Aircraft bearing elastic support rigidity measuring system

Abstract

The invention discloses an aircraft bearing elastic support rigidity measuring system which comprises a test bed, a mounting seat, a clamping and fixing device, a stepless loading device and a displacement detection device. The mounting seat is provided with a mounting surface, and the clamping and fixing devices are connected to the two opposite ends of the mounting seat respectively and used for fixing the bearing elastic support after the two sides of the mounting edge at the end of the bearing elastic support oppositely clamp the mounting edge after relative movement in the axial direction. And the loading end of the stepless loading device is fixed with the mounting end of the bearing elastic support, and the connecting end of the stepless loading device is connected with the test bed so as to apply a vertical stepless load to the mounting end of the bearing elastic support and display the magnitude of the loading force. The displacement detection device is connected to the mounting base and used for displaying the displacement of the bearing elastic support mounting end in the loading direction after the bearing elastic support mounting end is subjected to the action of the loading force. The measuring device can adapt to fixing of the bearing elastic support within a certain outer diameter range, repeated design of a pressing device is avoided, meanwhile, stepless application of loads can be carried out, and the loading range of the loads is wide and continuously adjustable.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to an aerospace bearing elastic support stiffness measurement system. Background Art

[0002] The bearing elastic support structure (abbreviated as bearing elastic support) is commonly used in the field of aircraft engines to provide a support with a suitable stiffness value for the rotor bearing. Its radial stiffness is called elastic support stiffness, which is the ratio of the change in radial load to the change in displacement of the free end of the elastic support along the loading direction caused by it.

[0003] At present, in the common bearing spring support stiffness measurement device, the bearing spring support mounting edge is fixed by the adapter plate, the loading lock body is locked in the bearing mounting position at the front end of the bearing spring support, and the loading lock body is also connected to the weight tray. During the measurement, while adding weights, the displacement change of the measuring plane on the loading lock body is recorded. According to the definition of spring support stiffness, the ratio of the load change of the weight to the displacement change of the measuring plane is the spring support stiffness.

[0004] Existing spring-loaded support stiffness measurement devices have two main disadvantages: first, the installation fixture (adapter plate, loading lock body) is not universal, and the bearing spring-loaded support test piece needs to be redesigned and processed when the size changes, which not only has a long cycle and low efficiency but also wastes resources; second, the number of weights that can be placed is limited, and the upper limit of the applied load is low. When the stiffness of the bearing spring to be tested is large, the deformation is too small and the displacement test error is large, which leads to low accuracy of the stiffness test results. Summary of the invention

[0005] The present invention provides an aviation bearing elastic support stiffness measurement system to solve the technical problem that the existing measuring device needs to be redesigned and processed when the size of the bearing elastic support test piece changes, which not only has a long cycle, low efficiency and wastes resources, but also has a low upper limit of applied load. When the stiffness of the bearing elastic support to be measured is large, the deformation is too small and the displacement test error is large, which leads to low accuracy of the stiffness test result.

[0006] The technical solution adopted by the present invention is as follows: An aviation bearing spring support stiffness measurement system comprises: a test bench, a mounting seat installed on the test bench, a clamping fixture, a stepless loading device and a displacement detection device; the mounting seat is provided with a vertical mounting surface, and the clamping fixture is separately arranged and connected to the opposite ends of the mounting seat, so as to fix the bearing spring support after relative movement along the axial direction by clamping the mounting edges of the two sides of the mounting edges of the end of the bearing spring support relatively; the loading end of the stepless loading device is fixed to the mounting end of the bearing spring support for mounting the bearing, and the opposite connecting end of the stepless loading device is connected to the test bench, so as to apply a vertical stepless load to the mounting end of the bearing spring support and display the load force; the displacement detection device is connected to the mounting seat, and its detection end is used to contact the outer cylindrical surface of the bearing spring support mounting end or the loading end of the stepless loading device, so as to display the displacement of the bearing spring support mounting end along the loading direction after the loading force acts on it.

