Aircraft body bearing radial dynamic load testing machine

Abstract

The utility model discloses an airplane body bearing radial dynamic load testing machine, comprising a test bench, the test bench is provided with a tool sleeve and a core shaft matched with the tool sleeve, the tool sleeve is provided with a tool hole for the core shaft to pass through, and the tool hole is provided with a tool hole for the core shaft to pass through. A test cavity for mounting and accommodating an external to-be-tested bearing is formed between the inner peripheral wall of the tool hole and the outer peripheral wall of the mandrel; the test bench is provided with a driving member used for driving the mandrel to axially rotate so as to drive the bearing to be tested to operate, a loading member used for applying a radial load to the tool sleeve so as to apply the radial load to the bearing to be tested, and a detection assembly used for being in linkage cooperation with the loading member so as to detect the load amount and the displacement amount of the bearing to be tested during operation. The utility model solves the problem that the prior art lacks a multifunctional testing machine for airplane body bearings, which is used for carrying out multidirectional tests on airplane body bearings and simulating bearing operation industrial control.

Description

TECHNICAL FIELD

[0001] The utility model relates to bearing test frock technical field, concretely is a kind of aircraft body bearing radial dynamic load testing machine. BACKGROUND

[0002] In the modern aviation field, the safety and stable operation of aircraft are crucial. Aircraft body bearings, as the key components connecting various parts of the aircraft, play an irreplaceable role. They effectively transmit force and motion through rotation and sliding, providing the foundation for normal flight operations of the aircraft. During the entire flight process of the aircraft, including takeoff, flight, and landing in different stages, the body bearings need to withstand extremely large loads and impacts. At the same time, to ensure that the aircraft can fly according to the predetermined attitude and trajectory, the bearings must also maintain high-precision operation. However, aircraft body bearings usually have the characteristics of small size but large load bearing. Due to their critical position in the flight process of the aircraft, once the bearings have problems, it is likely to cause serious flight accidents, resulting in immeasurable personnel casualties and property losses. Therefore, conducting comprehensive and strict tests on aircraft body bearings to ensure their safety and reliability has become an important work in the field of aviation manufacturing and maintenance. Currently, there is a lack of a multifunctional testing machine that can test aircraft body bearings in multiple directions and accurately simulate the actual operating conditions of the bearings. Existing test equipment often has single function and cannot comprehensively simulate various loads and different motion states that bearings bear in complex operating environments of the aircraft. This makes the performance evaluation of aircraft body bearings not accurate and comprehensive enough, making it difficult to meet the strict requirements of the aviation field for high reliability and safety of bearings. SUMMARY

[0003] In view of the deficiencies in the prior art, the utility model provides an aircraft body bearing radial dynamic load testing machine to solve the problem of the lack of a multifunctional testing machine for aircraft body bearings in the prior art.

[0004] To achieve the above-mentioned purpose, the utility model provides an aircraft body bearing radial dynamic load testing machine, which comprises a test bed, a tool holder and a mandrel matched with the tool holder are arranged on the test bed, a tool hole for the mandrel to pass through is arranged on the tool holder, a test cavity for mounting and accommodating the external bearing to be tested is formed between the inner circumferential wall of the tool hole and the outer circumferential wall of the mandrel, a driving member for driving the mandrel to rotate axially to drive the bearing to be tested to rotate, a loading member for applying radial load to the tool holder to apply radial load to the bearing to be tested, and a detection assembly for cooperating with the loading member to detect the load and displacement of the bearing to be tested during operation are arranged on the test bed.

