CN114754964B - Test system and method for testing impact damage resistance of aircraft structure by discrete source - Google Patents

Test system and method for testing impact damage resistance of aircraft structure by discrete source Download PDF

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Publication number
CN114754964B
CN114754964B CN202210671507.4A CN202210671507A CN114754964B CN 114754964 B CN114754964 B CN 114754964B CN 202210671507 A CN202210671507 A CN 202210671507A CN 114754964 B CN114754964 B CN 114754964B
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plate
grooves
fixing
adjusting
semicircular arc
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CN114754964A (en
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刘小川
杨欢
白春玉
郭军
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
    • 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
    • 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
    • G01N3/04—Chucks
    • 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
    • G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Abstract

The invention discloses a test system and a method for testing the impact damage resistance of a discrete source of an airplane structure, belonging to the technical field of airplane testing, wherein the test system comprises a bottom plate, a pressure plate and an inner cylinder; the bottom plate is provided with a first fixing groove and a second fixing groove, the pressing plate is arranged at the upper end of the bottom plate and is provided with an adjusting groove, and a long bolt connected with the bottom plate is clamped in the adjusting groove; a flange is arranged at the central position of the pressure plate, and a positioning screw is arranged on the flange; the bottom end of the side wall of the inner cylinder is provided with a boss, the inner cylinder is clamped in the flange plate, and the boss is abutted to the positioning screw; the outer part of the inner cylinder is provided with a hoop, the inner part of the inner cylinder is provided with an auxiliary clamping plate, and the inner cylinder is in threaded connection with a pushing screw rod clamped with the auxiliary clamping plate; the test system disclosed by the invention is reasonable in structural design, can meet the test requirements of test pieces with different sizes, different impact angles and different impact positions, and effectively improves the efficiency of the test of the discrete source impact damage resistance of the airplane blade structure.

Description

Test system and method for testing impact damage resistance of aircraft structure by discrete source
Technical Field
The invention relates to the technical field of airplane testing, in particular to a system and a method for testing impact damage resistance of an airplane structure to discrete sources.
Background
During the flight of the airplane, the propeller blades play the roles of balancing the structural moment and providing power, and the propeller blades cannot normally run once the propeller blades fail, so that the performance of the propeller blades is very important for checking the safety of the airplane structure; the operation environment of the airplane is various, propeller blades can be impacted by external discrete sources such as sand dust, broken stones, hailstones and flying birds when rotating, the impact angles of the external discrete sources are complex and changeable, the impact positions are complex and various, the safety, the service life and the reliability of the propeller blades after being impacted by the external discrete sources are changed, the operation performance and the structural safety of the airplane are directly influenced, and the propeller blades are key factors for evaluating the service life of the airplane.
At present, in the direction of impact resistance of a blade structure to discrete sources, a test is mainly developed domestically through a numerical analysis method, in the aspect of the test, an impact point or an impact angle generally corresponds to a set of clamp devices, and the clamp devices cannot be reused, which means that when one parameter of a test piece, the impact angle and the impact position changes, a set of clamp devices needs to be redesigned and processed; meanwhile, the test piece and the clamp are required to be assembled and disassembled in each test, the work is particularly complex when the continuous blade structure discrete source impact resistance test is carried out, the workload and the repeated labor are obviously increased, and the efficiency of the aircraft blade structure discrete source impact resistance test is reduced.
Therefore, it is imperative to design a discrete source impact resistance test which can be simply and efficiently carried out on the aircraft blade structure under different test pieces, different impact angles and different impact positions.
Disclosure of Invention
Aiming at the technical problems, the invention provides a test system and a test method for testing the impact damage of an aircraft structure against a discrete source.
