for the inner shaft of a drone according to claim 8, characterized in that: The tilt connecting rod (51) comprises a bearing rod (511), a sleeve (512) and a fixing rod (513); one end of the bearing rod (511) is connected to the connecting rod (522) via a bearing seat, and the other end is threadedly connected to the sleeve (512); one end of the fixing rod (513) is connected to the deceleration bracket assembly (4), and the other end is threadedly connected to the sleeve (512).

10. The fatigue test device for the inner shaft of a drone according to any one of claims 1 to 9, characterized in that: The deceleration bracket assembly (4) comprises a bracket (41) and a reducer (42); the reducer (42) is connected to the bracket (41); and the transmission wheel (3) is connected to the reducer (42).

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