[0005] The beneficial effects of the above technical scheme are as follows: the aircraft body bearing to be tested is cleaned and inspected for no obvious damage, a tooling sleeve and a mandrel are installed on the test bench to form a test cavity, and the bearing is installed into the test cavity; a driving member is connected with the mandrel, and a loading member and a detection assembly are installed and debugged; the driving member speed and the initial radial load of the loading member are set according to the test requirements, the driving member is started to drive the mandrel to rotate with the bearing, the loading member gradually increases the radial load according to the preset program, the detection assembly monitors the load and displacement in real time and transmits data; the mandrel speed and the radial load of the loading member are kept stable, and the bearing continuously rotates, and the detection assembly continuously monitors the related data during this period, and the driving member and the loading member are stopped when the predetermined test time is reached or the bearing is obviously damaged; the bearing is taken out for inspection and size measurement, and the bearing performance is evaluated in combination with the detection data to analyze the bearing load capacity, wear and life, etc., to provide a basis for bearing improvement and optimization; in the above technology, the test cavity is formed by setting the tooling sleeve and the mandrel, and the driving member is provided to drive the mandrel to rotate axially, which can effectively simulate the rotating state of the aircraft body bearing in the actual operation process, so that the test result is closer to the actual working condition, and a reliable basis is provided for evaluating the bearing performance; the loading member can apply a radial load to the tooling sleeve, and then to the bearing to be tested, and this accurate loading method can simulate the radial force borne by the aircraft body bearing in the actual work, which helps to accurately test the performance of the bearing under different radial loads, and improves the pertinence and accuracy of the test; the detection assembly and the loading member are linked to detect the load and displacement of the bearing to be tested in real time. Through accurate measurement and analysis of these key parameters, problems that may occur during the operation of the bearing, such as wear and deformation, can be found in time, and data support is provided for optimizing the bearing design and improving the quality; in the above technology, not only the radial dynamic load test of the bearing can be carried out, but also various related performance tests can be carried out by adjusting the loading conditions and detection parameters, such as the radial load test under different speeds and the bearing life test under different loads, which has strong multifunctional test capability and improves the use efficiency and application range of the equipment.

[0006] The utility model further sets up: test bench is provided with tooling seat, the activity cavity that is used for tooling sleeve activity is opened to tooling seat, the loading member includes setting hydraulic cylinder on test bench, the hydraulic cylinder output end is used for placing into activity cavity and the radial load that is applied to tooling sleeve when hydraulic cylinder runs loading end.

[0007] The beneficial effects of the above technical solution are: in the above technology, the tool holder is provided with a stable and movable installation space by setting the tool holder on the test bench and opening the movable cavity, and the loading part adopts a hydraulic cylinder, the output end of which is used as a loading end and can be accurately placed in the movable cavity and apply radial load to the tool holder. This design can ensure the accuracy and stability of the radial load application, so that when the radial dynamic load test of the aircraft body bearing is performed, the stress condition closer to the actual working condition can be simulated, and the reliability and effectiveness of the test results are improved. At the same time, as the loading part, the size of the radial load output by the hydraulic cylinder can be flexibly adjusted through the hydraulic system. When the radial dynamic load test of the aircraft body bearing is performed, the output load of the hydraulic cylinder can be easily adjusted according to different test requirements and bearing specifications to simulate the radial force borne by the bearing under different working conditions. This flexible loading method can adapt to various test requirements and improve the versatility and application range of the test equipment. The operation of the hydraulic cylinder can be accurately controlled through the hydraulic control system, and in cooperation with the detection assembly, the automation of the test process can be easily realized. For example, the output load of the hydraulic cylinder can be automatically adjusted according to the bearing load and displacement data fed back by the detection assembly, the real-time monitoring and accurate control of the test condition are realized, the efficiency and accuracy of the test are improved, and the interference of human factors on the test results is reduced. In the above technology, the hydraulic cylinder is a prior art, so its structure and function will not be described in detail, and a hydraulic power station can be arranged below the test bench to provide power support for the hydraulic cylinder according to actual operation requirements.

[0008] The detection assembly further comprises a load sensor arranged on the loading end of the hydraulic cylinder, and a loading shaft is arranged on the detection end of the load sensor.

[0009] The beneficial effects of the above technical solution are: in the above technology, the tool holder is provided with a stable and movable installation space by setting the tool holder on the test bench and opening the movable cavity, and the loading part adopts a hydraulic cylinder, the output end of which is used as a loading end and can be accurately placed in the movable cavity and apply radial load to the tool holder. This design can ensure the accuracy and stability of the radial load application, so that when the radial dynamic load test of the aircraft body bearing is performed, the stress condition closer to the actual working condition can be simulated, and the reliability and effectiveness of the test results are improved. At the same time, as the loading part, the size of the radial load output by the hydraulic cylinder can be flexibly adjusted through the hydraulic system. When the radial dynamic load test of the aircraft body bearing is performed, the output load of the hydraulic cylinder can be easily adjusted according to different test requirements and bearing specifications to simulate the radial force borne by the bearing under different working conditions. This flexible loading method can adapt to various test requirements and improve the versatility and application range of the test equipment. The operation of the hydraulic cylinder can be accurately controlled through the hydraulic control system, and in cooperation with the detection assembly, the automation of the test process can be easily realized. For example, the output load of the hydraulic cylinder can be automatically adjusted according to the bearing load and displacement data fed back by the detection assembly, the real-time monitoring and accurate control of the test condition are realized, the efficiency and accuracy of the test are improved, and the interference of human factors on the test results is reduced. In the above technology, the hydraulic cylinder is a prior art, so its structure and function will not be described in detail, and a hydraulic power station can be arranged below the test bench to provide power support for the hydraulic cylinder according to actual operation requirements.