The technical scheme of the invention is as follows: the test system for testing the impact damage resistance of the aircraft structure to discrete sources comprises a bottom plate, a pressing plate and an inner cylinder; two first fixing grooves and two second fixing grooves penetrate through the bottom plate, the two first fixing grooves and the two second fixing grooves are parallel to each other, and the two second fixing grooves are located between the two first fixing grooves;
the pressing plate is arranged at the upper end of the bottom plate, adjusting grooves are formed in the positions, corresponding to the two second fixing grooves, of the pressing plate, and long bolts fixedly connected with the bottom plate through the second fixing grooves on the corresponding sides are slidably clamped in the two adjusting grooves; a through hole is formed in the central position of the pressure plate, a flange plate is fixedly arranged in the through hole, a plurality of threaded holes are uniformly distributed in the flange plate, and a positioning screw rod is in threaded connection with the inner part of each threaded hole;
the inner cylinder is formed by splicing two symmetrically arranged semi-circular plates, bosses are arranged at the bottom ends of the side walls of the two semi-circular plates, the two semi-circular plates are connected in a sliding and clamping manner in the flange plate after being spliced, and the two semi-circular plates are respectively connected with each positioning screw rod on the lower bottom surface of the flange plate in a butting manner through the bosses on the side walls of the two semi-circular plates; the outer walls of the two semicircular arc plates are respectively provided with an anchor ear, and the two anchor ears are fixedly connected through a fixing bolt; all be provided with supplementary splint on the inner wall of two semicircle boards, equal threaded connection has the promotion screw rod that rotates the joint with the supplementary splint that correspond the side on two semicircle boards.
Furthermore, a plurality of positioning clamping grooves are formed in the two second fixing grooves, positioning sleeves capable of being movably clamped with the positioning clamping grooves are sleeved on the long bolts, the pressing plates can be prevented from sliding on the bottom plate in the test process by means of cooperation of the positioning sleeves and the positioning clamping grooves, and the fixing effect of the test piece is improved.
Furthermore, a plurality of auxiliary clamping plates are arranged on the inner walls of the two semicircular plates, the auxiliary clamping plates are hinged with each other, pushing screw rods are arranged on the two semicircular plates and correspond to the auxiliary clamping plates, pushing blocks are slidably clamped on the side walls of the auxiliary clamping plates, connectors are rotatably clamped on the pushing blocks, and the pushing screw rods are movably hinged with the connectors on the corresponding sides; by arranging the plurality of auxiliary clamping plates, the clamping and fixing effects of the auxiliary clamping plates on the test piece are favorably improved, and the high-efficiency performance of the test of the discrete source impact damage resistance of the airplane blade structure is effectively ensured; meanwhile, the test pieces with different sizes can be replaced on the premise of not disassembling the anchor ear and the flange plate, and the test efficiency is improved.
Furthermore, guide sliding rods are arranged at positions corresponding to the positions of the bottoms of the two semicircular arc plates and the positions of the auxiliary clamping plates, sliding blocks are connected to the guide sliding rods in a sliding mode, adapters are connected to the sliding blocks in a rotating mode, and the adapters are connected with the bottom ends of the auxiliary clamping plates at the corresponding positions in a sliding mode; each auxiliary clamp plate can slide on the guide slide bar of the corresponding side, the consistency of each auxiliary clamp plate in moving can be improved, and the uniformity of the auxiliary clamp plates to the clamping moment of the test piece can be further improved.
Furthermore, the inside joint that rotates through the axle sleeve of ring flange has the rotary sleeve, and the screw hole is located the rotary sleeve, and the cover is equipped with the ring gear on the outer wall of rotary sleeve, and the inside joint that rotates of ring flange has the drive gear of being connected with the ring gear meshing, is provided with the actuating lever that runs through the ring flange on the drive gear, through set up the rotary sleeve inside the ring flange, is convenient for carry out rotation regulation to the inner tube to can realize the regulation of the anti discrete source impact position of test piece.
Further, the joint is rotated with the inner wall of ring flange after the actuating lever lower extreme runs through drive gear, the outside cover of actuating lever is equipped with respectively with the reset spring of the inner wall butt of drive gear lower terminal surface and ring flange, the ring flange is inside and be located the drive gear upper end and be provided with the locking tooth piece that can with drive gear meshing, through setting up reset spring and locking tooth piece, drive gear upwards removes along the actuating lever under reset spring's effect after the swivel nut is adjusted and is accomplished, and finally with locking tooth piece meshing locking, the stability of swivel nut in the process of the test has been improved.