[0007] Furthermore, the mounting seat is detachably fixed to the test bench, and the middle part of the mounting surface thereof bulges outward to form a disc-shaped mounting boss, and the middle part of the mounting boss is processed with a mounting through hole axially passing through the mounting seat; the clamping and fixing device includes a hollow annular support drive disk, a plurality of movable rods arranged in sequence along the circumference of the support drive disk and sliding along the radial direction of the support drive disk, a sliding top column slidably installed in the mounting through hole, and a driving component for driving the sliding top column to move and self-lock; the support drive disk is connected to the mounting boss; the movable rod is used to extend radially under the action of the driving force to abut against one side of the mounting edge of the bearing elastic support, and the sliding top column is used to slide under the action of the driving component to abut against the other side of the mounting edge of the bearing elastic support, and then cooperate with the plurality of movable rods to relatively clamp the mounting edge of the bearing elastic support to fix the bearing elastic support during the continuous advancement of the sliding top column.

[0008] Furthermore, the supporting driving disk includes a spiral track disk movably mounted on the outer circle of the mounting boss, and a supporting disk located on the outer side of the spiral track disk and fixed to the end face of the mounting boss; a disc-shaped thread is processed on the outer facade of the spiral track disk facing the supporting disk; a plurality of movable rods are installed on the supporting disk, and each movable rod is processed with thread teeth matching the disc-shaped thread on the inner side surface facing the spiral track disk, so that when the spiral track disk is rotated by external force, the cooperation between its disc-shaped thread and the thread teeth can drive the plurality of movable rods to slide synchronously along the radial direction of the supporting disk.

[0009] Furthermore, the driving component includes a tail cover plate fixed to the end surface of the other end of the mounting seat, and a plurality of pushing screws threadedly connected to the tail cover plate; the inner end of the pushing screw extends into the mounting through hole to press against the end of the sliding top column.

[0010] Furthermore, the stepless loading device includes a loading lock body, a load loading assembly and a rigidity adjustment connection assembly; the loading lock body is used to be installed on the outer cylindrical surface of the bearing spring support mounting end, and the rigidity adjustment connection assembly is connected to the lower platen; the two ends of the load loading assembly are respectively connected to the loading lock body and the rigidity adjustment connection assembly, so as to be used to relatively tighten the loading lock body and the rigidity adjustment connection assembly under the action of external force, and then apply a vertical load to the mounting end of the bearing spring support through the loading lock body and display the load force size, and the rigidity adjustment connection assembly is also used to adjust the overall stiffness of the stepless loading device.

[0011] Furthermore, the loading lock body includes a loading plate and a locking plate that are relatively arranged, and a locking bolt for relatively locking and fixing the two; the loading plate and the locking plate are used to be relatively arranged on both sides of the outer circle of the bearing spring support mounting end, and are relatively locked by two sets of locking bolts to clamp the bearing spring support, and the locking plate is connected to the load loading assembly.

[0012] Furthermore, the load loading assembly includes a pull rod, a force sensor for measuring the load force, a stepless loader for steplessly loading the displacement load, a first connector and a second connector; one end of the pull rod is connected to the first connector, the other end of the first connector is connected to the loading lock body, the other end of the pull rod is connected to the force sensor, the other end of the force sensor is connected to the stepless loader, the other end of the stepless loader is connected to the second connector, and the other end of the second connector is connected to the rigid adjustment connection assembly.

[0013] Furthermore, the stepless loader includes an upper threaded barrel and a lower threaded barrel arranged at a relative interval, and a loading bolt threadedly connected therebetween; the upper end of the upper threaded barrel is connected to a force sensor, and the lower end of the lower threaded barrel is connected to a second connecting head, so as to control the displacement load size per unit torsion angle of the load loading component by setting the upper threaded barrel and the lower threaded barrel to have the same or different pitches and the same or opposite thread rotation directions.

[0014] Furthermore, the test bench includes an upper platen and a lower platen which are arranged in sequence and are horizontal; the stepless loading device also includes a torque-stop assembly for preventing the load loading assembly from twisting, and the torque-stop assembly includes a torque-stop base fixed on the lower platen, a torque-stop rod vertically supported on the torque-stop base, and a torque-stop wrench; one end of the torque-stop wrench is connected to the torque-stop rod, and the other end of the torque-stop wrench clamps the upper threaded tube.

[0015] Furthermore, the rigid adjustment connection assembly includes an elastic base plate, a pin connection seat fixed on the elastic base plate, multiple groups of pads and multiple groups of T-bolts; the elastic base plate is supported on the lower plate through multiple groups of pads, and is fixed to the lower plate through multiple groups of T-bolts; the second connecting head is hinged to the pin connection seat.

