CN117074017A - Load test device of helicopter speed reducer - Google Patents
Load test device of helicopter speed reducer Download PDFInfo
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- CN117074017A CN117074017A CN202311323709.0A CN202311323709A CN117074017A CN 117074017 A CN117074017 A CN 117074017A CN 202311323709 A CN202311323709 A CN 202311323709A CN 117074017 A CN117074017 A CN 117074017A
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 45
- 238000012360 testing method Methods 0.000 title claims abstract description 34
- 238000001514 detection method Methods 0.000 claims abstract description 39
- 230000005540 biological transmission Effects 0.000 claims abstract description 10
- 238000000926 separation method Methods 0.000 claims abstract description 8
- 230000004323 axial length Effects 0.000 claims description 7
- 230000000712 assembly Effects 0.000 claims description 2
- 238000000429 assembly Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000012546 transfer Methods 0.000 abstract description 2
- 238000003825 pressing Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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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
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
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- 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
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/32—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring the deformation in a solid
Abstract
The utility model discloses a load test device of a helicopter speed reducer, which belongs to the technical field of production equipment of the helicopter speed reducer, and comprises a frame, a speed reducer to be detected, a power mechanism, a transmission separation mechanism and a load detection mechanism, wherein the speed reducer to be detected is provided with a speed reducer gear box and a rotating shaft assembly, the rotating shaft assembly is connected with the power mechanism, the rotating shaft assembly is connected with the speed reducer gear box, and the speed reducer gear box is fixedly arranged on the frame; the transfer separation mechanism is provided with a movable frame and a state switching assembly, the state switching assembly is arranged on the movable frame, and the movable frame is in sliding connection with the frame; the load detection mechanism is provided with hydraulic equipment, an electric cylinder and a detection assembly, wherein the electric cylinder is fixedly arranged on the side surface of the frame, the telescopic end of the electric cylinder is fixedly connected with the movable frame, the hydraulic equipment is slidably arranged on the side surface of the movable frame, and the rotating shaft assembly is connected with the detection assembly.
Description
Technical Field
The utility model relates to the technical field of helicopter speed reducer production equipment, and particularly discloses a load test device of a helicopter speed reducer.
Background
With the increasing demands on helicopter performance, the transmission system of the helicopter retarder must meet a number of critical requirements, such as high life, high reliability, high efficiency, low noise, etc. To verify and ensure achievement of these requirements, a large number of bench test studies are necessary for performance testing of the decelerator. Generally, helicopter reducers comprise a set of transmission shafts for input torque, a set of main rotor shafts and a set of tail rotor shafts. In order to simulate different flight conditions, various bench tests are required, and various performance data of the speed reducer can be obtained through the tests, and potential faults are found and removed, so that an improved basis is provided for the design of the speed reducer.
However, the existing helicopter speed reducer load test apparatus has some problems. First, they cannot simultaneously simulate the installation stability of the fuselage truss, the endurance test of the main rotor, and the inertial rotation endurance test after the main rotor and tail rotor clutches are disconnected. Thus, to fulfill these different test requirements, a plurality of different test devices are required, which results in complexity of the detection process and is not convenient enough to use.
Based on the problems, a novel helicopter speed reducer load test device is provided. The device aims at solving the limitation of the existing device and realizing the integration of a plurality of test requirements. Through this device, can simulate the installation steadiness of helicopter fuselage truss, the endurance test of main rotor, inertial rotation endurance test after main rotor and tail rotor clutch disconnection. In this way, the testing process can be greatly simplified, the efficiency can be improved, and the number and complexity of the testing devices can be reduced.
The utility model discloses a load test device of a helicopter speed reducer, which is disclosed in Chinese patent publication No. CN217730825U, and the technical scheme of the utility model is as follows: the main reducer to be tested is fixedly arranged on the bracket. The output end of the motor is horizontally connected with a clutch switch and a free travel clutch to the right, and then is connected to a transmission shaft of the main speed reducer to be tested. The output end of the main rotor shaft auxiliary motor is vertically and downwards connected to a first hydraulic clutch at the tail end of a main rotor shaft of the main speed reducer to be tested. The output end of the tail rotor shaft auxiliary motor is horizontally connected to the left on a second hydraulic clutch at the tail rotor shaft tail end of the main speed reducer to be tested. A main rotor shaft of the main speed reducer to be tested is provided with a load applying point, an X-axis pressing cylinder is used for pressing the load applying point in the left-right direction, a Y-axis pressing cylinder is used for pressing the load applying point in the up-down direction, and a Z-axis pressing cylinder is used for pressing the load applying point in the front-back direction.
