CN114705387B - Push-back type vibration excitation control system and control method in airplane vibration fatigue test - Google Patents
Push-back type vibration excitation control system and control method in airplane vibration fatigue test Download PDFInfo
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- CN114705387B CN114705387B CN202210614960.1A CN202210614960A CN114705387B CN 114705387 B CN114705387 B CN 114705387B CN 202210614960 A CN202210614960 A CN 202210614960A CN 114705387 B CN114705387 B CN 114705387B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
Abstract
The invention discloses a push-back type vibration excitation control system and a control method in an airplane vibration fatigue test, belonging to the technical field of airplane tests, wherein the control system comprises a base, two vibration exciters which are respectively arranged at two sides of the base and are respectively provided with a vibration exciting rod, flexible connecting pieces which are respectively movably connected with the two vibration exciters, a fixed assembly arranged in the middle of the base, a test piece which is arranged between the two flexible connecting pieces and is clamped with the fixed assembly, and a PLC (programmable logic controller) electrically connected with the vibration exciters; the control system disclosed by the invention is reasonable in structural design, can alternatively load vibration excitation on the left side and the right side of a test piece, realizes the purpose of applying the vibration excitation while protecting the test piece, and is suitable for popularization and application.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a push-pull type vibration excitation control system and a push-pull type vibration excitation control method in airplane vibration fatigue testing.
Background
The airplane is subjected to repeated loads caused by sliding, gushing, maneuvering, landing impact, cabin pressurization and the like in the use process, fatigue cracks caused by alternating stress can be generated at parts such as a local stress concentration area, a defect area and the like of the airplane structure due to the repeated loads, the alternating stress continues to act, the fatigue cracks continuously expand to cause fatigue failure, and the fatigue failure is the fatigue of the airplane structure.
The vibration fatigue problem is one of the main problems of failure of an aviation structural part, so that a vibration fatigue test needs to be carried out on the structural part, when the vibration fatigue test of an airplane is carried out, the structural part is generally fixedly connected on a foundation through a root part, in order to effectively apply a vibration load reaching the prediction to the top of the structural part, the vibration excitation of the large aviation structural part is usually loaded in a response control mode; considering the requirement of protecting a structural member, the vibration exciter and the test piece cannot be fixedly connected through bolts or other modes, and the vibration excitation loading needs to be movably connected with the test piece in a flexible connection mode; however, for a large-load vibration fatigue test, the flexible connection mode has the problem of easy falling when the flexible connection mode receives a large tensile load, so that the vibration load cannot be loaded, and the effective performance of the airplane vibration fatigue test is limited.
Disclosure of Invention
Aiming at the technical problems, the invention provides a push-back type vibration excitation control system and a control method in an airplane vibration fatigue test.
The technical scheme of the invention is as follows: the push-pull type vibration excitation control system in the airplane vibration fatigue test comprises a base, a vibration exciter, a flexible connecting piece, a fixing assembly, a test piece and a PLC (programmable logic controller); the two vibration exciters are respectively arranged on two sides of the upper end surface of the base, vibration exciting rods are arranged on the opposite sides of the two vibration exciters, and vibration discs are sleeved on the two vibration exciting rods;
the number of the flexible connecting pieces is two, and the flexible connecting pieces comprise butt-joint rods, flexible disks and vacuum suckers; the two flexible disks are sleeved on the two butt-joint rods in a one-to-one correspondence mode respectively, a plurality of pushing rods sleeved with damping springs are slidably clamped on the circumferential directions of the two flexible disks, the two flexible disks are fixedly connected with the two vibrating disks in a one-to-one correspondence mode respectively through the pushing rods on the circumferential directions of the two flexible disks, and one ends of the two butt-joint rods are abutted to the two exciting rods in a one-to-one correspondence mode respectively; the two vacuum suckers are respectively and movably arranged at the other ends of the two butt-joint rods through regulating pieces;
the fixing assembly comprises a positioning box and a movable clamping plate, the positioning box is arranged in the middle of the upper end face of the base, a positioning seat penetrates through the middle of the upper end face of the positioning box, and a buffer spring abutted against the bottom end of the positioning seat is clamped in the positioning box; the two movable clamping plates are respectively and movably hinged to two sides of the upper end face of the positioning box, the two movable clamping plates are respectively and movably hinged to two side walls of the positioning seat through pulling plates, and a plurality of clamping rollers are movably hinged to one sides, opposite to the two movable clamping plates, of the two movable clamping plates;
the test piece is clamped between the two vacuum chucks, and the bottom end of the test piece is abutted to the upper end face of the positioning seat; an acceleration sensor is arranged at the joint of the test piece and one of the vacuum chucks;
and the PLC is respectively and electrically connected with the vibration exciter and the acceleration sensor.