[0010] The utility model further sets up: the loading shaft terminal end radial section presents circular arc setting and forms and has the loading ball head, the loading hole is passed in on the test platform outer wall, the loading block is slidably arranged in the loading hole along its axial direction, the loading block initial end is the force end for with the loading ball head abutment cooperation, the loading block terminal end is the contact end for putting into the movable cavity and with the tool set outer wall contact.

[0011] The above technical solution has the advantages that: the loading ball head at the end of the loading shaft is designed to abut with the force end of the loading block, which can make the radial load applied by the hydraulic cylinder more evenly transmitted to the loading block. Due to the arc shape of the ball head, stress concentration can be effectively avoided during contact, ensuring that the load is evenly distributed during transmission, thereby making the radial load borne by the tool set and the bearing to be tested more stable and uniform, improving the accuracy and reliability of the test results, and more realistically simulating the stress condition of the aircraft body bearing under actual working conditions; the loading block is slidably arranged in the loading hole along its axial direction, which makes the loading block flexible to adapt to the displacement change of the loading shaft. When the hydraulic cylinder pushes the loading shaft to apply a radial load, the loading block can freely slide in the loading hole, thereby better maintaining a good contact state with the loading ball head and ensuring effective load transmission. Even if there is some small displacement deviation or vibration during the test, the loading block can adjust itself to ensure the stability and continuity of the test; the contact end of the loading block is used to put into the movable cavity and contact with the outer wall of the tool set. This design can accurately apply a radial load to the tool set, and then to the bearing to be tested. Through accurate contact positioning, deviation or loss during load transmission can be avoided, so that the radial load applied during the test can accurately simulate the force borne by the aircraft body bearing during actual operation, improving the precision and relevance of the test and providing a more reliable basis for evaluating bearing performance. Meanwhile, the abutment cooperation between the loading ball head and the force end of the loading block can effectively reduce the friction and wear between them compared with flat contact. The arc-shaped ball head has a relatively small contact area and the contact point can be adjusted with the load direction, thereby reducing the friction resistance, reducing energy loss and component wear due to friction, and avoiding the phenomenon of load deviation or deviation of the loading ball head. This not only prolongs the service life of the loading shaft and the loading block, reduces the maintenance cost of the equipment, but also ensures the stability and accuracy of load transmission during the test.

[0012] The utility model further sets up: the tool seat is set with detection hole for communicating with movable cavity, detection component includes setting displacement sensor in detection hole, displacement sensor detection end is provided with probe for with tool set outer wall contact.

[0013] The beneficial effects of the above technical solution are: the detection hole is arranged on the tool seat and is in communication with the movable cavity, and the displacement sensor is arranged in the detection hole, and the probe is arranged in contact with the outer wall of the tool sleeve, so that the displacement of the tool sleeve under the radial load can be accurately measured, the displacement sensor is in direct contact with the tool sleeve, the displacement data of the tool sleeve can be obtained in real time, the error caused by the intermediate link or indirect measurement is avoided, reliable basis is provided for accurately evaluating the deformation of the aircraft body bearing under the radial load, the performance and working state of the bearing are helpful to be understood, and the structure and function of the displacement sensor are not described in detail.

[0014] The utility model further sets up: the probe beginning end radial section is round arc shape setting and is formed with the detection ball head, the detection hole inner wall and the probe outer wall are connected with linear bearing between.

[0015] The beneficial effects of the above technical solution are: the detection ball head of the probe beginning end is round arc shape setting, the contact between the probe and the outer wall of the tool sleeve is more ideal, compared with the plane contact, the contact between the detection ball head and the tool sleeve is point contact or small area surface contact, the small displacement change of the tool sleeve can be more sensitively perceived, the measurement error caused by the large contact area is reduced, the accuracy of displacement detection is significantly improved, more reliable data is provided for accurately evaluating the deformation of the aircraft body bearing under the radial load, and the linear bearing is connected between the inner wall of the detection hole and the outer wall of the probe, the existence of the linear bearing greatly reduces the friction resistance of the probe when moving in the detection hole, when the tool sleeve is displaced under the radial load and drives the probe to move, the linear bearing can make the probe more smoothly slide in the detection hole, the problem that the probe is jammed or the measurement data is inaccurate caused by too much friction is avoided, the real-time and continuity of displacement detection are ensured, and the service life of the probe and related components can be prolonged.