Disclosure of Invention
Aiming at the technical problems, the utility model adopts the following technical scheme: the utility model provides a load test device of helicopter reduction gear, includes frame, treats detect reduction gear, power unit, transmission separating mechanism and load detection mechanism, treat to detect the reduction gear be provided with reduction gear box and axis of rotation subassembly, axis of rotation subassembly link to each other with power unit, axis of rotation subassembly and reduction gear box link to each other, reduction gear box fixed mounting is in the frame.
The transmission separating mechanism is provided with a movable frame and a state switching assembly, the state switching assembly is arranged on the movable frame, the movable frame is in sliding connection with the frame, and connection and disconnection between the power mechanism and the rotating shaft assembly are realized through the state switching assembly.
The load detection mechanism is provided with hydraulic equipment, an electric cylinder and a detection assembly, the electric cylinder is fixedly arranged on the side face of the frame, the telescopic end of the electric cylinder is fixedly connected with the movable frame, the hydraulic equipment is slidably arranged on the side face of the movable frame, the rotating shaft assembly is connected with the detection assembly, the hydraulic equipment is connected with the detection assembly, and the detection assembly is arranged on the side face of the movable frame.
Further, axis of rotation subassembly be provided with main rotor shaft, input shaft and tail rotor shaft, main rotor shaft, input shaft and tail rotor shaft link to each other with the reduction gear box respectively, power unit be provided with first motor, second motor and third motor, first motor and main rotor shaft between link to each other through the state switching subassembly, second motor and input shaft between link to each other through the state switching subassembly, third motor and tail rotor shaft between link to each other through the state switching subassembly.
Further, main rotor shaft, input shaft and tail rotor shaft on all be provided with spline and shape size unanimity, first motor, second motor and third motor output all be provided with spline and shape size unanimity, main rotor shaft and first motor on spline shape size unanimity, every state switching component all be provided with the telescopic shaft, the telescopic shaft install in the movable frame side, telescopic shaft one end fixed mounting have fixed sleeve, fixed sleeve inner wall on rotate and install and remove the sleeve, fixed sleeve and remove sleeve coaxial.
Further, the inner wall of the movable sleeve is provided with a chute, the shape of the chute of the inner wall of the movable sleeve is consistent with that of a spline of the third motor, the direction of the central line of the chute of the inner wall of the movable sleeve is parallel to the direction of the axis of the movable sleeve, and the chute of the inner wall of the movable sleeve penetrates through the inner wall of the movable sleeve.
Further, the first motor and the main rotor shaft end face between leave the clearance, the second motor and the input shaft end face between leave the clearance, the third motor and the tail rotor shaft end face between leave the clearance, foretell each clearance distance equals, the axial length of moving sleeve be greater than foretell clearance length, the axial length of moving sleeve be greater than fixed sleeve's axial length, when the electric cylinder shrinkage reaches maximum, moving sleeve's spout breaks away from main rotor shaft, input shaft and the spline on the tail rotor shaft.
Further, the detection assembly is provided with three, each detection assembly is provided with a force application rod, the force application rods are communicated with the hydraulic equipment, the axial direction of each force application rod is perpendicular to the axial directions of the main rotor shaft, the input shaft and the tail rotor shaft respectively, and one end face of each force application rod is hemispherical.
Further, each of the detecting assemblies is further provided with a moving plate, each moving plate is mounted on one side of the main rotor shaft, the input shaft and the tail rotor shaft, which is far away from the force application rod, and each moving plate is tangent to the outer surfaces of the main rotor shaft, the input shaft and the tail rotor shaft.
