CN114673734B - Vibration locking system for airplane strength test and method thereof - Google Patents
Vibration locking system for airplane strength test and method thereof Download PDFInfo
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- CN114673734B CN114673734B CN202210584417.1A CN202210584417A CN114673734B CN 114673734 B CN114673734 B CN 114673734B CN 202210584417 A CN202210584417 A CN 202210584417A CN 114673734 B CN114673734 B CN 114673734B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
- F16D1/076—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
- F16D1/08—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hub; with hub and longitudinal key
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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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
- G01M7/08—Shock-testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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Abstract
The invention discloses a vibration locking system for an airplane strength test and a method thereof, belonging to the technical field of airplane test, wherein the vibration locking system comprises a transmission shaft, a baffle plate, a stop shaft, a first locking assembly and a second locking assembly; one end of the transmission shaft is sequentially provided with a connecting part, an external thread sleeve and an internal thread hole, the connecting part is sleeved with a connecting flange, the baffle is connected to the external thread sleeve, the stop shaft is clamped inside the external thread sleeve, and the stop shaft is provided with a locking screw rod which can be in threaded connection with the internal thread hole; the first locking assembly is arranged on the stop shaft and used for locking and fixing the stop shaft and the internal thread sleeve; the second locking assembly is arranged on the baffle and used for locking and fixing the baffle and the connecting flange; the locking system disclosed by the invention is reasonable in structural design, and is beneficial to improving the connection stability between the transmission shaft and the connecting flange in the test process of airplane strength test.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a vibration locking system for an airplane strength testing test and a method thereof.
Background
The requirement that the structural strength of the airplane meets the design requirement is the basis for the successful design of the civil airplane body structure, and the aim that the structural weight is the lightest under the set design aim is always pursued by the airplane structural designer. For over 100 years of the birth of aircraft, ensuring structural strength of airframes is one of the first issues that aircraft designers began to consider. With the popularization of the airplane, an airplane designer continuously expands the problems to be considered in the airplane design by summarizing the encountered problems, and a perfect airplane body structure design verification system which relates to the body structure safety and covers the relevant specialties of static strength, dynamic response, fatigue and damage tolerance, bird collision, falling collision, flutter, forced landing on water and the like is formed at present.
In the process of testing the strength of the airplane, a rotating mechanism is needed, however, in the prior art, a transmission shaft of the rotating mechanism is generally connected with an input connecting flange by a common flat key, so that relative movement in all directions is easily caused between the transmission shaft and the input connecting flange under the continuous and violent vibration environment of the rotating mechanism, and the normal use of airplane testing equipment is seriously influenced; furthermore, even with the threaded connection of the protruding end of the drive shaft to the stop plate, it is still difficult to eliminate relative movement between the drive shaft and the input connection flange.
Disclosure of Invention
Aiming at the technical problems, the invention provides a vibration locking system for an airplane strength test and a method thereof.
The technical scheme of the invention is as follows: a vibration locking system for an airplane strength test comprises a transmission shaft, a baffle, a stop shaft, a first locking assembly and a second locking assembly; one end of the transmission shaft is sequentially provided with a connecting part and an external thread sleeve, one end of the connecting part, which is far away from the transmission shaft, is provided with an internal thread hole, the connecting part is sleeved with a connecting flange, and a first flat key is arranged at the joint of the connecting flange and the connecting part;
the baffle is in threaded connection with the external thread sleeve, and the end part of the baffle is abutted against the connecting flange;
the stop shaft is clamped inside the external thread sleeve, the end part of the stop shaft is abutted against the baffle, composite keys are arranged at the joints of the stop shaft, the baffle and the external thread sleeve, a locking screw rod penetrates through the stop shaft, and the locking screw rod can be in threaded connection with the internal thread hole;
the first locking component comprises a plurality of pushing rods and locking blocks, each pushing rod is movably clamped on the locking shaft, the push rods are located in the circumferential direction of the locking screw rod, one end, close to the locking screw rod, of each push rod is provided with an extrusion ball head, a first damping spring is clamped between one end, far away from the locking screw rod, of each push rod and the inner wall of each locking shaft, the number of the locking blocks is consistent with that of the push rods, each locking block is connected to each push rod in a sliding and clamping mode through a strip-shaped groove, each locking block is provided with an inclined part, each push rod is sleeved with a second damping spring located between each locking block and the end part of each push rod, chute for providing a moving space for each locking block is arranged on the side wall of each locking shaft at the position corresponding to each locking block, and an annular locking groove is formed in the position, corresponding to each locking block, on the inner wall of the external thread sleeve;
the second locking assembly comprises an installation disc, a positioning arc plate and an adjusting rod; the mounting disc fixed cover is established on the baffle, one side evenly distributed that is close to flange on the mounting disc has several installation counter bore, it is provided with the several to adjust the pole, each is adjusted the pole and all rotates the joint on the mounting disc, and with the position one-to-one of each installation counter bore, all the cover is equipped with the regulation tooth cover on each regulation pole, two liang of settings of location arc board are in each installation counter bore, and slide the joint with the installation counter bore respectively, one side that two location arc boards of every group are relative all is provided with the pinion rack, two pinion racks are connected with the regulation tooth cover meshing that corresponds position department respectively, the last department of corresponding with each installation counter bore position of flange all is provided with the locking groove.
