CN110937136B - Aircraft landing gear buffer friction force testing device and testing method thereof - Google Patents
Aircraft landing gear buffer friction force testing device and testing method thereof Download PDFInfo
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- CN110937136B CN110937136B CN201911022192.5A CN201911022192A CN110937136B CN 110937136 B CN110937136 B CN 110937136B CN 201911022192 A CN201911022192 A CN 201911022192A CN 110937136 B CN110937136 B CN 110937136B
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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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Abstract
Provided are a friction force testing device and a friction force testing method for an aircraft landing gear buffer. Relates to the technical field of airplane undercarriage tests. The friction force test device and the test method of the aircraft landing gear buffer have the advantages that the structure is exquisite, the stability is good, the reliability is high, the real loading condition of the buffer for the aircraft landing gear during working can be simulated during use, and the friction force of the buffer under any stroke can be finally obtained. The device comprises a workbench, an axial force loading mechanism, a load loading platform, a fixed block and a lateral force loading mechanism. The invention has the following beneficial effects: the nose landing gear test for simulating the carrier aircraft catapulting release process under the condition that no carrier aircraft engine exists in a laboratory is realized; the cylinder can be used for loading lateral force, so that the load is stable and the continuity is good; the testing device is simple in structure, reduces the testing scale and saves the testing cost.
Description
Technical Field
The invention relates to the technical field of airplane undercarriage tests.
Background
The hydraulic buffer buffers and decelerates the object acting on the hydraulic buffer to stop by means of hydraulic damping, and plays a role in protecting to a certain extent; the purpose is to avoid the damage of the mechanism caused by hard collision in the working process. Hydraulic shock absorbers, in particular for aircraft landing gears, in which the piston rod is subjected to friction during operation, are an important factor in the performance of the shock absorber.
At present, in the prior art, no relevant published test research reports exist on a friction force test device and a test method for an aircraft landing gear buffer, so how to further carry out test simulation research on the problem becomes a technical problem to be urgently solved by a technical person in the field.
Disclosure of Invention
Aiming at the problems, the invention provides the test device and the test method for the friction force of the buffer of the undercarriage, which have the advantages of exquisite structure, good stability and high reliability, can simulate the real loading condition of the buffer of the undercarriage during working and finally obtain the friction force of the buffer under any stroke.
The technical scheme of the invention is as follows: the buffer comprises a workbench, an axial force loading mechanism, a load loading platform, a fixed block and a lateral force loading mechanism, wherein a fixed component is arranged on one side of the top surface of the workbench, an outer cylinder of the buffer is detachably connected onto the workbench through the fixed component, and the end of a piston rod of the buffer, which is far away from the outer cylinder, is detachably connected onto the fixed block;
the axial force loading mechanism comprises a rotary driving mechanism, a screw rod nut and an axial force sensor, wherein two ends of the screw rod are hinged to the top surface of the workbench, the screw rod is arranged on one side of the buffer in parallel, the screw rod nut is sleeved on the screw rod and is in threaded connection with the screw rod, the rotary driving mechanism is connected to the workbench and is connected with the screw rod, and the screw rod is driven to rotate through the rotary driving mechanism;
the load loading platform is arranged on the top surface of the workbench in a sliding manner and is fixedly connected with the screw rod nut;
the axial force sensor is arranged along the axial direction of the buffer, one side of the axial force sensor is connected with the load loading platform, and the other side of the axial force sensor is connected with the fixing block;
the lateral force loading mechanism comprises a linear driving mechanism, a lever and a lateral force sensor, the middle part of the lever is hinged on the top surface of the load loading platform, one end of the lever is hinged with the linear driving mechanism, and the other end of the lever is hinged with the lateral force sensor; the linear driving mechanism is connected to the load loading platform and is used for applying acting force to the lever; the lateral force sensor is arranged along the radial direction of the buffer, and one side of the lateral force sensor, which is far away from the lever, is connected with the fixed block.
An oil pressure sensor is further arranged on the outer barrel of the buffer.