Furthermore, an angle adjusting plate is movably clamped on the bottom plate, the bottom end of the inner cylinder is abutted against the angle adjusting plate, arc-shaped grooves are formed in the upper end and the lower end of one side, close to the bottom plate, of the angle adjusting plate, auxiliary sliding grooves are formed in the upper end surface of the bottom plate and correspond to the two arc-shaped grooves in position, and adjusting balls are clamped between the two groups of auxiliary sliding grooves which are oppositely arranged and the arc-shaped grooves in a sliding mode; all run through with the arc wall position department of corresponding on angle adjusting plate and the clamp plate and be provided with the regulation and lead to the groove, all be provided with the regulation push rod that runs through the regulation logical groove on angle adjusting plate and the clamp plate in proper order on two adjusting balls, through set up angle adjusting plate on the bottom plate, utilize adjusting push rod to promote the adjusting ball and remove in the arc wall, thereby utilize the adjusting ball with angle adjusting plate jack-up, can realize the regulation of each position inclination of angle adjusting plate, be convenient for carry out the anti discrete source impact damage test of different angles to the testpieces.
Furthermore, 2-6 fixing bolts are arranged on two sides of the hoop, the number of the fixing bolts is even, and the mounting load of the hoop can be balanced by arranging the even number of fixing bolts on the two sides of the hoop.
Furthermore, the upper end face of the flange plate is provided with scale marks, and the rotation angle of the rotary sleeve can be accurately controlled conveniently by arranging the scale marks on the flange plate.
Furthermore, a gasket is arranged between the boss and the rotary sleeve; the abrasion of the system in a high-frequency use state can be reduced by arranging the gasket, and the service life of the system is prolonged.
The invention also provides a test method for testing the aircraft structure to resist the impact damage of the discrete source, which comprises the following steps:
s1, after the two semi-circular arc plates are spliced, placing the two semi-circular arc plates on a bottom plate, then sleeving the flange plate outside the two semi-circular arc plates, and enabling the flange plate to be respectively abutted against the two bosses; at the moment, the adjusting groove on the pressing plate is superposed with the second fixing groove on the bottom plate; finally, sleeving the two anchor ears outside the two semi-circular arc plates through fixing bolts;
s2, inserting the test piece between the two semicircular plates, adjusting the position of the test piece, screwing the fixing bolt on the hoop, pushing the auxiliary clamping plate to move on the semicircular plate on the corresponding side by using the pushing screw rod, and fixing the test piece for the second time by using the auxiliary clamping plate;
s3, fixing the pressure plate with the bottom plate through a long bolt, then connecting a positioning screw rod on each threaded hole on the flange plate in a threaded manner, and enabling the lower end part of each positioning screw rod to be abutted against the upper end face of the boss;
s4, inserting bolts into the two first fixing grooves on the bottom plate, and fixing the bottom plate on a bearing wall by using the bolts; transmitting a discrete source to the surface of the test piece by using an air cannon, and carrying out an anti-discrete source impact damage test on the airplane blade structure;
s5, the test of the discrete source impact damage resistance of the airplane blade structure under the conditions of different impact angles and different impact positions is completed by adjusting the height of the pressure plate on the bottom plate and the rotating angle of the test piece in the semi-circular arc plate.
Compared with the prior art, the invention has the beneficial effects that:
firstly, the test system provided by the invention has reasonable structural design, and can realize simple and rapid adjustment of test pieces with different blade structures, any impact angles and any impact positions, thereby meeting the test requirements of test pieces with different sizes, different impact angles and different impact positions and effectively improving the efficiency and accuracy of the test of the discrete source impact damage resistance of the aircraft blade structure;
secondly, the auxiliary clamping plate is arranged in the inner cylinder, so that the inner cylinder can clamp and fix test pieces with different sizes, the clamping and fixing effects of the inner cylinder on the test pieces are improved, and the high-efficiency performance of an aircraft blade structure discrete source impact damage resistance test is promoted;
thirdly, the test system is convenient to assemble, the early time investment of the test for the discrete source impact damage resistance of the airplane blade structure is shortened, and the convenience of the test work is improved; meanwhile, the test system has lower maintenance cost and effectively reduces the economic investment of the test.