Furthermore, a telescopic rod is connected between the two positioning arc plates of each group through a guide sleeve, return springs respectively abutted against the positioning arc plates and the telescopic rod are sleeved on the two guide sleeves, and the telescopic rod is connected with the mounting disc through a pull rod; stability when can improve the removal of location arc board through setting up uide bushing and telescopic link to improve second locking Assembly's vibration locking effect.
Furthermore, the composite key comprises a U-shaped key and a second flat key, and the second flat key and the U-shaped key are mutually clamped; through setting up the compound key by the mutual joint of second parallel key and U type key, be favorable to improving the stability of being connected between stop shaft and baffle, the external screw thread cover to reduce the vibration interference that the rotatory in-process of transmission shaft caused flange.
Furthermore, two first flat keys are symmetrically arranged at the connecting part of the connecting flange and the connecting part, and the two first flat keys are connected through a filling ring sleeved on the connecting part; the filling ring is used for connecting the two first flat keys, so that the portability of the first flat keys during installation and disassembly is improved, and the repeated utilization rate of the first flat keys is improved.
Furthermore, a self-locking assembly is arranged on the locking screw rod and comprises a self-locking lead screw, a moving sleeve and self-locking pins, the self-locking lead screw is rotatably clamped inside the locking screw rod, the moving sleeve is in threaded connection with the self-locking lead screw, a plurality of first ejector rods are uniformly distributed on the outer side wall of the moving sleeve in the circumferential direction, a second ejector rod is arranged inside the locking screw rod and corresponds to each first ejector rod in position, a plurality of self-locking pins are arranged, each self-locking pin is respectively clamped on the locking screw rod in a sliding mode, each self-locking pin is hinged with the first ejector rod and the second ejector rod at the corresponding positions, and a self-locking groove is arranged on the inner wall of the inner thread hole and corresponds to each self-locking pin in position; through rotatory auto-lock lead screw, make the movable sleeve remove along auto-lock lead screw length direction, be close to the second ejector pin that the position corresponds the department with each first ejector pin of movable hinge joint of movable sleeve, each self-locking round pin under the impetus of first ejector pin and second ejector pin with the locking of the self-locking groove joint on the internal thread downthehole wall to avoid the rotatory in-process locking screw of transmission shaft not hard up to drop, improved the locking effect of locking screw.
Furthermore, the inclined part is rotatably clamped with a ball abutted against the chute; through set up the ball on the rake, be favorable to improving the smoothness degree of locking piece when moving on the rake to make first locking Assembly's locking action rapider.
Furthermore, one side of each positioning arc plate, which is close to the inner wall of the locking groove, is provided with a wear-resistant coating; the wear-resistant coating is arranged on the positioning arc plate, so that the wear of the positioning arc plate is reduced, and the service life of the positioning arc plate can be prolonged.
Further, when the baffle plate is connected with the external thread sleeve and the locking screw rod is connected with the internal thread hole, the torque is controlled to be 10-15 Nm; by controlling the torque moment when the baffle plate is connected with the external thread sleeve and the locking screw rod is connected with the internal thread hole, the phenomenon that the workpiece slips and is broken due to metal fatigue is avoided on the premise that the connection tightness of the baffle plate and the external thread sleeve is ensured.
Furthermore, the moving directions of the two positioning arc plates in each group are kept consistent, so that the axial vibration generated to the connecting flange when the transmission shaft rotates can be reduced, and the stability of the connecting flange during rotation is improved.