The fixing assembly comprises a supporting seat, a supporting sleeve and a supporting connecting rod, the supporting seat and the supporting sleeve are fixedly connected to the top surface of the workbench, the outer cylinder of the buffer is arranged in the supporting sleeve in a penetrating mode, and the end, far away from the piston rod, of the outer cylinder is detachably connected to the supporting seat;
the supporting connecting rod and the lateral force sensor are respectively positioned on two sides of the buffer, one end of the supporting connecting rod is hinged with the supporting sleeve, and the other end of the supporting connecting rod is hinged with the supporting seat.
One side of the axial force sensor is hinged with the load loading platform, and the other side of the axial force sensor is hinged with the fixed block; one side of the lateral force sensor is hinged with the lever, and the other side of the lateral force sensor is hinged with the fixed block.
The rotary driving mechanism comprises a motor, a speed reducer and a coupler, the motor and the speed reducer are fixedly connected to the workbench, the coupler is connected between the speed reducer and the screw rod, and an output shaft of the motor is linked with the screw rod through the speed reducer and the coupler.
The linear driving mechanism is a cylinder or a hydraulic cylinder.
The top surface of the workbench is also fixedly connected with a slide rail parallel to the axial direction of the buffer, a slide block is fixedly connected below the load loading platform, and the slide block is matched with the slide rail and is connected on the slide rail in a sliding manner.
The test was carried out as follows:
1) Assembling a testing device according to the testing technical requirements, calculating the compression speed of the piston rod required by the test, and calculating the rotating speed of the corresponding motor through conversion; the rotating speed, the rotating direction and the number of rotating turns of the motor are controlled through programming;
2) Starting the linear driving mechanism according to the test technical requirements, and adjusting the pressure of the linear driving mechanism through the lateral force sensor to obtain the lateral force required by the test requirements;
3) Starting a motor, wherein a computer acquires a plurality of instantaneous data of an axial force sensor in the process of compressing a piston rod, the motor reversely rotates to return to an original position after the piston rod is compressed to a termination position, and the computer acquires a plurality of instantaneous data of the axial force sensor in the process of extending the piston rod;
4) Repeating the step 3) for a plurality of times to acquire a plurality of groups of data;
5) And processing the data to obtain the change curve of the axial acting force of the piston rod along with the stroke in the compression process and the extension process, and finally obtaining the change curve of the friction force along with the stroke after calculation.
The invention has the following beneficial effects: the nose landing gear test for simulating the carrier aircraft catapulting release process under the condition that no carrier aircraft engine exists in a laboratory is realized; the cylinder can be used for loading lateral force, so that the load is stable and the continuity is good; the testing device is simple in structure, reduces the testing scale and saves the testing cost.
Drawings
FIG. 1 is a schematic structural diagram of the present invention,
FIG. 2 is a perspective view of FIG. 1;
in the figure, 1 is a workbench, 10 is a slide rail, 11 is a supporting seat, 12 is a supporting sleeve, and 13 is a supporting connecting rod;
2 is an axial force loading mechanism, 21 is a rotary driving mechanism, 211 is a motor, 212 is a speed reducer, 213 is a coupling, 22 is a screw rod, 23 is a screw rod nut, and 24 is an axial force sensor;
3 is a load loading platform, and 4 is a fixed block;
5 is a lateral force loading mechanism, 51 is a linear driving mechanism, 52 is a lever, and 53 is a lateral force sensor;
Detailed Description
The invention is shown in fig. 1-2, and comprises a workbench 1, an axial force loading mechanism 2, a load loading platform 3, a fixed block 4 and a lateral force loading mechanism 5, wherein one side of the top surface of the workbench 1 is provided with a fixing component, an outer cylinder 61 of a buffer is detachably connected onto the workbench 1 through the fixing component, and the end of a piston rod 62 of the buffer, which is far away from the outer cylinder 61, is detachably connected (can be inserted as shown in fig. 1, or can be in the forms of threaded connection, spot welding, hinging and the like) onto the fixed block 4;
the axial force loading mechanism comprises a rotary driving mechanism 21, a screw rod 22, a screw rod nut 23 and an axial force sensor 24, two ends of the screw rod 22 are hinged to the top surface of the workbench 1 through hinge seats, the screw rod 22 is arranged on one side of the buffer 6 in parallel, the screw rod nut 23 is sleeved with the screw rod 22 and is in threaded connection with the screw rod 22, the rotary driving mechanism 21 is connected to the workbench 1 and is connected with the screw rod 22, and the screw rod is driven to rotate through the rotary driving mechanism;