[0016] The utility model further sets up: the driving part includes servo motor that sets up on test table, servo motor output end is coaxial with the core axle and is connected with the coupling between servo motor output end and the core axle.

[0017] The technical scheme has the beneficial effects that: in the above technical scheme, the servo motor is used as the driving element, so that the rotation speed of the mandrel can be accurately controlled, the servo motor has high-precision rotation speed adjustment performance, the rotation speed of the mandrel can be accurately set and adjusted according to test requirements, the test requirements of different aircraft body bearings under various working conditions can be met, the accurate rotation speed control is helpful for simulating different running states of the bearing in the actual flight process, so that the performance of the bearing can be more accurately tested, and the reliability and effectiveness of the test results are improved; meanwhile, the output end of the servo motor is coaxially connected with the mandrel and connected through the coupling, so that the stability of power transmission is ensured, the coaxial connection reduces vibration and energy loss caused by inconsistent axes, so that the power of the servo motor can be efficiently and stably transmitted to the mandrel to drive the bearing to be tested to stably run, and the use of the coupling further compensates for possible slight coaxiality deviation, enhances the reliability of the connection, ensures the continuity of power transmission in the test process, and avoids affecting the test results due to unstable power transmission. The coupling and the servo motor are both prior art, and therefore the structure and function thereof will not be described in detail.

[0018] The utility model further sets up: the tool cover is provided with the temperature measuring hole for aligning with the bearing position to be tested outside.

[0019] The technical scheme has the beneficial effects that: in the above technical scheme, the servo motor is used as the driving element, so that the rotation speed of the mandrel can be accurately controlled, the servo motor has high-precision rotation speed adjustment performance, the rotation speed of the mandrel can be accurately set and adjusted according to test requirements, the test requirements of different aircraft body bearings under various working conditions can be met, the accurate rotation speed control is helpful for simulating different running states of the bearing in the actual flight process, so that the performance of the bearing can be more accurately tested, and the reliability and effectiveness of the test results are improved; meanwhile, the output end of the servo motor is coaxially connected with the mandrel and connected through the coupling, so that the stability of power transmission is ensured, the coaxial connection reduces vibration and energy loss caused by inconsistent axes, so that the power of the servo motor can be efficiently and stably transmitted to the mandrel to drive the bearing to be tested to stably run, and the use of the coupling further compensates for possible slight coaxiality deviation, enhances the reliability of the connection, ensures the continuity of power transmission in the test process, and avoids affecting the test results due to unstable power transmission. The coupling and the servo motor are both prior art, and therefore the structure and function thereof will not be described in detail. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is a three-dimensional view of the utility model;

[0021] Figure 2 It is a three-dimensional view of the tool holder and the matching structure in the utility model;

[0022] Figure 3for Figure 2 a side sectional view;

[0023] Figure 4 for Figure 2 a partial sectional view of a top perspective view;

[0024] Figure 5 a sectional view of a tooling sleeve in the utility model. DETAILED DESCRIPTION

[0025] The utility model provides a kind of aircraft body bearing radial dynamic load testing machine, including test bed 1, tooling sleeve 11 and with tooling sleeve 11 cooperation mandrel 12 are provided on the test bed 1, the tooling sleeve 11 is passed and is equipped with tooling hole 111 for mandrel 12, the test cavity for outside bearing 112 to be tested installation and accommodation is formed between the inner peripheral wall of tooling hole 111 and the outer peripheral wall of mandrel 12, the test bed 1 is provided with the driving member for driving mandrel 12 to make axial rotation to drive bearing 112 to be tested to operate, the loading piece for applying radial load to tooling sleeve 11 to bearing 112 to be tested is applied radial load, and the detection assembly for being linked with loading piece to detect the load amount and displacement amount when bearing 112 to be tested operates, tooling seat 2 is provided on the test bed 1, the movable cavity 21 for tooling sleeve 11 movement is opened in the tooling seat 2, the loading piece includes hydraulic cylinder 3 being provided on test bed 1, the output end of hydraulic cylinder 3 is loading end for being placed into movable cavity 21 and applying radial load to tooling sleeve 11 when hydraulic cylinder 3 operates, the detection assembly includes load sensor 31 being provided on the loading end of hydraulic cylinder 3, load sensor 31 detection end is provided with loading shaft 32, loading shaft 32 is coaxially aligned with the loading end of hydraulic cylinder 3, the end of loading shaft 32 radial section is arranged as circular arc and is formed with loading ball head 321, loading hole 331 is passed through on the outer wall of test bed 1, loading block 33 is slidably arranged in loading hole 331 along its axial direction, the beginning end of loading block 33 is stress end for being abutted with loading ball head 321, the end of loading block 33 is contact end for being placed into movable cavity 21 and being contacted with the outer peripheral wall of tooling sleeve 11, detection hole 22 for being communicated with movable cavity 21 is opened in tooling seat 2, the detection assembly includes displacement sensor 4 being provided in detection hole 22, the detection end of displacement sensor 4 is provided with probe 41 for being contacted with the outer peripheral wall of tooling sleeve 11, the beginning end of probe 41 radial section is arranged as circular arc and is formed with detection ball head 411, linear bearing 42 is connected between the inner peripheral wall of detection hole 22 and the outer peripheral wall of probe 41, the driving member includes servo motor 5 being provided on test bed 1, the output end of servo motor 5 is coaxially connected with mandrel 12 and is connected with shaft coupling 51 between the output end of servo motor 5 and mandrel 12, temperature measuring hole 13 for being aligned with the position of outside bearing 112 to be tested is provided on tooling sleeve 11.