[0016] The present invention has the following beneficial effects: Compared with the prior art in which the clamping device is installed on the outer circumferential surface of the bearing spring and then the mounting edge is pressed against the mounting surface, in the aviation bearing spring stiffness measurement system of the present invention, the clamping and fixing devices are separately connected to the opposite ends of the mounting seat. When the bearing spring needs to be fixed, the two parts of the clamping and fixing device move relative to each other, and the two sides of the mounting edge of the bearing spring clamp the mounting edge relatively to fix the bearing spring. Since the clamping and fixing device does not need to be installed on the outer circumferential surface of the bearing spring, but is separately arranged at the two ends of the mounting seat, and the two sides of the mounting edge clamp the mounting edge relatively to fix the bearing spring, it is not limited by the outer diameter of the bearing spring, can adapt to the fixation of the bearing spring within a certain outer diameter range, avoids repeated design and processing of the clamping device, and improves the measurement. Efficiency and reduce fixture management costs; on the other hand, in the measuring device of the present invention, the stepless loading device can apply a vertical stepless load to the mounting end of the bearing spring support and display the load force, so that the spring support stiffness of the bearing spring support can be easily obtained in combination with the displacement change value of the bearing spring support mounting end along the loading direction detected by the displacement detection device. At the same time, the stepless loading device can apply the load steplessly, and the load loading range is wide, continuously adjustable, and not restricted by the mass of the weights. The loading range can cover a few kilograms to more than 1000 kilograms, which can effectively improve the measurement accuracy of large stiffness test pieces; the measuring device of the present invention has been successfully used in the bearing spring support stiffness test of a certain type of turboshaft engine, with normal function, expected results, simple operation, safety and reliability.

[0017] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a schematic diagram of the spatial structure of the squirrel cage bearing spring support; Figure 2 It is a schematic diagram of the spatial structure of an aviation bearing elastic support stiffness measurement system according to a preferred embodiment of the present invention; Figure 3 yes Figure 2 Schematic diagram of the clamping space structure of the middle clamping fixture and the mounting seat; Figure 4 This is a schematic diagram of the spatial structure of the clamping fixture. Figure 1 ; Figure 5 yes Figure 4 Schematic diagram of the main structure; Figure 6 This is a schematic diagram of the spatial structure of the clamping fixture. Figure 2 ; Figure 7 yes Figure 4 Schematic diagram of the spatial structure of the medium spiral orbit disk; Figure 8 yes Figure 4 Schematic diagram of the spatial structure of the middle support plate; Fig. 9 yes Figure 4 Schematic diagram of the spatial structure of the middle mounting seat; Fig.10 yes Figure 4 Schematic diagram of the spatial structure of the middle movable rod; Fig.11 yes Figure 2 Schematic diagram of the spatial structure of the stepless loading device.

[0019] Legend: 1. Test bench; 11. Upper platform; 12. Lower platform; 21, mounting seat; 201, mounting surface; 204, mounting boss; 205, mounting through hole; 41. movable rod; 411. threaded teeth; 42. sliding top column; 43. spiral track plate; 431. disc-shaped thread; 44. support plate; 45. tail cover plate; 5. Loading lock body; 51. Loading plate; 52. Locking plate; 53. Locking bolt; 6. Load loading assembly; 61. Pull rod; 62. Force sensor; 63. Stepless loader; 631. Upper threaded barrel; 632. Lower threaded barrel; 633. Loading bolt; 64. First connector; 65. Second connector; 7. Adjustment and connection assembly; 71. Elastic bottom plate; 72. Pin connection seat; 73. Spacer block; 74. T-bolt; 8. Anti-twist assembly; 81. Anti-twist base; 82. Anti-twist rod; 83. Anti-twist wrench; 9. displacement detection device; 91. mounting frame; 92. displacement sensor; 10. Bearing spring support; 101. Mounting edge; 102. Mounting end. DETAILED DESCRIPTION