Drawings
FIG. 1 is a flow chart of the test method of the present invention;
FIG. 2 is a longitudinal section of the present invention;
FIG. 3 is a front view of the present invention;
FIG. 4 is a schematic structural view of the base plate of the present invention;
FIG. 5 is a schematic structural view of the angle adjusting plate of the present invention in an inclined state;
FIG. 6 is an enlarged partial schematic view at A of FIG. 2 of the present invention;
FIG. 7 is a schematic view of the connection of the flange to the swivel sleeve of the present invention;
FIG. 8 is a schematic view of the connection of the drive gear to the ring gear of the present invention;
FIG. 9 is an enlarged partial schematic view of the invention at B in FIG. 2;
FIG. 10 is a schematic view of the construction of the auxiliary splint of the present invention;
wherein, 1-bottom plate, 10-first fixed groove, 11-second fixed groove, 12-positioning clamping groove, 13-angle adjusting plate, 130-arc groove, 14-auxiliary sliding groove, 15-adjusting ball, 16-adjusting through groove, 17-adjusting push rod, 2-pressure plate, 20-adjusting groove, 21-long bolt, 210-positioning sleeve, 22-through hole, 23-flange plate, 230-threaded hole, 231-positioning screw rod, 24-rotating sleeve, 240-shaft sleeve, 241-gear ring, 242-driving gear, 243-driving rod, 2430-reset spring, 2431-locking tooth block, 3-inner cylinder, 30-semi-arc plate, 31-boss, 310-gasket, 32-hoop, 320-fixing bolt, 33-auxiliary clamping plate, 330-pushing screw rod, 331-pushing block, 332-connector, 34-guide slide bar, 340-slide block and 341-adapter.
Detailed Description
Example 1
The test system for testing the impact damage resistance of the aircraft structure to the discrete source as shown in fig. 2 and 4 comprises a bottom plate 1, a pressure plate 2 and an inner cylinder 3; two first fixing grooves 10 and two second fixing grooves 11 are arranged on the bottom plate 1 in a penetrating mode, the two first fixing grooves 10 and the two second fixing grooves 11 are parallel to each other, and the two second fixing grooves 11 are located between the two first fixing grooves 10;
as shown in fig. 2, 3, 4 and 9, the pressing plate 2 is arranged at the upper end of the bottom plate 1, adjusting grooves 20 are respectively arranged on the pressing plate 2 at positions corresponding to the two second fixing grooves 11, and long bolts 21 fixedly connected with the bottom plate 1 through the second fixing grooves 11 at the corresponding sides are slidably clamped in the two adjusting grooves 20; a through hole 22 is formed in the center of the pressure plate 2, a flange plate 23 is fixedly arranged in the through hole 22, 8 threaded holes 230 are uniformly distributed in the flange plate 23, and a positioning screw 231 is in threaded connection with the inner part of each threaded hole 230;
as shown in fig. 2 and 3, the inner cylinder 3 is formed by splicing two symmetrically arranged semicircular arc plates 30, bosses 31 are arranged at the bottom ends of the side walls of the two semicircular arc plates 30, the two semicircular arc plates 30 are slidably clamped inside the flange plate 23 after being spliced, and the two semicircular arc plates 30 are respectively abutted to each positioning screw 231 on the lower bottom surface of the flange plate 23 through the bosses 31 on the side walls; the outer walls of the two semicircular arc plates 30 are respectively provided with an anchor ear 32, and the two anchor ears 32 are fixedly connected through a fixing bolt 320; the inner walls of the two semicircular arc plates 30 are respectively provided with 1 auxiliary clamping plate 33, and the two semicircular arc plates 30 are respectively in threaded connection with 1 pushing screw rod 330 which is rotationally clamped with the auxiliary clamping plate 33 on the corresponding side; the number of the fixing bolts 320 on both sides of the anchor ear 32 is 4.