Further, the side fixed mounting that removes the frame towards the reduction gear box have two L shape pieces, every L shape piece side be provided with the spout, every two sides of movable plate are provided with a cylindrical protrusion respectively, the cylindrical protruding slidable mounting of movable plate is in the spout of L shape piece, the cylindrical protruding surface rotation of movable plate install the second connecting rod, the one end that the L shape piece was kept away from to the second connecting rod install the slider in the rotation, slider slidable mounting at the side of removing the frame, slider side rotate and install first connecting rod, the one end that the slider was kept away from to the first connecting rod rotate with hydraulic equipment and be connected.
Further, in the initial state, the distance between the slider and the hydraulic device is smaller than the distance between the slider and the moving plate.
Compared with the prior art, the utility model has the beneficial effects that: (1) According to the utility model, load detection is carried out on each position of each rotating shaft through the matching of the rotating shaft assembly and the detection assembly; (2) According to the utility model, the load detection of each position of each rotating shaft is realized through the cooperation of the state switching assembly and the detection assembly, the bending degree of the rotating shaft is monitored in the detection process, and the monitoring is stopped when the bending degree is overlarge; (3) According to the utility model, the rotating states and the static states of the rotating shafts are detected through the cooperation of the rotating shaft assembly and the state switching assembly.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model.
Fig. 2 is a front view of the overall structure of the present utility model.
Fig. 3 is a side view of the overall structure of the present utility model.
Fig. 4 is a schematic structural view of a rotating shaft assembly according to the present utility model.
Fig. 5 is an enlarged schematic view of the structure at a in fig. 4.
FIG. 6 is a schematic diagram of a detecting assembly according to the present utility model.
Fig. 7 is an enlarged schematic view of the structure at B in fig. 6.
Fig. 8 is a schematic structural diagram of a state switching component according to the present utility model.
Fig. 9 is an enlarged schematic view of fig. 8 at C.
Figure 10 is a schematic diagram of the positional relationship of the speed reducer gearbox, main rotor shaft, input shaft, and tail rotor shaft of the present utility model.
Fig. 11 is an enlarged schematic view of the structure of fig. 10 at D.
Reference numerals: 1-a frame; 2-a speed reducer to be detected; 3-a power mechanism; 4-a transfer separation mechanism; 5-a load detection mechanism; 201-a reducer gearbox; 202-main rotor shaft; 203-an input shaft; 204-tail rotor shaft; 301-a first motor; 302-a second motor; 303-a third motor; 401-a mobile rack; 402-telescoping shaft; 403-a limit frame; 404-fixing the sleeve; 405-moving the sleeve; 406-a baffle; 407-slide slots; 501-a hydraulic device; 502-an electric cylinder; 503-a first link; 504-a second link; 505-L-shaped blocks; 506-moving the plate; 507-spring shaft; 508-a slider; 509-side channel plates; 510-force bar.
Detailed Description
The technical scheme of the utility model is further described below by the specific embodiments with reference to the accompanying drawings.
As shown in fig. 1 to 11, the load test device further comprises a transmission separation mechanism 4 and a load detection mechanism 5, the speed reducer 2 to be detected is provided with a speed reducer gear box 201 and a rotating shaft assembly, the rotating shaft assembly is connected with the power mechanism 3, the rotating shaft assembly is connected with the speed reducer gear box 201, and the speed reducer gear box 201 is fixedly arranged on the frame 1; the transmission separation mechanism 4 is provided with a movable frame 401 and a state switching assembly, the state switching assembly is arranged on the movable frame 401, the movable frame 401 is in sliding connection with the frame 1, and the connection and disconnection between the power mechanism 3 and the rotating shaft assembly are realized through the state switching assembly; the load detection mechanism 5 is provided with hydraulic equipment 501, an electric cylinder 502 and a detection assembly, the electric cylinder 502 is fixedly arranged on the side face of the frame 1, the telescopic end of the electric cylinder 502 is fixedly connected with the movable frame 401, the hydraulic equipment 501 is slidably arranged on the side face of the movable frame 401, the rotation shaft assembly is connected with the detection assembly, the hydraulic equipment 501 is connected with the detection assembly, and the detection assembly is arranged on the side face of the movable frame 401.