[0026] The basic principle and main features of the present application and the advantages of the present application are shown and described above. Those skilled in the art should understand that the present application is not limited by the above embodiments. The above embodiments and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application. These changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. An aircraft airframe bearing radial dynamic load tester characterized by: The test bench comprises a tool sleeve and a mandrel matched with the tool sleeve, a tool hole is formed through the tool sleeve for the mandrel to pass through, a test cavity is formed between the inner circumferential wall of the tool hole and the outer circumferential wall of the mandrel for mounting and accommodating the bearing to be tested, a driving member is arranged on the test bench for driving the mandrel to rotate axially to drive the bearing to be tested to rotate, a loading member is arranged on the test bench for applying a radial load to the tool sleeve to apply a radial load to the bearing to be tested, and a detection assembly is arranged on the test bench for cooperating with the loading member to detect the load and displacement of the bearing to be tested when the bearing to be tested rotates.

2. The radial dynamic load testing machine for aircraft engine bearing according to claim 1, characterized in that: The test bench comprises a tool sleeve and a mandrel matched with the tool sleeve, a tool hole is formed through the tool sleeve for the mandrel to pass through, a test cavity is formed between the inner circumferential wall of the tool hole and the outer circumferential wall of the mandrel for mounting and accommodating the bearing to be tested, a driving member is arranged on the test bench for driving the mandrel to rotate axially to drive the bearing to be tested to rotate, a loading member is arranged on the test bench for applying a radial load to the tool sleeve to apply a radial load to the bearing to be tested, and a detection assembly is arranged on the test bench for cooperating with the loading member to detect the load and displacement of the bearing to be tested when the bearing to be tested rotates.

3. An aircraft engine bearing radial dynamic load tester as claimed in claim 2, wherein: The detection assembly comprises a load sensor arranged on the loading end of the hydraulic cylinder, a loading shaft is arranged on the detection end of the load sensor, and the loading shaft is coaxially aligned with the loading end of the hydraulic cylinder.

4. The radial dynamic load testing machine for aircraft engine bearing as claimed in claim 3, wherein: The loading shaft is arranged in a circular arc shape at the end of the radial section and forms a loading ball head, a loading hole is formed through the outer wall of the test bench, a loading block is arranged in the loading hole along the axial direction of the loading hole, the initial end of the loading block is a force receiving end for abutting with the loading ball head, and the end of the loading block is a contact end for being arranged in the activity cavity and contacting with the outer circumferential wall of the tool sleeve.

5. An aircraft engine bearing radial dynamic load tester as set forth in claim 2 wherein: The tool holder is provided with a detection hole for communicating with the activity cavity, and the detection assembly comprises a displacement sensor arranged in the detection hole, and a probe is arranged on the detection end of the displacement sensor for contacting with the outer circumferential wall of the tool sleeve.

6. An aircraft engine bearing radial dynamic load tester as claimed in claim 5, wherein: The probe is arranged in a circular arc shape at the initial end of the radial section and forms a detection ball head, and a linear bearing is connected between the inner circumferential wall of the detection hole and the outer circumferential wall of the probe.

7. The radial dynamic load testing machine for aircraft engine bearing as claimed in claim 1 wherein: The driving member comprises a servo motor arranged on the test bench, the output end of the servo motor is coaxially connected with the mandrel, and a shaft coupling is connected between the output end of the servo motor and the mandrel.

8. The aircraft engine bearing radial dynamic load tester of Claim 1, wherein: The tool sleeve is provided with a temperature measuring hole for aligning with the position of the bearing to be tested.

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