Furthermore, a lifting seat is connected in a sliding and clamping mode inside the base, the top end of the lifting seat penetrates through the base, the vibration exciter and the fixing assembly are arranged on the lifting seat, supporting columns penetrating through the base are arranged at the left end and the right end of the lifting seat, and a sliding groove for providing a moving space for the supporting columns and a hydraulic oil cylinder for providing power for the supporting columns are arranged on the left side arm and the right side arm of the base; the supporting column is pushed by the hydraulic oil cylinder to move up and down along the sliding groove, so that the heights of the vibration exciter and the flexible connecting piece can be adjusted, and the test piece can be loaded with vibration excitations of different heights.
Furthermore, locking plates are arranged on the upper end face of the positioning box and positioned on the front side and the rear side of the two movable clamping plates, an arc-shaped tooth socket is arranged on each locking plate, locking gears capable of being meshed with the arc-shaped tooth sockets on the corresponding sides are rotatably clamped on the side walls of the two movable clamping plates, locking racks capable of being meshed with the locking gears on the corresponding sides are slidably clamped in the locking plates, and locking screw rods used for pushing the locking racks in the locking plates to move are in threaded connection with the tops of the locking plates; when the movable clamping plate rotates under the pulling action of the pulling plate, the locking gear rotates in the arc-shaped tooth groove, so that the stability of the movable clamping plate during rotation is improved; simultaneously, after the clamping roller on two movable clamp plates is abutted to the test piece, the locking screw is used for pushing the locking rack to move downwards and then to be engaged with the locking gear on the corresponding side for locking, so that the locking of the two movable clamp plates is realized, the test piece is prevented from loosening in the process of testing the vibration fatigue of the airplane, and the reliability of the test result of the vibration fatigue of the airplane is improved.
Furthermore, the adjusting piece comprises an adjusting part and a connecting part, one end of the adjusting part is provided with a screw rod in threaded connection with the butt joint rod, the other end of the adjusting part is provided with a gear ring, one end of the connecting part is rotatably clamped with the vacuum chuck, the other end of the connecting part is rotatably clamped with the adjusting part, an adjusting seat is rotatably clamped on the connecting part, and an adjusting gear meshed with the gear ring is arranged on the adjusting seat; the rotary adjusting seat drives the gear ring to rotate by utilizing the adjusting gear, so that the adjusting part drives the screw rod to rotate, and convenience of adjusting the clamping degree of the test piece by the vacuum chuck is realized.
Further, lift seat up end activity joint has the removal seat, and the both sides of removing the seat all are provided with the guide bar, and the outside cover of guide bar is equipped with the extrusion spring, and the lower extreme of two butt joint poles all is provided with run through the base and with remove seat up end fixed connection's anchor strut, when two vibration exciters exert thrust load to the test piece in turn, remove the seat along with the vibration reciprocating motion on the lift seat of test piece to form the guard action to the test piece.
Furthermore, each guide rod is sleeved with two extrusion springs and two shifting plates, the two shifting plates on the same guide rod are positioned between the two extrusion springs, each shifting plate penetrates through the lifting seat and the base, and the shifting plates positioned on the same side of the base are connected through an adjusting screw rod; through adjusting the distance between two stirring plates on the same guide rod, the extrusion force degree of the extrusion spring can be adjusted, and therefore the moving distance of the moving seat can be adjusted according to the vibration excitation size of the vibration exciter.
Furthermore, guide pipes are arranged at the joints of the flexible disc and the push rods, a plurality of guide wheels are rotatably clamped on the inner wall of each guide pipe, and guide grooves are arranged on the outer wall of each push rod corresponding to the positions of the guide wheels; through set up stand pipe and guide roller on the flexible disk, be favorable to improving the smoothness nature of catch bar when moving on the flexible disk to the interference of catch bar to aircraft vibration fatigue test result has been reduced.