The invention also provides a vibration locking method for the airplane strength test, which comprises the following steps:
s1, sleeving the connecting flange on the connecting part of the transmission shaft, and fixing the connecting flange and the connecting part through a first flat key;
s2, connecting the baffle plate with the external thread sleeve through threads, and enabling the baffle plate to be tightly attached to the connecting flange; then clamping the stop shaft inside the external thread sleeve, enabling the end part of the stop shaft to be abutted against the baffle plate, and fixing the stop shaft with the baffle plate and the external thread sleeve through the composite key; finally, the locking screw penetrates through the stop shaft and then is in threaded connection with the internal thread hole;
s3, continuously pressing the extrusion ball head in the rotation process of the locking screw rod, so that the pushing rod corresponding to the extrusion ball head moves along the length direction of the locking shaft, and the locking block connected with the pushing rod moves along the direction vertical to the pushing rod under the action of the strip-shaped groove and the inclined part and is finally clamped with the annular locking groove on the inner wall of the external thread sleeve;
s4, fixedly sleeving the mounting disc on the baffle plate, and enabling the mounting counter bores on the mounting disc to correspond to the locking groove positions on the baffle plate one by one; at the moment, every two groups of positioning arc plates are inserted into the corresponding locking grooves; then, each adjusting rod is rotated, and the adjusting gear sleeve is utilized to drive the two toothed plates of each group to move in the opposite direction, so that the two positioning arc plates of each group are fixedly clamped with the corresponding locking grooves.
Compared with the prior art, the beneficial effects of the invention are embodied in the following points:
firstly, the vibration locking system is reasonable in structural design, the connecting part of the connecting flange and the transmission shaft is locked and fixed by the stop shaft through the baffle, and then the stop shaft and the external thread sleeve of the transmission shaft are locked and fixed by the locking screw rod, so that the generation of vibration between the connecting flange and the transmission shaft in the rotation process is avoided;
secondly, the stop shaft and the internal thread sleeve part are locked and fixed for the second time by the first locking assembly, and the baffle plate and the connecting flange are locked and fixed by the second locking assembly, so that the connecting flange is prevented from loosening and falling off from the transmission shaft in the continuous and violent vibration process, the safety of the airplane strength test is improved, and the efficient performance of the airplane strength test is ensured;
and thirdly, the transmission shaft, the baffle, the stop shaft, the first locking assembly and the second locking assembly are detachably connected, so that the connecting flange has the advantages of easiness in disassembly and high repeated utilization rate on the premise of ensuring the stable locking effect of the connecting flange and the transmission shaft.
Drawings
FIG. 1 is a flow chart of the vibration locking method of the present invention;
FIG. 2 is a longitudinal section of the present invention;
FIG. 3 is a left side view of the present invention;
FIG. 4 is a schematic view of the connection of the attachment flange of the present invention to the attachment portion;
FIG. 5 is a schematic view of the connection of the stop plate to the stop shaft of the present invention;
FIG. 6 is a schematic view of the first locking assembly of the present invention connected to the stop shaft;
FIG. 7 is an enlarged, fragmentary, schematic view taken at A of FIG. 6 in accordance with the present invention;
FIG. 8 is a view of the locking block of the present invention in position on the pusher arm;
FIG. 9 is an enlarged partial schematic view of the invention at B in FIG. 2;
FIG. 10 is a schematic view of the attachment of the positioning arc plate of the present invention to the adjustment rod;
FIG. 11 is an enlarged, fragmentary, schematic view at C of FIG. 2 of the present invention;
FIG. 12 is a profile view of the self-locking pin of the present invention on the locking screw;
wherein, 1-transmission shaft, 10-connecting part, 100-internal threaded hole, 101-self-locking groove, 11-external threaded sleeve, 12-connecting flange, 120-locking groove, 13-first flat key, 130-loading ring, 2-baffle, 3-stop shaft, 30-composite key, 300-U-shaped key, 301-second flat key, 31-locking screw, 4-first locking component, 40-push rod, 400-extrusion ball head, 401-first damping spring, 402-second damping spring, 41-locking block, 410-strip groove, 411-inclined part, 4110-ball, 412-inclined groove, 413-annular locking groove, 5-second locking component, 50-mounting disc, 500-mounting counter bore, 51-positioning arc plate, 510-a toothed plate, 511-a guide sleeve, 512-a telescopic rod, 513-a return spring, 52-an adjusting rod, 520-an adjusting gear sleeve, 6-a self-locking assembly, 60-a self-locking screw rod, 61-a moving sleeve, 62-a self-locking pin, 63-a first ejector rod and 64-a second ejector rod.