the load loading platform 3 is slidably arranged on the top surface of the workbench 1 and is fixedly connected with the screw rod nut 23; after the rotary driving mechanism is started, the screw rod nut and the load loading platform can be driven to perform reciprocating translation through the rotation of the screw rod;
the axial force sensor 24 is axially arranged along the buffer 6, one side of the axial force sensor 24 is connected with the load loading platform 3, and the other side of the axial force sensor is connected with the fixed block 4; thereby applying axial force to the piston rod of the buffer in the process of reciprocating translation of the load loading platform;
the lateral force loading mechanism 5 comprises a linear driving mechanism 51, a lever 52 and a lateral force sensor 53, the middle part of the lever 52 is hinged on the top surface of the load loading platform 3, one end of the lever 52 is hinged with the linear driving mechanism 51, and the other end of the lever is hinged with the lateral force sensor 53; the linear driving mechanism 51 is connected to the load loading platform 3 and is used for applying acting force to the lever 52; the lateral force sensor 53 is arranged in the radial direction of the damper 6 and is connected to the fixed block 4 on the side thereof remote from the lever 52. Thus, after the linear driving mechanism is started, the output force of the linear driving mechanism can be continuously increased by continuously pressurizing the linear driving mechanism, so that the lateral force is applied to the piston rod of the buffer in the lateral direction of the fixed block, namely the radial direction of the buffer through the lever and the lateral force sensor.
The buffer for the aircraft landing gear can truly and effectively simulate the actual loading condition of the buffer for the aircraft landing gear during working through the matching of the axial force loading mechanism and the lateral force loading mechanism, namely the condition that the end of a piston rod in the buffer is subjected to radial acting force; and the change curve of the axial acting force of the piston rod along with the stroke in the compression process and the extension process can be drawn through the reading of the axial force sensor.
During subsequent calculation, when the piston rod is at a certain position, the friction force is the same no matter in the compression process or the extension process, the reading of the pressure sensor in the compression process of the piston rod is the sum of the oil pressure and the friction force, and the reading of the pressure sensor in the extension process of the piston rod is the difference between the oil pressure and the friction force; therefore, the values of the two change curves on the same abscissa can be subtracted and then divided by 2 to obtain the instantaneous friction force of the buffer, so that the change curve of the friction force along with the stroke is finally obtained through the subtraction of the two curves.
After that, the operator can obtain the friction force under any stroke by means of the change curve of the friction force along with the stroke, thereby measuring the performance of the friction device. On the whole, the invention can simulate the real loading condition of the buffer for the aircraft landing gear during working and finally obtain the friction force of the buffer under any stroke, and has the advantages of exquisite structure, good stability, high reliability and the like.
An oil pressure sensor is further arranged on the outer barrel of the buffer 6. Therefore, subsequent calculation processing and mutual verification of calculation results are facilitated, specifically, the reading of the pressure sensor in the compression process of the piston rod is the sum of the oil pressure and the friction force, and the reading of the pressure sensor in the extension process of the piston rod is the difference between the oil pressure and the friction force; by calculating the friction during compression and during extension, the final calculation can be verified.
The fixing component comprises a supporting seat 11, a supporting sleeve 12 and a supporting connecting rod 13, the supporting seat 11 and the supporting sleeve 12 are both fixedly connected to the top surface of the workbench 1, an outer cylinder 61 of the buffer penetrates through the supporting sleeve 12, and the end of the outer cylinder 61 far away from the piston rod 62 is detachably connected to the supporting seat 11 (in a hinged manner as shown in fig. 1, or in a threaded connection manner, a spot welding manner, an insertion manner and the like);
the supporting connecting rod 13 and the lateral force sensor 53 are respectively positioned at two sides of the buffer 6, one end of the supporting connecting rod 13 is hinged with the supporting sleeve 12, and the other end of the supporting connecting rod is hinged with the supporting seat 11. Therefore, good and stable support is provided for the outer cylinder, and stable lateral support is provided for the buffer in the opposite direction of the applied lateral force, so that the real loading condition of the buffer for the aircraft landing gear during working can be better simulated.