Furthermore, an unlocking spring is sleeved on the locking screw rod; through setting up the locking spring, be favorable to breaking away from fast of locking rack and locking gear to be convenient for remove the testpieces, be favorable to improving aircraft vibration fatigue test efficiency.
Furthermore, the free ends of the push rods on the same flexible disk are connected through a connecting ring; through setting up the go-between, can guarantee the uniformity of each catch bar vibration frequency to the loaded homogeneity of test piece surface vibration excitation has been improved.
The invention also provides a control method of the push-pull type vibration excitation control system in the airplane vibration fatigue test, which comprises the following steps:
s1, placing the test piece on the positioning seat, and compressing the buffer spring after the positioning seat moves downwards under the pressure action of the test piece; in the moving process of the positioning seat, the two movable clamping plates are pulled to be close to each other through the two pulling plates, and the clamping rollers on the two movable clamping plates are used for fixing the test piece;
s2, respectively adjusting the distance between the vacuum chuck on the corresponding side and the test piece by using the two adjusting pieces to enable the two vacuum chucks to be respectively tightly attached to the two side walls of the test piece; then, an acceleration sensor is stuck at the joint of the test piece and one of the vacuum chucks;
and S3, respectively connecting external power supplies of the two vibration exciters, controlling the two vibration exciters to be opened through a PLC (programmable logic controller), and respectively sending control signals to the two vibration exciters by the PLC according to acceleration signals sent by the acceleration sensor to enable the two vibration exciters to alternately apply thrust loads to the two butt-joint rods on the corresponding sides, so that the control of vibration excitation in the airplane vibration fatigue test is realized.
Compared with the prior art, the beneficial effects of the invention are embodied in the following points:
firstly, the control system is reasonable in structural design, the flexible connecting piece is arranged between the excitation rod and the test piece, the problem that the traditional flexible connecting mode cannot bear tensile force to carry out vibration excitation loading on the test piece is solved on the premise of protecting the test piece, and the two vibration exciters are used for carrying out alternate loading on vibration fatigue loads on two side surfaces of the test piece, so that the reliability of an airplane vibration fatigue test is improved;
secondly, the vacuum chuck and the fixing assembly are used for clamping and fixing the test piece at the same time, so that the stability of the test piece in the test process of the airplane vibration fatigue test is effectively improved, and the positive promotion effect on improving the accuracy of the test result is achieved;
thirdly, the flexible connection between the vibration disk and the butt joint rod is realized by movably arranging a plurality of push rods fixedly connected with the vibration disk in the circumferential direction of the flexible disk, so that the application of vibration fatigue load in the vibration fatigue test process of the airplane is more uniform.
Drawings
FIG. 1 is a flow chart of a control method of the present invention;
FIG. 2 is a longitudinal section of the present invention;
FIG. 3 is a front view of the invention;
FIG. 4 is a left side view of the present invention;
FIG. 5 is a schematic view of the connection between the movable base and the lifting base;
FIG. 6 is a schematic view of the connection of the flexible disk of the present invention to a docking rod;
FIG. 7 is a schematic view showing the connection of the push rod of the present invention with the guide tube;
FIG. 8 is a view of the push rod of the present invention in a configuration in which it is disposed within a flexible disk;
FIG. 9 is a schematic view of the structure of the adjustment member of the present invention;
FIG. 10 is a schematic view of the attachment of the fixture assembly of the present invention to a test piece;
FIG. 11 is a schematic view of the attachment of the locking plate of the present invention to the movable clamp plate;
FIG. 12 is an enlarged, fragmentary, schematic view at A of FIG. 3 of the present invention;
FIG. 13 is a schematic view of the engagement of the locking rack and locking plate of the present invention;
wherein, 1-base, 10-lifting base, 100-supporting column, 101-sliding chute, 11-hydraulic oil cylinder, 12-moving base, 120-extrusion spring, 121-guide rod, 122-reinforcing rod, 123-toggle plate, 124-adjusting screw rod, 2-vibration exciter, 20-exciting rod, 21-vibration disk, 3-flexible connecting piece, 30-butt rod, 31-flexible disk, 310-damping spring, 311-push rod, 312-guide tube, 3120-guide wheel, 313-connecting ring, 32-vacuum chuck, 33-adjusting piece, 330-adjusting part, 331-connecting part, 332-screw rod, 333-gear ring, 334-adjusting base, 335-adjusting gear, 4-fixing component, 40-positioning box, 41-movable clamping plate, 410-pulling plate, 411-clamping roller, 412-locking gear, 42-positioning seat, 420-buffer spring, 43-locking plate, 430-arc tooth groove, 431-locking rack, 432-locking screw, 4320-unlocking spring and 5-test piece.