Detailed Description
Example 1
As shown in fig. 2 and 4, the vibration locking system for the airplane strength test comprises a transmission shaft 1, a baffle plate 2, a stop shaft 3, a first locking assembly 4 and a second locking assembly 5; one end of the transmission shaft 1 is sequentially provided with a connecting part 10 and an external thread sleeve 11, one end of the connecting part 10, which is far away from the transmission shaft 1, is provided with an internal thread hole 100, the connecting part 10 is sleeved with a connecting flange 12, the connecting part 10 and the connecting part 12 are symmetrically provided with two first flat keys 13, and the two first flat keys 13 are connected through a filling ring 130 sleeved on the connecting part 10;
as shown in fig. 2, the baffle 2 is screwed on the external thread sleeve 11, and the end part of the baffle 2 is abutted with the connecting flange 12;
as shown in fig. 2 and 5, the stop shaft 3 is clamped inside the external thread sleeve 11, the end of the stop shaft 3 abuts against the baffle plate 2, the composite keys 30 are arranged at the joints of the stop shaft 3, the baffle plate 2 and the external thread sleeve 11, each composite key 30 comprises a U-shaped key 300 and a second flat key 301, and the second flat keys 301 and the U-shaped keys 300 are clamped with each other; a locking screw 31 penetrates through the stop shaft 3, and the locking screw 31 can be in threaded connection with the internal threaded hole 100;
as shown in fig. 2, 6, 7 and 8, the first locking assembly 4 includes 4 pushing rods 40 and locking blocks 41, the number of the pushing rods 40 is 4, each pushing rod 40 is movably clamped on the locking shaft 3 and is located in the circumferential direction of the locking screw 31, one end of each pushing rod 40 close to the locking screw 31 is provided with an extrusion ball 400, a first damping spring 401 is clamped between one end of each pushing rod 40 far from the locking screw 31 and the inner wall of the locking shaft 3, the number of the locking blocks 41 is consistent with the number of the pushing rods 40, each locking block 41 is slidably clamped on each pushing rod 40 through a strip-shaped groove 410, each locking block 41 is provided with an inclined portion 411, each pushing rod 40 is sleeved with a second damping spring 402 located between the locking block 41 and the end of the pushing rod 40, a chute 412 providing a moving space for the locking block 41 is arranged on the side wall of the locking shaft 3 corresponding to the position of each locking block 41, an annular locking groove 413 is formed in the inner wall of the external thread sleeve 11 and corresponds to each locking block 41 in position;
as shown in fig. 2, 3, 9 and 10, the second locking assembly 5 comprises a mounting plate 50, a positioning arc plate 51 and an adjusting rod 52; the fixed cover of mounting disc 50 is established on baffle 2, one side evenly distributed that is close to flange 12 on mounting disc 50 has 4 installation counter bores 500, it is provided with 4 to adjust pole 52, each adjusts pole 52 all rotates the joint on mounting disc 50, and with each installation counter bore 500 position one-to-one, all the cover is equipped with regulation tooth cover 520 on each adjusts pole 52, two liang of settings of location arc board 51 are in each installation counter bore 500, and respectively with installation counter bore 500 slip joint, one side that every two location arc boards 51 of a set are relative all is provided with pinion rack 510, two pinion rack 510 are connected with the regulation tooth cover 520 meshing that corresponds position department respectively, the moving direction of every two location arc boards 51 of a set keeps unanimous, the department that corresponds with each installation counter bore 500 position on flange 12 all is provided with locking groove 120.