One side of the axial force sensor is hinged with the load loading platform, and the other side of the axial force sensor is hinged with the fixed block; one side of the lateral force sensor is hinged with the lever, and the other side of the lateral force sensor is hinged with the fixed block. Therefore, the fixing block can be conveniently and efficiently assembled between the axial force sensor and the lateral force sensor.
The rotary driving mechanism 21 comprises a motor 211, a speed reducer 212 and a coupler 213, the motor 211 and the speed reducer 212 are fixedly connected to the workbench 1, the coupler 213 is connected between the speed reducer 212 and the screw rod 22, and an output shaft of the motor 211 is linked with the screw rod 22 through the speed reducer 212 and the coupler 213. Thereby realizing the rotary drive of the screw rod.
The linear driving mechanism is a cylinder or a hydraulic cylinder. Thereby effecting application of force to the lever.
The top surface of the workbench 1 is also fixedly connected with a slide rail 10 parallel to the axial direction of the buffer, and a slide block is fixedly connected below the load loading platform and is matched with the slide rail 10 and is connected on the slide rail in a sliding manner. Thereby realizing the sliding connection of the load loading platform and the workbench.
The test was carried out as follows:
1) Assembling a test device according to the test technical requirements, calculating the compression speed of the piston rod required by the test, and calculating the rotating speed of the corresponding motor through conversion; the rotating speed, the rotating direction and the rotating number of turns of the motor are controlled through programming;
2) Starting the linear driving mechanism according to the test technical requirements, and adjusting the pressure of the linear driving mechanism through the lateral force sensor to obtain the lateral force required by the test requirements;
3) Starting a motor, wherein a computer acquires a plurality of instantaneous data of an axial force sensor in the process of compressing a piston rod, the motor reversely rotates to return to an original position after the piston rod is compressed to a termination position, and the computer acquires a plurality of instantaneous data of the axial force sensor in the process of extending the piston rod;
4) Repeating the step 3) for a plurality of times to acquire a plurality of groups of data;
5) And processing the data to obtain the change curve of the axial acting force of the piston rod along with the stroke in the compression process and the extension process, and finally obtaining the change curve of the friction force along with the stroke after calculation. During subsequent calculation, the reading of the pressure sensor in the compression process of the piston rod is the sum of the oil pressure and the friction force, and the reading of the pressure sensor in the extension process of the piston rod is the difference between the oil pressure and the friction force; therefore, the values of the two change curves on the same abscissa can be subtracted and then divided by 2 to obtain the instantaneous friction force of the buffer, so that the change curve of the friction force along with the stroke is finally obtained through the subtraction of the two curves.