Detailed Description
Example 1
The push-back type vibration excitation control system in the airplane vibration fatigue test as shown in fig. 2, 3 and 6 comprises a base 1, a vibration exciter 2, a flexible connecting piece 3, a fixing assembly 4, a test piece 5 and a PLC (programmable logic controller); the two vibration exciters 2 are respectively arranged on two sides of the upper end face of the base 1, the opposite sides of the two vibration exciters 2 are respectively provided with a vibration exciting rod 20, and the two vibration exciting rods 20 are respectively sleeved with a vibration disc 21;
as shown in fig. 2, 3 and 9, two flexible connecting pieces 3 are provided, and the flexible connecting pieces 3 comprise butt-joint rods 30, flexible disks 31 and vacuum suction cups 32; the two flexible disks 31 are respectively sleeved on the two butt-joint rods 30 in a one-to-one correspondence manner, the circumferential directions of the two flexible disks 31 are respectively clamped with 6 pushing rods 311 sleeved with damping springs 310 in a sliding manner, the two flexible disks 31 are respectively fixedly connected with the two vibrating disks 21 in a one-to-one correspondence manner through the pushing rods 311 in the circumferential directions, and one ends of the two butt-joint rods 30 are respectively abutted with the two exciting rods 20 in a one-to-one correspondence manner; the two vacuum suction cups 32 are respectively and movably arranged at the other ends of the two butt-joint rods 30 through adjusting pieces 33; the adjusting part 33 comprises an adjusting part 330 and a connecting part 331, one end of the adjusting part 330 is provided with a screw rod 332 in threaded connection with the butt joint rod 30, the other end is provided with a gear ring 333, one end of the connecting part 331 is rotationally clamped with the vacuum chuck 32, the other end is rotationally clamped with the adjusting part 330, an adjusting seat 334 is rotationally clamped on the connecting part 331, and an adjusting gear 335 meshed with the gear ring 333 is arranged on the adjusting seat 334;
as shown in fig. 2, 3, 10 and 11, the fixing assembly 4 includes a positioning box 40 and a movable clamping plate 41, the positioning box 40 is disposed in the middle of the upper end surface of the base 1, a positioning seat 42 is disposed through the middle of the upper end surface of the positioning box 40, and a buffer spring 420 abutted against the bottom end of the positioning seat 42 is clamped in the positioning box 40; two movable clamping plates 41 are arranged, the two movable clamping plates 41 are respectively and movably hinged on two sides of the upper end surface of the positioning box 40, the two movable clamping plates 41 are respectively and movably hinged with two side walls of the positioning seat 42 through pull plates 410, and one sides of the two movable clamping plates 41 opposite to each other are respectively and movably hinged with 3 clamping rollers 411;
as shown in fig. 2, the test piece 5 is clamped between the two vacuum chucks 32, and the bottom end of the test piece 5 abuts against the upper end face of the positioning seat 42; an acceleration sensor is arranged at the joint of the test piece 5 and one of the vacuum chucks 32;
the PLC is respectively and electrically connected with the vibration exciter 2 and the acceleration sensor, and the PLC, the vibration exciter 2 and the acceleration sensor are all commercially available products.