Example 2
The embodiment describes a locking method of the vibration locking system for the airplane strength test in embodiment 1, which includes the following steps:
s1, sleeving the connecting flange 12 on the connecting part 10 of the transmission shaft 1, and fixing the connecting flange 12 and the connecting part 10 through the first flat key 13;
s2, connecting the baffle 2 with the external thread sleeve 11 in a threaded manner, and enabling the baffle 2 to be tightly attached to the connecting flange 12; then, the stop shaft 3 is clamped in the external thread sleeve 11, the end part of the stop shaft 3 is abutted against the baffle plate 2, and the stop shaft 3 is fixed with the baffle plate 2 and the external thread sleeve 11 through the composite key 30; finally, the locking screw 31 penetrates through the locking shaft 3 and then is in threaded connection with the internal threaded hole 100;
s3, continuously pressing the extrusion bulb 400 in the rotation process of the locking screw 31, so that the push rod 40 corresponding to the extrusion bulb 400 moves along the length direction of the stop shaft 3, the locking block 41 connected with the push rod 40 moves along the direction vertical to the push rod 40 under the action of the strip-shaped groove 410 and the inclined part 411, and is finally clamped with the annular locking groove 413 on the inner wall of the external thread sleeve 11;
s4, fixedly sleeving the mounting disc 50 on the baffle plate 2, and enabling the mounting counter bores 500 in the mounting disc 50 to correspond to the locking grooves 120 in the baffle plate 2 in a one-to-one mode; at this time, each set of positioning arc plates 51 arranged two by two are inserted into the corresponding locking groove 120; then, each adjusting rod 52 is rotated, and the two tooth plates 510 of each group are driven by the adjusting gear sleeve 520 to move in opposite directions, so that the two positioning arc plates 51 of each group are clamped and fixed with the corresponding locking grooves 120.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 9, a telescopic rod 512 is connected between the two positioning arc plates 51 of each group through a guide sleeve 511, return springs 513 respectively abutted against the positioning arc plates 51 and the telescopic rod 512 are sleeved on the two guide sleeves 511, and the telescopic rod 512 is connected with the mounting plate 50 through a pull rod.
Example 4
The present embodiment is different from embodiment 1 in that:
as shown in fig. 11 and 12, a self-locking assembly 6 is arranged on the locking screw 31, the self-locking assembly 6 includes a self-locking lead screw 60, a movable sleeve 61 and a self-locking pin 62, the self-locking lead screw 60 is rotatably clamped inside the locking screw 31, the movable sleeve 61 is in threaded connection with the self-locking lead screw 60, 4 first push rods 63 are uniformly distributed on the outer side wall of the movable sleeve 61 in the circumferential direction, second push rods 64 are arranged at positions corresponding to the first push rods 63 inside the locking screw 31, the self-locking pins 62 are 4, the self-locking pins 62 are respectively slidably clamped on the locking screw 31, the self-locking pins 62 are respectively hinged to the first push rods 63 and the second push rods 64 at positions corresponding to the positions, and self-locking grooves 101 are arranged at positions corresponding to the self-locking pins 62 on the inner wall of the internal thread hole 100.
Example 5
This example describes a locking method of the vibration locking system for the airplane strength test in example 4, which is different from example 2 in that it further includes S5,
s5, rotating the self-locking screw rod 60 to enable the moving sleeve 61 to move along the length direction of the self-locking screw rod 60, enabling the first push rods 63 movably hinged with the moving sleeve 61 to approach to the second push rods 64 at the corresponding positions, and enabling the self-locking pins 62 to be clamped and locked with the self-locking grooves 101 in the inner wall of the internal thread hole 100 under the pushing action of the first push rods 63 and the second push rods 64.
Example 6
The present embodiment is different from embodiment 1 in that:
as shown in fig. 7, a ball 4110 abutting against the inclined groove 412 is rotatably engaged with the inclined portion 411.
Example 7
The present embodiment is different from embodiment 1 in that:
as shown in fig. 10, a side of each positioning arc plate 51 close to the inner wall of the locking groove 120 is provided with a wear-resistant coating, such as a wear-resistant ceramic coating.
Example 8
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, the torque is controlled to be 10Nm when the retainer 2 is coupled to the male screw housing 11 and the lock screw 31 is coupled to the female screw hole 100.
Example 9
The present embodiment is different from embodiment 8 in that:
as shown in fig. 2, the torque is controlled to 15Nm when the retainer 2 is coupled to the male housing 11 and the lock screw 31 is coupled to the female screw hole 100.