Example 2
The embodiment describes a test method of the test system for testing the aircraft structure against the impact damage of the discrete source in the embodiment 1, which includes the following steps:
s1, splicing the two semicircular arc plates 30, placing the spliced two semicircular arc plates on the bottom plate 1, sleeving the flange plate 23 outside the two semicircular arc plates 30, and enabling the flange plate 23 to be respectively abutted against the two bosses 31; at the moment, the adjusting groove 20 on the pressing plate 2 is superposed with the second fixing groove 11 on the bottom plate 1; finally, the two anchor ears 32 are sleeved outside the two semicircular arc plates 30 through the fixing bolts 320;
s2, inserting the test piece between the two semicircular arc plates 30, adjusting the position of the test piece, screwing the fixing bolt 320 on the hoop 32, pushing the auxiliary clamping plate 33 to move on the semicircular arc plate 30 on the corresponding side by using the pushing screw 330, and fixing the test piece for the second time by using the auxiliary clamping plate 33;
s3, fixing the pressure plate 2 and the bottom plate 1 through the long bolt 21, then connecting the positioning screw 231 on each threaded hole 230 on the flange plate 23 in a threaded manner, and enabling the lower end part of each positioning screw 231 to be abutted against the upper end surface of the boss 31;
s4, inserting bolts into the two first fixing grooves 10 on the bottom plate 1, and fixing the bottom plate 1 on a bearing wall by using the bolts; transmitting a discrete source to the surface of the test piece by using an air cannon, and carrying out an anti-discrete source impact damage test on the airplane blade structure;
s5, completing the test of the discrete source impact damage resistance of the airplane blade structure under the conditions of different impact angles and different impact positions by adjusting the height of the pressure plate 2 on the bottom plate 1 and the rotating angle of the test piece in the semi-circular arc plate 30.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, 3 and 10, the inner walls of the two semicircular plates 30 are respectively provided with 5 auxiliary clamping plates 33, the auxiliary clamping plates 33 are hinged with each other, the positions of the two semicircular plates 30 corresponding to the positions of the auxiliary clamping plates 33 are respectively provided with a pushing screw 330, the side wall of each auxiliary clamping plate 33 is slidably clamped with a pushing block 331, the pushing block 331 is rotatably clamped with a connector 332, and each pushing screw 330 is movably hinged with the connector 332 on the corresponding side; the bottom all is provided with the direction slide bar 34 with each supplementary splint 33 position correspondence department in two semicircular arc boards 30, and all the slip joint has slider 340 on each direction slide bar 34, all rotates the joint on each slider 340 to have adapter 341, and each adapter 341 respectively with the bottom slip joint of the supplementary splint 33 of corresponding position department.
Example 4
The embodiment describes a test method of the test system for testing the aircraft structure to resist the impact damage of the discrete source in the embodiment 3, which is different from the embodiment 2 in that:
in step S2, the respective pushing screws 330 are rotated, and the auxiliary clamp plates 33 corresponding to the respective pushing screws 330 slide on the guide slide bars 34 on the corresponding sides, so that the auxiliary clamp plates 33 on the two semicircular arc plates 30 are brought close to each other, thereby stably clamping the test piece.
Example 5
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, 3, 7, 8 and 9, a rotary sleeve 24 is rotatably clamped in the flange plate 23 through a shaft sleeve 240, the upper end surface of the flange plate 23 is provided with scale marks, a threaded hole 230 is positioned on the rotary sleeve 24, a gear ring 241 is sleeved on the outer wall of the rotary sleeve 24, a driving gear 242 meshed with the gear ring 241 is rotatably clamped in the flange plate 23, and a driving rod 243 penetrating through the flange plate 23 is arranged on the driving gear 242; a gasket 310 is arranged between the boss 31 and the rotary sleeve 24;
the lower end of the driving rod 243 penetrates through the driving gear 242 and then is rotationally clamped with the inner wall of the flange plate 23, a return spring 2430 which is respectively abutted against the lower end face of the driving gear 242 and the inner wall of the flange plate 23 is sleeved outside the driving rod 243, and a locking tooth block 2431 which can be meshed with the driving gear 242 is arranged inside the flange plate 23 and at the upper end of the driving gear 242.