Claims (6)
1. The method for testing the friction force of the aircraft landing gear buffer is characterized by being realized through a friction force testing device, wherein the friction force testing device comprises a workbench, an axial force loading mechanism, a load loading platform, a fixed block and a lateral force loading mechanism, a fixed assembly is arranged on one side of the top surface of the workbench, an outer cylinder of the buffer is detachably connected onto the workbench through the fixed assembly, and the end, far away from the outer cylinder, of a piston rod of the buffer is detachably connected onto the fixed block;
the axial force loading mechanism comprises a rotary driving mechanism, a screw rod nut and an axial force sensor, wherein two ends of the screw rod are hinged to the top surface of the workbench, the screw rod is arranged on one side of the buffer in parallel, the screw rod nut is sleeved on the screw rod and is in threaded connection with the screw rod, the rotary driving mechanism is connected to the workbench and is connected with the screw rod, and the screw rod is driven to rotate through the rotary driving mechanism;
the load loading platform is arranged on the top surface of the workbench in a sliding manner and is fixedly connected with the screw rod nut;
the axial force sensor is arranged along the axial direction of the buffer, one side of the axial force sensor is connected with the load loading platform, and the other side of the axial force sensor is connected with the fixed block;
the lateral force loading mechanism comprises a linear driving mechanism, a lever and a lateral force sensor, the middle part of the lever is hinged on the top surface of the load loading platform, one end of the lever is hinged with the linear driving mechanism, and the other end of the lever is hinged with the lateral force sensor; the linear driving mechanism is connected to the load loading platform and is used for applying acting force to the lever; the lateral force sensor is arranged along the radial direction of the buffer, and one side of the lateral force sensor, which is far away from the lever, is connected with the fixed block;
the rotary driving mechanism comprises a motor, a speed reducer and a coupler, the motor and the speed reducer are both fixedly connected to the workbench, the coupler is connected between the speed reducer and the screw rod, and an output shaft of the motor is linked with the screw rod through the speed reducer and the coupler;
the test was carried out as follows:
1) Assembling a test device according to the test technical requirements, calculating the compression speed of the piston rod required by the test, and calculating the rotating speed of the corresponding motor through conversion; the rotating speed, the rotating direction and the number of rotating turns of the motor are controlled through programming;
2) Starting the linear driving mechanism according to the test technical requirements, and adjusting the pressure of the linear driving mechanism through the lateral force sensor to obtain the lateral force required by the test requirements;
3) Starting a motor, wherein a computer acquires a plurality of instantaneous data of an axial force sensor in the process of compressing a piston rod, the motor reversely rotates to return to an original position after the piston rod is compressed to a termination position, and the computer acquires a plurality of instantaneous data of the axial force sensor in the process of extending the piston rod;
4) Repeating the step 3) for a plurality of times to acquire a plurality of groups of data;
5) Processing the data to obtain a change curve of the axial acting force of the piston rod along with the stroke in the compression process and the extension process, and finally obtaining a change curve of the friction force along with the stroke after calculation;
during calculation, the reading of the pressure sensor in the compression process of the piston rod is the sum of the oil pressure and the friction force, and the reading of the pressure sensor in the extension process of the piston rod is the difference between the oil pressure and the friction force; therefore, the values of the two change curves on the same abscissa are subtracted and then divided by 2 to obtain the instantaneous friction force of the buffer, so that the change curve of the friction force along with the stroke is finally obtained through the subtraction of the two curves.
2. The method for testing the friction force of the aircraft landing gear bumper according to claim 1, wherein an oil pressure sensor is further arranged on an outer cylinder of the bumper.
3. The method for testing the friction force of the aircraft landing gear bumper according to claim 1, wherein the fixing assembly comprises a supporting seat, a supporting sleeve and a supporting connecting rod, the supporting seat and the supporting sleeve are fixedly connected to the top surface of the workbench, an outer cylinder of the bumper penetrates through the supporting sleeve, and the end, far away from the piston rod, of the outer cylinder is detachably connected to the supporting seat;
the supporting connecting rod and the lateral force sensor are respectively arranged on two sides of the buffer, one end of the supporting connecting rod is hinged with the supporting sleeve, and the other end of the supporting connecting rod is hinged with the supporting seat.
4. The method for testing the friction force of the aircraft landing gear buffer is characterized in that one side of the axial force sensor is hinged with the load loading platform, and the other side of the axial force sensor is hinged with the fixing block; one side of the lateral force sensor is hinged with the lever, and the other side of the lateral force sensor is hinged with the fixed block.
5. The method for testing the friction force of the aircraft landing gear bumper according to claim 1, wherein the linear driving mechanism is an air cylinder or a hydraulic cylinder.
6. The method for testing the friction force of the buffer of the landing gear of the airplane according to claim 1, wherein a slide rail parallel to the axial direction of the buffer is fixedly connected to the top surface of the workbench, a slide block is fixedly connected to the lower portion of the load loading platform, and the slide block is matched with the slide rail and is slidably connected to the slide rail.
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| CN114088275B (en) * | 2021-11-22 | 2024-04-05 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and measuring method |
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| 基于有限元分析的液压缸侧向力试验装置的设计;王宇恒等;《机械制造与自动化》;20170420(第02期);85-87 * |
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|---|---|
| CN110937136A (en) | 2020-03-31 |
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