As shown in fig. 2 to 10, the rotating shaft assembly is provided with a main rotor shaft 202, an input shaft 203 and a tail rotor shaft 204, the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 are respectively connected with a speed reducer gearbox 201, the power mechanism 3 is provided with a first motor 301, a second motor 302 and a third motor 303, the first motor 301 is connected with the main rotor shaft 202 through a state switching assembly, the second motor 302 is connected with the input shaft 203 through a state switching assembly, and the third motor 303 is connected with the tail rotor shaft 204 through a state switching assembly; the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 are provided with splines and have the same shape and size, the output ends of the first motor 301, the second motor 302 and the third motor 303 are provided with splines and have the same shape and size, the shapes and sizes of the splines on the main rotor shaft 202 and the first motor 301 are the same, each state switching component is provided with a telescopic shaft 402, the telescopic shaft 402 is arranged on the side surface of the movable frame 401, the side surface of the movable frame 401 is provided with a sliding slotted hole 407, a limiting frame 403 is arranged in the sliding slotted hole 407 in a sliding manner, a sliding groove is arranged on the limiting frame 403, the telescopic shaft 402 is arranged in the sliding groove of the limiting frame 403 in a sliding manner, the limiting frame 403 is fixedly connected with a force application rod 510, one end of the telescopic shaft 402 is fixedly provided with a fixed sleeve 404, the inner wall of the fixed sleeve 404 is rotatably provided with a movable sleeve 405, and the fixed sleeve 404 and the movable sleeve 405 are coaxial; the inner wall of the moving sleeve 405 is provided with a chute, the shape of the chute of the inner wall of the moving sleeve 405 is consistent with the shape of a spline of the third motor 303, the direction of the central line of the chute of the inner wall of the moving sleeve 405 is parallel to the axial line direction of the moving sleeve 405, and the chute of the inner wall of the moving sleeve 405 penetrates through the inner wall of the moving sleeve 405; three baffles 406 are fixedly arranged on the frame 1, and a first motor 301, a second motor 302 and a third motor 303 are respectively and fixedly arranged on the side surface of each baffle 406.
As shown in fig. 3 to 11, a gap is left between the first motor 301 and the end face of the main rotor shaft 202, a gap is left between the second motor 302 and the end face of the input shaft 203, a gap is left between the third motor 303 and the end face of the tail rotor shaft 204, the gap distances are equal, the axial length of the moving sleeve 405 is greater than the gap length, the axial length of the moving sleeve 405 is greater than the axial length of the fixed sleeve 404, and when the contraction amount of the electric cylinder 502 reaches the maximum value, the sliding grooves of the moving sleeve 405 are separated from the splines on the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204; the detection assembly is provided with three, and every detection assembly is provided with a force application rod 510, and the force application rod 510 is communicated with the hydraulic equipment 501, and the axial direction of each force application rod 510 is perpendicular to the axial directions of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 respectively, and one end face of the force application rod 510 is hemispherical.
As shown in fig. 4 to 11, each detection assembly is further provided with a moving plate 506, a spring shaft 507 is slidably mounted on the side surface of the moving plate 506, a spring is wound on the outer surface of the spring shaft 507, one end of the spring on the outer surface of the spring shaft 507 is fixedly mounted on the moving plate 506, the other end of the spring on the outer surface of the spring shaft 507 is fixedly mounted on the spring shaft 507, the spring shaft 507 is slidably mounted on the frame 1, each moving plate 506 is mounted on one side, far away from the force application rod 510, of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204, and each moving plate 506 is tangent to the outer surfaces of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204; the side surface of the movable frame 401 facing the reducer gearbox 201 is fixedly provided with two L-shaped blocks 505, the side surface of each L-shaped block 505 is provided with a chute, the two side surfaces of each movable plate 506 are respectively provided with a cylindrical protrusion, the cylindrical protrusions of the movable plates 506 are slidably arranged in the chute of the L-shaped block 505, the outer surfaces of the cylindrical protrusions of the movable plates 506 are rotatably provided with second connecting rods 504, one ends of the second connecting rods 504, which are far away from the L-shaped blocks 505, are rotatably provided with sliding blocks 508, the sliding blocks 508 are slidably arranged on side chute plates 509, the side chute plates 509 are fixedly arranged on the side surfaces of the movable frame 401, the side surfaces of the sliding blocks 508 are rotatably provided with first connecting rods 503, and one ends of the first connecting rods 503, which are far away from the sliding blocks 508, are rotatably connected with the hydraulic equipment 501; in the initial state, the distance between the slider 508 and the hydraulic device 501 is smaller than the distance between the slider 508 and the moving plate 506.