[0020] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0021] Reference Figure 1-2The preferred embodiment of the present invention provides an aviation bearing elastic support stiffness measurement system, comprising: a test bench 1, a mounting seat 21 mounted on the test bench 1, a clamping fixture, a stepless loading device and a displacement detection device 9. A vertical mounting surface 201 is provided on the mounting seat 21, and the clamping fixture is separately provided and connected to the two ends of the mounting seat 21, so as to clamp the mounting edge 101 relatively on both sides of the mounting edge 101 provided at the end of the bearing elastic support 10 after axial movement towards each other, so as to fix the bearing elastic support 10. The loading end of the stepless loading device is fixed to the mounting end 102 of the bearing elastic support 10 for mounting the bearing, and the connecting end of the stepless loading device is connected to the test bench 1, so as to apply a vertical stepless load to the mounting end 102 of the bearing elastic support and display the load force. The displacement detection device 9 is connected to the mounting seat 21, and its detection end is used to contact the outer cylindrical surface of the bearing elastic support mounting end or the loading end of the stepless loading device, so as to display the displacement of the bearing elastic support mounting end along the loading direction after the loading force acts on it.

[0022] Compared with the prior art in which the clamping device is installed on the outer circumferential surface of the bearing spring and then the mounting edge is pressed against the mounting surface, in the aviation bearing spring stiffness measurement system of the present invention, the clamping and fixing devices are separately arranged and connected to the opposite ends of the mounting seat 21. When the bearing spring needs to be fixed, the two parts of the clamping and fixing device move relative to each other, and then the two sides of the mounting edge of the bearing spring clamp the mounting edge relatively to fix the bearing spring. Since the clamping and fixing device does not need to be installed on the outer circumferential surface of the bearing spring, but is separately arranged at the two ends of the mounting seat 21, and the two sides of the mounting edge clamp the mounting edge relatively to fix the bearing spring, it is not limited by the outer diameter of the bearing spring, can adapt to the fixation of the bearing spring within a certain outer diameter range, avoids repeated design and processing of the clamping device, and improves the measurement efficiency. On the other hand, the measuring device of the present invention can apply a vertical stepless load to the mounting end of the bearing spring support and display the load force, so that the spring support stiffness of the bearing spring support can be easily obtained by combining the displacement change value of the bearing spring support mounting end along the loading direction detected by the displacement detection device 9. At the same time, the stepless loading device can apply the load steplessly, and the load loading range is wide, continuously adjustable, and not restricted by the mass of the weights. The loading range can cover a few kilograms to more than 1000 kilograms, which can effectively improve the measurement accuracy of large stiffness test pieces. The measuring device of the present invention has been successfully used in the bearing spring support stiffness test of a certain type of turboshaft engine, with normal function, expected results, simple operation, safety and reliability.

[0023] Alternatively, if Figure 2 As shown, the test bench 1 includes an upper platen 11 and a lower platen 12 which are arranged in sequence and are horizontal. The mounting seat 21 is detachably fixed to the upper platen 11 by connecting screws. The end surface of the suspended end of the mounting seat 21 forms a mounting surface 201. The mounting seat 21 is simple to fix and remove, and is easy to implement.

[0024] Alternatively, if Figure 3-6 and Fig. 9 As shown, the middle of the mounting surface 201 is convex to form a disk-shaped mounting boss 204, and the middle of the mounting boss 204 is processed with a mounting through hole 205 that axially penetrates the mounting seat 21. The clamping and fixing device includes a hollow annular support drive disk, a plurality of movable rods 41 arranged in sequence along the circumference of the support drive disk and sliding along the radial direction of the support drive disk, a sliding top column 42 slidably installed in the mounting through hole 205, and a driving member for driving the sliding top column 42 to move and self-lock. The support drive disk is connected to the mounting boss 204. The movable rod 41 is used to extend radially under the action of the driving force to abut against one side of the mounting edge of the bearing elastic support, and the sliding top column 42 is used to slide under the action of the driving member to abut against the other side of the mounting edge of the bearing elastic support, and then cooperate with the plurality of movable rods 41 to relatively clamp the mounting edge of the bearing elastic support to fix the bearing elastic support during the continuous advancement of the sliding top column 42. During clamping, the multiple movable rods 41 are simultaneously extended radially by external force to abut against the outer side of the bearing elastic support mounting edge, and then the driving member is started to drive the sliding top column 42 to slide along the mounting through hole 205 to abut against the inner side of the bearing elastic support mounting edge, and the sliding top column 42 is continuously pushed forward so that the sliding top column 42 and the multiple movable rods 41 cooperate to relatively clamp the opposite sides of the bearing elastic support mounting edge, and at the same time, the driving member is self-locked to fix and tighten the sliding top column 42 to the bearing elastic support mounting edge. In this embodiment, through the cooperation of the supporting driving disk, the movable rod 41, the sliding top column 42 and the driving member, the clamping and fixing requirements of the bearing elastic support mounting edges of different diameters can be met, and the repeated design and processing of the test fixture can be avoided, and the efficiency can be improved and the fixture management cost can be reduced.