Claims (9)
1. A vibration locking system for an airplane strength test is characterized by comprising a transmission shaft (1), a baffle (2), a stop shaft (3), a first locking assembly (4) and a second locking assembly (5); a connecting part (10) and an external thread sleeve (11) are sequentially arranged at one end of the transmission shaft (1), an internal thread hole (100) is formed in one end, far away from the transmission shaft (1), of the connecting part (10), a connecting flange (12) is sleeved on the connecting part (10), and a first flat key (13) is arranged at the connecting part of the connecting flange (12) and the connecting part (10);
the baffle (2) is in threaded connection with the external thread sleeve (11), and the end part of the baffle (2) is abutted against the connecting flange (12);
the stop shaft (3) is clamped inside the external thread sleeve (11), the end part of the stop shaft (3) is abutted against the baffle (2), composite keys (30) are arranged at the joints of the stop shaft (3) and the baffle (2) as well as the external thread sleeve (11), a locking screw (31) penetrates through the stop shaft (3), and the locking screw (31) can be in threaded connection with the internal thread hole (100);
the first locking assembly (4) comprises push rods (40) and locking blocks (41), the push rods (40) are provided with a plurality of push rods, each push rod (40) is movably clamped on the corresponding stop shaft (3) and is located in the circumferential direction of the corresponding stop screw (31), one end, close to the corresponding stop screw (31), of each push rod (40) is provided with an extrusion ball head (400), a first damping spring (401) is clamped between one end, far away from the corresponding stop screw (31), of each push rod (40) and the inner wall of the corresponding stop shaft (3), the number of the corresponding locking blocks (41) is consistent with the number of the corresponding push rods (40), each locking block (41) is slidably clamped on each push rod (40) through a strip-shaped groove (410), each locking block (41) is provided with an inclined portion (411), each push rod (40) is sleeved with a second damping spring (402) located between the corresponding locking block (41) and the end of the corresponding stop rod (40), inclined grooves (412) for providing a moving space for the locking blocks (41) are formed in the positions, corresponding to the positions of the locking blocks (41), on the side wall of the locking shaft (3), and annular locking grooves (413) are formed in the positions, corresponding to the positions of the locking blocks (41), on the inner wall of the external thread sleeve (11);
the second locking assembly (5) comprises a mounting disc (50), a positioning arc plate (51) and an adjusting rod (52); the mounting disc (50) is fixedly sleeved on the baffle plate (2), a plurality of mounting counter bores (500) are uniformly distributed on one side of the mounting disc (50) close to the connecting flange (12), a plurality of adjusting rods (52) are arranged, each adjusting rod (52) is rotationally clamped on the mounting disc (50), and the positions of the adjusting rods (52) are in one-to-one correspondence with the positions of the mounting counterbores (500), adjusting gear sleeves (520) are sleeved on the adjusting rods (52), the positioning arc plates (51) are arranged in the mounting counterbores (500) in pairs, and respectively with installation counter bore (500) slip joint, one side that two location arc boards (51) of every group are relative all is provided with pinion rack (510), two pinion rack (510) are connected with the regulation tooth cover (520) meshing that corresponds position department respectively, correspond the department on flange (12) with each installation counter bore (500) position and all be provided with locking groove (120).
2. The vibration locking system for the aircraft strength test is characterized in that a telescopic rod (512) is connected between two positioning arc plates (51) of each group through a guide sleeve (511), return springs (513) which are respectively abutted against the positioning arc plates (51) and the telescopic rod (512) are sleeved on the two guide sleeves (511), and the telescopic rod (512) is connected with a mounting disc (50) through a pull rod.
3. The vibration locking system for aircraft strength test experiments according to claim 1, wherein the composite key (30) comprises a U-shaped key (300) and a second flat key (301), and the second flat key (301) and the U-shaped key (300) are clamped with each other.
4. The vibration locking system for the aircraft strength test is characterized in that two first flat keys (13) are symmetrically arranged at the joint of the connecting flange (12) and the connecting part (10), and the two first flat keys (13) are connected through a filling ring (130) sleeved on the connecting part (10).
5. The vibration locking system for the aircraft strength test according to claim 1, wherein the locking screw (31) is provided with a self-locking assembly (6), the self-locking assembly (6) comprises a self-locking lead screw (60), a moving sleeve (61) and a self-locking pin (62), the self-locking lead screw (60) is rotatably clamped inside the locking screw (31), the moving sleeve (61) is in threaded connection with the self-locking lead screw (60), a plurality of first ejector rods (63) are uniformly distributed on the outer side wall of the moving sleeve (61) in the circumferential direction, a second ejector rod (64) is arranged inside the locking screw (31) and corresponds to each first ejector rod (63), a plurality of self-locking pins (62) are arranged, each self-locking pin (62) is respectively clamped on the locking screw (31) in a sliding manner, and each self-locking pin (62) is respectively hinged to the first ejector rod (63) and the second ejector rod (64) corresponding to the position, self-locking grooves (101) are formed in the inner wall of the internal thread hole (100) and correspond to the self-locking pins (62).