Example 2
The embodiment describes a control method of the push-back vibration excitation control system in the aircraft vibration fatigue test in the embodiment 1, which includes the following steps:
s1, placing the test piece 5 on the positioning seat 42, and compressing the buffer spring 420 after the positioning seat 42 moves downwards under the pressure action of the test piece 5; in the moving process of the positioning seat 42, the two movable clamping plates 41 are pulled to approach each other through the two pulling plates 410, and the test piece 5 is fixed by the clamping rollers 411 on the two movable clamping plates 41;
s2, respectively rotating the two rotary adjusting seats 334, and driving the gear ring 333 to rotate by using the adjusting gear 335, so that the adjusting part 330 drives the screw rod 332 to rotate, thereby adjusting the distance between the two vacuum chucks 32 and the test piece 5, and enabling the two vacuum chucks 32 to respectively cling to the two side walls of the test piece; then an acceleration sensor is stuck at the joint of the test piece 5 and one of the vacuum chucks 32;
and S3, respectively connecting external power supplies of the two vibration exciters 2, controlling the two vibration exciters 2 to be opened through a PLC (programmable logic controller), and respectively sending control signals to the two vibration exciters 2 by the PLC according to acceleration signals sent by the acceleration sensor so that the two vibration exciters 2 alternately apply thrust loads to the two butt-joint rods 30 on the corresponding sides, thereby realizing the control of vibration excitation in the airplane vibration fatigue test.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2 and 4, a lifting seat 10 is slidably clamped inside a base 1, the top end of the lifting seat 10 penetrates through the base 1, a vibration exciter 2 and a fixing component 4 are both arranged on the lifting seat 10, supporting columns 100 penetrating through the base 1 are both arranged at the left end and the right end of the lifting seat 10, and a chute 101 for providing a moving space for the supporting columns 100 and a hydraulic cylinder 11 for providing power for the supporting columns 100 are both arranged on the left side arm and the right side arm of the base 1;
example 4
The present embodiment describes a control method of a push-back vibration excitation control system in an aircraft vibration fatigue test in embodiment 3, which is different from embodiment 2 in that:
before step S1, according to the application requirement of the vibration fatigue load of the test piece 5, the support column 100 is pushed by the hydraulic cylinder 11 to move up and down along the chute 101, so that the heights of the vibration exciter 2 and the flexible connecting piece 3 are adjusted, and the two vacuum suction cups 32 are clamped at the designated positions on the test piece 5.
Example 5
The present embodiment is different from embodiment 1 in that:
as shown in fig. 12 and 13, locking plates 43 are respectively disposed on the upper end surface of the positioning box 40 and located on the front side and the rear side of the two movable clamping plates 41, each locking plate 43 is provided with an arc-shaped tooth socket 430, the side walls of the two movable clamping plates 41 are rotatably clamped with locking gears 412 capable of being meshed with the arc-shaped tooth sockets 430 on the corresponding side, each locking plate 43 is slidably clamped with a locking rack 431 capable of being meshed with the locking gear 412 on the corresponding side, and the top of each locking plate 43 is in threaded connection with a locking screw 432 for pushing the locking rack 431 inside to move; the locking screw 432 is sleeved with an unlocking spring 4320.
Example 6
The present embodiment describes a control method of a push-back vibration excitation control system in an aircraft vibration fatigue test in embodiment 5, which is different from embodiment 2 in that:
in step S1, when the clamping rollers 411 of the two movable clamping plates 41 abut against the test piece 5, the locking screw 432 pushes the locking rack 431 to move downward and then to engage with the locking gear 412 on the corresponding side for locking, thereby locking the two movable clamping plates 41.
Example 7
The present embodiment is different from embodiment 3 in that:
as shown in fig. 2, 3, 5, the movable joint of the upper end face of the lifting seat 10 has a movable seat 12, both sides of the movable seat 12 are provided with guide rods 121, the outer sleeve of the guide rods 121 is provided with an extrusion spring 120, the lower ends of the two butt-joint rods 30 are provided with reinforcing rods 122 which penetrate through the base 1 and are fixedly connected with the upper end face of the movable seat 12, each guide rod 121 is sleeved with two extrusion springs 120 and two toggle plates 123, the two toggle plates 123 on the same guide rod 121 are located between the two extrusion springs 120, each toggle plate 123 penetrates through the lifting seat 10 and the base 1, and each toggle plate 123 on the same side of the base 1 is connected through an adjusting screw 124.
Example 8
The present embodiment describes a control method of a push-back vibration excitation control system in an aircraft vibration fatigue test in embodiment 7, which is different from embodiment 2 in that:
in step S3, when the two exciters 2 alternately apply thrust loads to the test piece 5, the moving base 12 reciprocates on the lifting base 10 along with the vibration of the test piece 5; meanwhile, according to the vibration excitation magnitude of the vibration exciter 2, the distance between the two poking plates 123 on the same guide rod 121 is adjusted by the adjusting screw rod 124, so that the extrusion degree of the extrusion spring 120 is adjusted.