[0025] In this option, if Figure 4-10 As shown, the supporting drive disk includes a spiral track disk 43 movably mounted on the outer circumference of the mounting flange 204, and a supporting disk 44 located outside the spiral track disk 43 and fixed to the end surface of the mounting flange 204. A disc-shaped thread 431 is processed on the outer surface of the spiral track disk 43 facing the supporting disk 44, as shown in FIG. Figure 7 As shown. Multiple movable rods 41 are installed on the support plate 44, and the inner side surface of each movable rod 41 facing the spiral track plate 43 is processed with thread teeth 411 that cooperate with the disc-shaped thread 431, so that when the spiral track plate 43 is rotated by external force, the disc-shaped thread 431 cooperates with the thread teeth 411 to drive the multiple movable rods 41 to slide synchronously along the radial direction of the support plate 44. When clamping, the spiral track plate 43 is rotated, and the spiral track plate 43 cooperates with the thread teeth 411 on the movable rod 41, thereby driving the multiple movable rods 41 to slide synchronously along the radial direction of the spiral track plate 43 to extend to one side of the bearing spring support installation edge.

[0026] In this option, if Figure 6As shown, the driving member includes a tail cover plate 45 fixed to the end surface of the other end of the mounting seat 21, and a plurality of push screws threadedly connected to the tail cover plate 45. The inner extension end of the push screw extends into the mounting through hole 205 to abut against the end of the sliding top column 42. During operation, the push screw is rotated, and the push screw abuts against the sliding top column 42, and is locked and fixed by the push screw, while the sliding top column 42 is fixed, and the sliding top column 42 abuts against the mounting edge of the bearing elastic support and the plurality of movable rods 41, so that the plurality of movable rods 41 are positioned by the abutting force of the sliding top column 42. Of course, the movable rods 41 can also be positioned by other settings, such as by screwing the spiral track plate 43 through the screw and then screwing it into the screw holes arranged in sequence along the circumferential direction on the end surface of the mounting seat 21, so as to fix the spiral track plate 43.

[0027] Alternatively, if Figure 2 and Fig.11 As shown, the stepless loading device includes a loading lock body 5, a load loading assembly 6 and a rigidity adjustment connection assembly 7. The loading lock body 5 is used to be installed on the outer circumferential surface of the bearing elastic support mounting end, and the rigidity adjustment connection assembly 7 is connected to the lower plate 12. The two ends of the load loading assembly 6 are respectively connected to the loading lock body 5 and the rigidity adjustment connection assembly 7, so as to relatively tighten the loading lock body 5 and the rigidity adjustment connection assembly 7 under the action of external force, and then apply a vertical load to the mounting end of the bearing elastic support through the loading lock body 5 and display the load force. The rigidity adjustment connection assembly 7 is also used to adjust the rigidity of the stepless loading device as a whole.

[0028] In this option, if Figure 3 As shown, the loading lock body 5 includes a loading plate 51 and a locking plate 52 which are arranged opposite to each other, and a locking bolt 53 for locking and fixing the two relative to each other. The loading plate 51 and the locking plate 52 are used to be arranged opposite to each other on both sides of the outer circle of the bearing spring support mounting end, and are relatively locked by two sets of locking bolts 53 to clamp the bearing spring support, and the locking plate 52 is also connected to the load loading assembly 6. Preferably, as Figure 3 As shown, the contact points between the loading plate 51 and the locking plate 52 and the outer cylindrical surface of the bearing spring-support mounting end are formed by three arc surfaces connected in sequence, which can meet the loading requirements of the bearing spring-support mounting end within a certain diameter range. Therefore, in this optional solution, the loading lock body 5 has a simple structure and is easy to process and prepare. At the same time, through the cooperation of the loading plate 51 and the locking plate 52, it can adapt to the clamping requirements of the bearing spring-support mounting ends of different diameters, avoid repeated design and processing of the test fixture, improve efficiency and reduce fixture management costs.