6. The vibration locking system for the aircraft strength test according to claim 1, wherein the inclined portion (411) is rotatably clamped with a ball (4110) abutting against the inclined groove (412).
7. The vibration locking system for the aircraft strength test according to claim 1, wherein each positioning arc plate (51) is provided with a wear-resistant coating on one side close to the inner wall of the locking groove (120).
8. The vibration locking system for the airplane strength test is characterized in that the torque of the baffle plate (2) is controlled to be 10-15 Nm when the baffle plate is connected with the external thread sleeve (11) and the locking screw (31) is connected with the internal thread hole (100).
9. The method for locking the vibration locking system for the airplane strength test according to any one of claims 1 to 8, characterized by comprising the following steps:
s1, sleeving the connecting flange (12) on the connecting part (10) of the transmission shaft (1), and fixing the connecting flange (12) and the connecting part (10) through a first flat key (13);
s2, connecting the baffle (2) with the external thread sleeve (11) in a threaded manner, and enabling the baffle (2) to be tightly attached to the connecting flange (12); then clamping the stop shaft (3) in the external thread sleeve (11), enabling the end part of the stop shaft (3) to be abutted against the baffle (2), and fixing the stop shaft (3) with the baffle (2) and the external thread sleeve (11) through a composite key (30); finally, the locking screw (31) penetrates through the stop shaft (3) and then is in threaded connection with the internal threaded hole (100);
s3, continuously pressing the extrusion ball head (400) in the rotation process of the locking screw rod (31), so that the push rod (40) corresponding to the extrusion ball head (400) moves along the length direction of the stop shaft (3), the locking block (41) connected with the push rod (40) moves along the direction vertical to the push rod (40) under the action of the strip-shaped groove (410) and the inclined part (411), and is finally clamped and fixed with the annular locking groove (413) on the inner wall of the external thread sleeve (11);
s4, fixedly sleeving the mounting disc (50) on the baffle plate (2), and enabling the mounting counter bores (500) on the mounting disc (50) to correspond to the locking grooves (120) on the baffle plate (2) in position one by one; at the moment, every two positioning arc plates (51) are inserted into the corresponding locking grooves (120); then, each adjusting rod (52) is rotated, and the two toothed plates (510) of each group are driven to move reversely by the adjusting toothed sleeve (520), so that the two positioning arc plates (51) of each group are clamped and fixed with the corresponding locking grooves (120).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210584417.1A CN114673734B (en) | 2022-05-27 | 2022-05-27 | Vibration locking system for airplane strength test and method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210584417.1A CN114673734B (en) | 2022-05-27 | 2022-05-27 | Vibration locking system for airplane strength test and method thereof |
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| CN114673734A CN114673734A (en) | 2022-06-28 |
| CN114673734B true CN114673734B (en) | 2022-08-05 |
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| CN202210584417.1A Active CN114673734B (en) | 2022-05-27 | 2022-05-27 | Vibration locking system for airplane strength test and method thereof |
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| CN116576203B (en) * | 2023-07-13 | 2023-09-08 | 深圳市百川滚珠丝杆有限公司 | Synchronous wheel structure of shaft coupling |
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| CN113606231A (en) * | 2021-07-30 | 2021-11-05 | 西安中车永电捷力风能有限公司 | Anti-loosening fastening device capable of transmitting large torque and mounting method thereof |
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|---|---|---|---|---|
| KR970045107U (en) * | 1995-12-20 | 1997-07-31 | 대우자동차주식회사 | Flywheel coupling flange for engine testing |
| DE10238361A1 (en) * | 2002-08-16 | 2004-03-04 | Johann A. Krause Maschinenfabrik Gmbh | Engine test electric motor drive unit has coupling with spring loaded probes to align threaded holes for clamp bolts |
| WO2017013147A1 (en) * | 2015-07-23 | 2017-01-26 | Avl List Gmbh | Arrangement for the rotational connection of a load machine of a test stand to a test specimen |
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| CN114673734A (en) | 2022-06-28 |
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