Example 9
The present embodiment is different from embodiment 1 in that:
as shown in fig. 6, 7 and 8, the flexible disk 31 is provided with guide tubes 312 at the connection parts with the push rods 311, the inner wall of each guide tube 312 is rotatably clamped with 6 guide wheels 3120, and the outer wall of each push rod 311 is provided with guide grooves at the positions corresponding to the guide wheels 3120; the free ends of the push rods 311 on the same flexible disk 31 are connected by a connecting ring 313.
Claims (9)
1. The push-pull type vibration excitation control system in the airplane vibration fatigue test is characterized by comprising a base (1), a vibration exciter (2), a flexible connecting piece (3), a fixing assembly (4), a test piece (5) and a PLC (programmable logic controller); the vibration exciter comprises two vibration exciters (2), wherein the two vibration exciters (2) are respectively arranged on two sides of the upper end face of the base (1), vibration exciting rods (20) are respectively arranged on one opposite sides of the two vibration exciters (2), and vibration discs (21) are respectively sleeved at the tail ends of the two vibration exciting rods (20);
the number of the flexible connecting pieces (3) is two, and the flexible connecting pieces (3) comprise butt-joint rods (30), flexible discs (31) and vacuum suckers (32); the two flexible disks (31) are respectively sleeved on the two butt-joint rods (30) in a one-to-one corresponding manner, a plurality of pushing rods (311) are respectively circumferentially arranged on one sides, away from the excitation rods (20), of the two vibration disks (21), the free ends of the pushing rods (311) are connected through connecting rings (313), guide tubes (312) are slidably sleeved on the pushing rods (311), damping springs (310) are respectively sleeved between the end portions of the guide tubes (312) and the connecting rings (313), the flexible disks (31) are connected with the corresponding guide tubes (312), and one ends of the two butt-joint rods (30) are respectively abutted against the two excitation rods (20) in a one-to-one corresponding manner; the two vacuum suckers (32) are respectively and movably arranged at the other ends of the two butt-joint rods (30) through adjusting pieces (33);
the fixing assembly (4) comprises a positioning box (40) and a movable clamping plate (41), the positioning box (40) is arranged in the middle of the upper end face of the base (1), a positioning seat (42) penetrates through the middle of the upper end face of the positioning box (40), and a buffer spring (420) which is abutted to the bottom end of the positioning seat (42) is clamped in the positioning box (40); the two movable clamping plates (41) are respectively and movably hinged to two sides of the upper end face of the positioning box (40), the two movable clamping plates (41) are respectively and movably hinged to two side walls of the positioning seat (42) through pull plates (410), and a plurality of clamping rollers (411) are movably hinged to opposite sides of the two movable clamping plates (41);
the test piece (5) is clamped between the two vacuum suckers (32), and the bottom end of the test piece (5) is abutted against the upper end face of the positioning seat (42); an acceleration sensor is arranged at the joint of the test piece (5) and one of the vacuum chucks (32);
and the PLC is respectively and electrically connected with the vibration exciter (2) and the acceleration sensor.
2. The push-back type vibration excitation control system in the aircraft vibration fatigue test is characterized in that a lifting seat (10) is connected to the inside of the base (1) in a sliding and clamping mode, the top end of the lifting seat (10) penetrates through the base (1), the vibration exciter (2) and the fixing assembly (4) are arranged on the lifting seat (10), supporting columns (100) penetrating through the base (1) are arranged at the left end and the right end of the lifting seat (10), and sliding grooves (101) providing moving spaces for the supporting columns (100) and hydraulic cylinders (11) providing power for the supporting columns (100) are arranged on the left side arm and the right side arm of the base (1).
3. The push-back type vibration excitation control system in the aircraft vibration fatigue test is characterized in that locking plates (43) are arranged on the upper end face of the positioning box (40) and located on the front side and the rear side of the two movable clamping plates (41), arc-shaped tooth grooves (430) are formed in each locking plate (43), locking gears (412) capable of being meshed with the arc-shaped tooth grooves (430) on the corresponding side are rotationally clamped on the side walls of the two movable clamping plates (41), locking racks (431) capable of being meshed with the locking gears (412) on the corresponding side are slidably clamped in each locking plate (43), and locking screw rods (432) used for pushing the locking racks (431) inside each locking plate (43) to move are in threaded connection with the tops of the locking plates (43).