[0029] In this option, if Figure 2 and Fig.11As shown, the load loading assembly 6 includes a pull rod 61, a force sensor 62 for measuring the load force, a stepless loader 63 for steplessly loading the displacement load, a first connector 64, and a second connector 65. One end of the pull rod 61 is connected to the first connector 64, the other end of the first connector 64 is connected to the loading lock body 5, the other end of the pull rod 61 is connected to the force sensor 62, the other end of the force sensor 62 is connected to the stepless loader 63, the other end of the stepless loader 63 is connected to the second connector 65, and the other end of the second connector 65 is connected to the rigid connection assembly 7.

[0030] Furthermore, if Fig.11 As shown, the stepless loader 63 includes an upper threaded barrel 631 and a lower threaded barrel 632 arranged at a relative interval, and a loading bolt 633 threadedly connected therebetween. The upper end of the upper threaded barrel 631 is connected to the force sensor 62, and the lower end of the lower threaded barrel 632 is connected to the second connector 65, so as to control the displacement load size of the load loading assembly 6 per unit torsion angle by setting the same or different pitches and the same or opposite thread rotation directions of the upper threaded barrel 631 and the lower threaded barrel 632. During loading, the upper and lower ends of the loading bolt 633 are respectively connected to the upper threaded barrel 631 and the lower threaded barrel 632, and the upper threaded barrel 631 and the lower threaded barrel 632 can be pulled closer and farther apart by twisting the loading bolt 633, that is, the loading and unloading process. In practice, different pitches can be selected for the upper threaded barrel 631 and the lower threaded barrel 632, or the upper threaded barrel 631 and the lower threaded barrel 632 can be controlled to have the same or opposite rotation directions, and the displacement load size applied by the loading bolt 633 rotating one circle can be controlled by these two methods. For example, assuming that the upper thread pitch of the loading bolt 633 is P1 and the lower thread pitch is P2, if the upper thread barrel 631 and the lower thread barrel 632 have the same rotation direction, the displacement load of the loading bolt 633 when it rotates one circle is the absolute value of P1-P2; if the upper thread barrel 631 and the lower thread barrel 632 have opposite rotation directions, the displacement load of the loading bolt 633 when it rotates one circle is P1+P2. In this way, the displacement load per unit torsion angle of the stepless loader 63 can be controlled to adapt to different loading requirements.

[0031] In this option, if Fig.11As shown, the rigidity adjustment connection assembly 7 includes an elastic base plate 71, a pin connection seat 72 fixed on the elastic base plate 71, multiple groups of pads 73 and multiple groups of T-bolts 74. The elastic base plate 71 is supported on the lower plate 12 by multiple groups of pads 73, and is fixed to the lower plate 12 by multiple groups of T-bolts 74. The second connector 65 is hinged to the pin connection seat 72. In this optional scheme, the function of the elastic base plate 71 is to adjust the series stiffness of the system; the load force applied by the stepless loading device is equal to the displacement load multiplied by the series stiffness of the system, that is, F=P×k, where F is the load force, P is the displacement load applied by the load loading assembly 6, and k is the series stiffness of the system, which is mainly determined by the stiffness of the bearing elastic support and the stiffness of the elastic base plate 71. By increasing or decreasing the thickness of the elastic base plate 71, the load force applied by the unit displacement load can be controlled, so that the loading accuracy can be controlled to meet the loading requirements of the device for test pieces with different stiffness.