The utility model discloses a load test device of a helicopter speed reducer, which has the following working principle.
The first electric cylinder 502 is started, the electric cylinder 502 drives the movable frame 401 to move, the movable frame 401 drives the telescopic shaft 402 to move, the telescopic shaft 402 drives the fixed sleeve 404 to move, the fixed sleeve 404 drives the movable sleeve 405 to move, so that the first motor 301 is in butt joint with the main rotor shaft 202, the second motor 302, the input shaft 203, the third motor 303 and the tail rotor shaft 204 through the sliding grooves of the movable sleeve 405, the electric cylinder 502 is closed, and then the first motor 301, the second motor 302 and the third motor 303 are started, and the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 are respectively driven to rotate through the movable sleeve 405.
And (II) the hydraulic equipment 501 is started, the force application rod 510 is pressed by the hydraulic equipment 501, so that load force is applied to the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204, and the electric cylinder 502 drives the movable frame 401 to move, so that load tests are carried out on different positions of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204.
And (III) when the bending degree of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 exceeds the pushing stroke of the hydraulic equipment 501 during load detection, the moving plate 506 moves, the moving plate 506 drives the second connecting rod 504 to move, the second connecting rod 504 drives the first connecting rod 503 to move, and the first connecting rod 503 drives the hydraulic equipment 501 to move along the direction away from the moving plate 506, so that separation is realized, and damage caused by the excessive bending degree of the main rotor shaft 202, the input shaft 203 and the tail rotor shaft 204 is avoided.
Claims (9)
1. The utility model provides a load test device of helicopter reduction gear, includes frame (1), treats detection reduction gear (2) and power unit (3), its characterized in that: the load test device also comprises a transmission separation mechanism (4) and a load detection mechanism (5), the speed reducer (2) to be detected is provided with a speed reducer gear box (201) and a rotating shaft assembly, the rotating shaft assembly is connected with the power mechanism (3), the rotating shaft assembly is connected with the speed reducer gear box (201), and the speed reducer gear box (201) is fixedly arranged on the frame (1);
the transmission separation mechanism (4) is provided with a movable frame (401) and a state switching assembly, the state switching assembly is arranged on the movable frame (401), the movable frame (401) is in sliding connection with the frame (1), and the connection and disconnection between the power mechanism (3) and the rotating shaft assembly are realized through the state switching assembly;
the load detection mechanism (5) is provided with hydraulic equipment (501), an electric cylinder (502) and a detection assembly, the electric cylinder (502) is fixedly installed on the side face of the frame (1), the telescopic end of the electric cylinder (502) is fixedly connected with the movable frame (401), the hydraulic equipment (501) is slidably installed on the side face of the movable frame (401), the rotation shaft assembly is connected with the detection assembly, the hydraulic equipment (501) is connected with the detection assembly, and the detection assembly is installed on the side face of the movable frame (401).
2. The load test device for a helicopter reducer according to claim 1, wherein: the rotary shaft assembly is provided with a main rotor shaft (202), an input shaft (203) and a tail rotor shaft (204), the main rotor shaft (202), the input shaft (203) and the tail rotor shaft (204) are respectively connected with a speed reducer gearbox (201), the power mechanism (3) is provided with a first motor (301), a second motor (302) and a third motor (303), the first motor (301) is connected with the main rotor shaft (202) through a state switching assembly, the second motor (302) is connected with the input shaft (203) through a state switching assembly, and the third motor (303) is connected with the tail rotor shaft (204) through a state switching assembly.