4. The push-back type vibration excitation control system in the aircraft vibration fatigue test of claim 1, wherein the adjusting part (33) comprises an adjusting part (330) and a connecting part (331), one end of the adjusting part (330) is provided with a screw rod (332) in threaded connection with the butt rod (30), the other end of the adjusting part is provided with a gear ring (333), one end of the connecting part (331) is in rotating clamping connection with the vacuum chuck (32), the other end of the connecting part is in rotating clamping connection with the adjusting part (330), the connecting part (331) is in rotating clamping connection with an adjusting seat (334), and the adjusting seat (334) is provided with an adjusting gear (335) meshed with the gear ring (333).
5. The push-back type vibration excitation control system in the aircraft vibration fatigue test is characterized in that the upper end surface of the lifting seat (10) is movably clamped with a moving seat (12), guide rods (121) are arranged on both sides of the moving seat (12), an extrusion spring (120) is sleeved outside the guide rods (121), and reinforcing rods (122) which penetrate through the base (1) and are fixedly connected with the upper end surface of the moving seat (12) are arranged at the lower ends of the two butt-joint rods (30).
6. The push-back type vibration excitation control system in the airplane vibration fatigue test is characterized in that two extrusion springs (120) and two poking plates (123) are sleeved on each guide rod (121), the two poking plates (123) on the same guide rod (121) are located between the two extrusion springs (120), each poking plate (123) penetrates through the lifting seat (10) and the base (1), and the poking plates (123) located on the same side of the base (1) are connected through an adjusting screw rod (124).
7. The push-back type vibration excitation control system for the aircraft vibration fatigue test is characterized in that a plurality of guide wheels (3120) are rotatably clamped on the inner wall of each guide tube (312), and a guide groove is formed in the outer wall of each push rod (311) corresponding to the position of each guide wheel (3120).
8. The push-and-pull type vibration excitation control system for the aircraft vibration fatigue test as claimed in claim 3, wherein an unlocking spring (4320) is sleeved on the locking screw (432).
9. The control method of the push-back type vibration excitation control system in the aircraft vibration fatigue test according to any one of claims 1 to 8, characterized by comprising the following steps:
s1, placing the test piece (5) on the positioning seat (42), and compressing the buffer spring (420) after the positioning seat (42) moves downwards under the pressure action of the test piece (5); in the moving process of the positioning seat (42), the two movable clamping plates (41) are pulled to be close to each other through the two pulling plates (410), and the test piece (5) is fixed by using clamping rollers (411) on the two movable clamping plates (41);
s2, utilizing the two adjusting pieces (33) to respectively adjust the distance between the vacuum suction cups (32) on the corresponding sides and the test piece (5), so that the two vacuum suction cups (32) are respectively tightly attached to the two side walls of the test piece; then an acceleration sensor is stuck at the joint of the test piece (5) and one of the vacuum chucks (32);
and S3, respectively connecting external power supplies of the two vibration exciters (2), controlling the two vibration exciters (2) to be started through a PLC (programmable logic controller), and respectively sending control signals to the two vibration exciters (2) by the PLC according to acceleration signals sent by the acceleration sensor so that the two vibration exciters (2) alternately apply thrust loads to the two butt-joint rods (30) on the corresponding sides, thereby realizing the control of vibration excitation in the airplane vibration fatigue test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210614960.1A CN114705387B (en) | 2022-06-01 | 2022-06-01 | Push-back type vibration excitation control system and control method in airplane vibration fatigue test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210614960.1A CN114705387B (en) | 2022-06-01 | 2022-06-01 | Push-back type vibration excitation control system and control method in airplane vibration fatigue test |
Publications (2)
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| DE19860168C2 (en) * | 1998-12-24 | 2002-07-11 | Lambis Tassakos | Method and sensor for measuring a closing pulse of a flap of a vehicle |
| JP4157011B2 (en) * | 2003-10-29 | 2008-09-24 | トヨタ自動車株式会社 | Vehicle towing device for side impact test |
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