[0032] Preferably, if Figure 2 and Fig.11 As shown, the stepless loading device also includes a torsion-stop assembly 8 for preventing the load loading assembly 6 from twisting. The torsion-stop assembly 8 includes a torsion-stop base 81 fixed on the lower plate 12, a torsion-stop rod 82 vertically supported on the torsion-stop base 81, and a torsion-stop wrench 83. One end of the torsion-stop wrench 83 is connected to the torsion-stop rod 82, and the other end of the torsion-stop wrench 83 clamps the upper threaded cylinder 631. In this preferred embodiment, as Fig.11 As shown, a square groove is machined inside the anti-twist base 81, and the lower end of the anti-twist rod 82 is clamped in the square groove to prevent the anti-twist rod 82 from twisting. The upper end cross-section of the anti-twist rod 82 is polygonal, and the anti-twist wrench 83 is mounted on the outer circle of the upper end of the anti-twist rod 82 to prevent twisting, or the upper end of the anti-twist rod 82 and the anti-twist wrench 83 are slotted to simultaneously connect the anti-twist key, and the anti-twist wrench 83 is forked tightly on the upper threaded tube 631 to prevent twisting, thereby preventing twisting of the load loading component 6.

[0033] Alternatively, if Figure 2 As shown, the displacement detection device 9 includes a mounting frame 91 fixed on the mounting seat 21, and a displacement sensor 92 which is vertically arranged and the upper end is fixedly connected to the mounting frame 91 and the lower end is suspended. Preferably, the surface on the loading plate 51 of the loading lock body 5 for contacting the detection end of the displacement sensor 92 is a plane to improve the detection accuracy and detection stability.

[0034] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aviation bearing elastic stiffness measurement system, characterized in that: include: A test bench (1), a mounting seat (21) mounted on the test bench (1), a clamping device, a stepless loading device and a displacement detection device (9); The mounting seat (21) is provided with a vertical mounting surface (201) and a mounting through hole (205) which penetrates the mounting surface (201) and the rear end surface of the mounting seat (21) in the axial direction. The clamping and fixing device comprises a hollow annular support drive disk connected to the mounting seat (21), a plurality of movable rods (41) which are sequentially arranged along the circumference of the support drive disk and slide along the radial direction of the support drive disk, a sliding top column (42) which is slidably installed in the mounting through hole (205), and a driving member for driving the sliding top column (42) to move and self-lock. The movable rod (41) is used to extend radially under the action of a driving force to abut against one side of the mounting edge (101) of the bearing elastic support (10), and the sliding top column (42) is used to slide under the action of the driving member to abut against the other side of the mounting edge of the bearing elastic support, thereby cooperating with the plurality of movable rods (41) to relatively clamp the mounting edge of the bearing elastic support to fix the bearing elastic support during the continuous advancement of the sliding top column (42); The stepless loading device comprises a loading lock body (5), a load loading assembly (6) and a rigidity adjustment connection assembly (7); the loading lock body (5) is used to be installed on the outer circle of the mounting end (102) of the bearing elastic support (10), and the rigidity adjustment connection assembly (7) is connected to the lower table (12) located below the test bench (1); the two ends of the load loading assembly (6) are respectively connected to the loading lock body (5) and the rigidity adjustment connection assembly (7), so as to relatively tighten the loading lock body (5) and the rigidity adjustment connection assembly (7) under the action of an external force, thereby applying a vertical load to the mounting end of the bearing elastic support through the loading lock body (5) and displaying the load force; the rigidity adjustment connection assembly (7) is also used to adjust the rigidity of the entire stepless loading device; The displacement detection device (9) is connected to the mounting seat (21), and its detection end is used to contact the outer cylindrical surface of the bearing elastic support mounting end or the loading end of the stepless loading device to display the displacement size of the bearing elastic support mounting end along the loading direction after the loading force acts on it.

2. The aviation bearing elastic stiffness measurement system according to claim 1, characterized in that: The mounting seat (21) is detachably fixed on the test bench (1), and the middle portion of the mounting surface (201) thereof is convex outward to form a disc-shaped mounting protrusion (204); The mounting through hole (205) passes through the middle of the mounting boss (204).

3. The aviation bearing elastic stiffness measurement system according to claim 2, characterized in that: The supporting driving disk comprises a spiral track disk (43) movably sleeved on the outer circle of the mounting boss (204), and a supporting disk (44) located outside the spiral track disk (43) and fixed to the end surface of the mounting boss (204); A disc-shaped thread (431) is processed on the outer surface of the spiral track disc (43) facing the support disc (44); A plurality of movable rods (41) are mounted on a support disk (44), and thread teeth (411) cooperating with the disc-shaped threads (431) are processed on the inner side surface of each movable rod (41) facing the spiral track disk (43), so that when the spiral track disk (43) is rotated by an external force, the plurality of movable rods (41) are driven to slide synchronously along the radial direction of the support disk (44) through the cooperation between the disc-shaped threads (431) and the thread teeth (411).