3. A load test device for a helicopter reducer according to claim 2 wherein: main rotor shaft (202), input shaft (203) and tail rotor shaft (204) on all be provided with spline and shape size unanimity, first motor (301), second motor (302) and third motor (303) output all be provided with spline and shape size unanimity, main rotor shaft (202) and first motor (301) on spline shape size unanimity, every state switching component all be provided with telescopic shaft (402), telescopic shaft (402) install in movable frame (401) side, telescopic shaft (402) one end fixed mounting have fixed sleeve (404), fixed sleeve (404) inner wall on rotate and install and remove sleeve (405), fixed sleeve (404) and remove sleeve (405) coaxial.
4. A load test apparatus for a helicopter reducer according to claim 3 wherein: the inner wall of the movable sleeve (405) is provided with a chute, the shape of the chute of the inner wall of the movable sleeve (405) is consistent with the shape of a spline of the third motor (303), the direction of the central line of the chute of the inner wall of the movable sleeve (405) is parallel to the axial direction of the movable sleeve (405), and the chute of the inner wall of the movable sleeve (405) penetrates through the inner wall of the movable sleeve (405).
5. The load testing device of a helicopter reducer according to claim 4, wherein: the novel rotor shaft comprises a first motor (301) and a main rotor shaft (202), a gap is reserved between the end faces of the first motor and the main rotor shaft (202), a gap is reserved between the end faces of the second motor (302) and an input shaft (203), a gap is reserved between the end faces of a third motor (303) and a tail rotor shaft (204), the gap distances are equal, the axial length of a movable sleeve (405) is larger than that of a fixed sleeve (404), and when the shrinkage of an electric cylinder (502) reaches the maximum value, a sliding groove of the movable sleeve (405) is separated from splines on the main rotor shaft (202), the input shaft (203) and the tail rotor shaft (204).
6. A load test apparatus for a helicopter reducer according to claim 3 wherein: the three detection assemblies are arranged, each detection assembly is provided with a force application rod (510), the force application rods (510) are communicated with the hydraulic equipment (501), the axial direction of each force application rod (510) is perpendicular to the axial directions of the main rotor shaft (202), the input shaft (203) and the tail rotor shaft (204), and one end face of each force application rod (510) is hemispherical.
7. The load testing device of a helicopter reducer of claim 6, wherein: each detection assembly is further provided with a movable plate (506), each movable plate (506) is arranged on one side, far away from the force application rod (510), of the main rotor shaft (202), the input shaft (203) and the tail rotor shaft (204), and each movable plate (506) is tangent to the outer surfaces of the main rotor shaft (202), the input shaft (203) and the tail rotor shaft (204).
8. The load testing device of a helicopter reducer according to claim 7, wherein: the utility model provides a movable rack (401) towards the side fixed mounting of reduction gear box (201) have two L shape piece (505), every L shape piece (505) side be provided with the spout, every two sides of movable plate (506) are provided with a cylindrical protrusion respectively, the cylindrical protrusion slidable mounting of movable plate (506) is in the spout of L shape piece (505), the cylindrical protrusion surface rotation of movable plate (506) install second connecting rod (504), the one end rotation of keeping away from L shape piece (505) of second connecting rod (504) install slider (508), slider (508) slidable mounting in movable rack (401) side, slider (508) side rotation install first connecting rod (503), one end that slider (508) were kept away from to first connecting rod (503) rotate with hydraulic equipment (501) and be connected.
9. The load test device for a helicopter reducer according to claim 8, wherein: in the initial state, the distance between the slide block (508) and the hydraulic device (501) is smaller than the distance between the slide block (508) and the moving plate (506).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311323709.0A CN117074017B (en) | 2023-10-13 | 2023-10-13 | Load test device of helicopter speed reducer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311323709.0A CN117074017B (en) | 2023-10-13 | 2023-10-13 | Load test device of helicopter speed reducer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117074017A true CN117074017A (en) | 2023-11-17 |
| CN117074017B CN117074017B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202311323709.0A Active CN117074017B (en) | 2023-10-13 | 2023-10-13 | Load test device of helicopter speed reducer |
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| CN117074017B (en) | 2024-04-05 |
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