4. The aviation bearing elastic stiffness measurement system according to claim 2, characterized in that: The driving component comprises a tail cover plate (45) fixed to the end surface of the other end of the mounting seat (21), and a plurality of driving screws threadedly connected to the tail cover plate (45); The inner extension end of the push screw extends into the installation through hole (205) to abut against the end of the sliding top column (42).

5. The aviation bearing elastic stiffness measurement system according to claim 2, characterized in that: The loading lock body (5) comprises a loading plate (51) and a locking plate (52) which are arranged opposite to each other, and a locking bolt (53) for locking and fixing the two relative to each other; The loading plate (51) and the locking plate (52) are arranged relatively on two sides of the outer circle of the bearing spring support installation end, and are relatively locked by two sets of locking bolts (53) to clamp the bearing spring support, and the locking plate (52) is connected to the load loading assembly (6).

6. The aviation bearing elastic stiffness measurement system according to claim 2, characterized in that: The load loading assembly (6) comprises a pull rod (61), a force sensor (62) for measuring the magnitude of the load force, a stepless loader (63) for steplessly loading the displacement load, a first connector (64) and a second connector (65); One end of the pull rod (61) is connected to the first connector (64), the other end of the first connector (64) is connected to the loading lock body, the other end of the pull rod (61) is connected to the force sensor (62), the other end of the force sensor (62) is connected to the stepless loader (63), the other end of the stepless loader (63) is connected to the second connector (65), and the other end of the second connector (65) is connected to the rigidity adjustment connection assembly (7).

7. The aviation bearing elastic stiffness measurement system according to claim 6, characterized in that: The stepless loader (63) comprises an upper threaded cylinder (631) and a lower threaded cylinder (632) which are arranged relatively spaced apart, and a loading bolt (633) threadedly connected between the upper threaded cylinder and the lower threaded cylinder. The upper end of the upper threaded barrel (631) is connected to the force sensor (62), and the lower end of the lower threaded barrel (632) is connected to the second connector (65), so that the displacement load per unit torsion angle of the load applying assembly (6) can be controlled by setting the upper threaded barrel (631) and the lower threaded barrel (632) to have the same or different pitches and the same or opposite thread rotation directions.

8. The aviation bearing elastic stiffness measurement system according to claim 7, characterized in that: The test bench (1) also includes an upper platform (11) located above and horizontally; The stepless loading device also includes a torsion-stop assembly (8) for preventing the load loading assembly (6) from twisting, the torsion-stop assembly (8) including a torsion-stop base (81) fixed on the lower platform (12), a torsion-stop rod (82) vertically supported on the torsion-stop base (81), and a torsion-stop wrench (83); One end of the anti-torque wrench (83) is connected to the anti-torque rod (82), and the other end of the anti-torque wrench (83) clamps the upper threaded cylinder (631).

9. The aviation bearing elastic stiffness measurement system according to claim 8, characterized in that: A square groove is machined in the anti-twist base (81), and the lower end of the anti-twist rod (82) is clamped in the square groove, so as to prevent the anti-twist rod (82) from twisting. The cross section of the upper end of the anti-twist rod (82) is polygonal, and the anti-twist wrench (83) is sleeved on the outer circle of the upper end of the anti-twist rod (82) to prevent twisting, or a anti-twist key is provided between the upper end of the anti-twist rod (82) and the anti-twist wrench (83) to connect the two at the same time through a slot; The torque-stopping wrench (83) is forked to tighten the upper threaded cylinder (631) to stop the torque, thereby achieving torque-stopping of the load-applying assembly (6).

10. The aviation bearing elastic stiffness measurement system according to claim 8, characterized in that: The rigidity-adjusting connection assembly (7) comprises an elastic base plate (71), a pin connection seat (72) fixed on the elastic base plate (71), a plurality of groups of cushion blocks (73) and a plurality of groups of T-bolts (74); The elastic bottom plate (71) is supported on the lower plate (12) by a plurality of sets of cushion blocks (73), and is fixed to the lower plate (12) by a plurality of sets of T-bolts (74); The second connecting head (65) is hingedly connected to the pin connecting seat (72).

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