Example 6
The embodiment describes a test method of the test system for testing the aircraft structure to resist the impact damage of the discrete source in the embodiment 5, which is different from the embodiment 2 in that:
in step S5, when the rotation angle of the test piece needs to be adjusted, each positioning screw 231 is unscrewed, the driving rod 243 is rotated after the driving rod 243 is pressed downward, the driving gear 242 drives the gear ring 241 to rotate, so that the rotating sleeve 24 drives the test piece to rotate, and the rotation angle of the test piece is adjusted by referring to the scale marks on the flange plate 23; after the adjustment of the rotary sleeve 24 is completed, the driving gear 242 moves upward along the driving rod 243 under the action of the return spring 2430, and finally engages with the locking tooth block 2431 to be locked, and finally, the positioning screws 231 are screwed again.
Example 7
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, 3, 4, 5 and 6, an angle adjusting plate 13 is movably clamped on the bottom plate 1, the bottom end of the inner cylinder 3 is abutted against the angle adjusting plate 13, the upper end and the lower end of one side of the angle adjusting plate 13 close to the bottom plate 1 are both provided with arc-shaped grooves 130, auxiliary sliding grooves 14 are respectively arranged at the positions of the upper end surface of the bottom plate 1 corresponding to the two arc-shaped grooves 130, and adjusting balls 15 are respectively clamped between the two groups of auxiliary sliding grooves 14 which are oppositely arranged and the arc-shaped grooves 130 in a sliding manner; the positions of the angle adjusting plate 13 and the pressure plate 2 corresponding to the arc-shaped grooves 130 are provided with adjusting through grooves 16 in a penetrating manner, and the two adjusting balls 15 are provided with adjusting push rods 17 which penetrate through the adjusting through grooves 16 on the angle adjusting plate 13 and the pressure plate 2 in sequence.
Example 8
The present embodiment describes a test method of the aircraft structure discrete source impact damage resistance test system in embodiment 7, which is different from embodiment 2 in that:
in step S5, when the inclination angle of the test piece needs to be adjusted, each long bolt 21 is loosened, the adjusting ball 15 is pushed by the adjusting push rod 17 to move in the arc-shaped groove 130, the adjusting ball 15 is used to jack up the angle adjusting plate 13, so as to adjust the inclination angle of each direction of the angle adjusting plate 13, and after the adjustment is completed, each long bolt 21 is screwed again.
Example 9
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2 and 4, two second fixing grooves 11 are provided with 9 positioning clamp grooves 12, and each long bolt 21 is sleeved with a positioning sleeve 210 which can be movably clamped with the positioning clamp grooves 12.
Example 10
The present embodiment is different from embodiment 1 in that:
the number of the fixing bolts 320 on both sides of the anchor ear 32 is 2.
Example 11
The present embodiment is different from embodiment 1 in that:
the number of the fixing bolts 320 on both sides of the anchor ear 32 is 6.
Example 12
The present embodiment is different from embodiment 3 in that:
the inner walls of the two semicircular arc plates 30 are provided with 8 auxiliary clamping plates 33.

Claims (7)

1. The test system for testing the impact damage resistance of the aircraft structure to the discrete source is characterized by comprising a bottom plate (1), a pressing plate (2) and an inner cylinder (3); the bottom plate (1) is provided with two first fixing grooves (10) and two second fixing grooves (11) in a penetrating mode, the two first fixing grooves (10) and the two second fixing grooves (11) are parallel to each other, and the two second fixing grooves (11) are located between the two first fixing grooves (10);
the pressing plate (2) is arranged at the upper end of the bottom plate (1), adjusting grooves (20) are formed in the positions, corresponding to the two second fixing grooves (11), of the pressing plate (2), and long bolts (21) fixedly connected with the bottom plate (1) through the second fixing grooves (11) on the corresponding sides are slidably clamped in the two adjusting grooves (20); a through hole (22) is formed in the center of the pressing plate (2), a flange plate (23) is fixedly arranged in the through hole (22), a plurality of threaded holes (230) are uniformly distributed in the flange plate (23), and a positioning screw (231) is in threaded connection with the inner part of each threaded hole (230);
the inner cylinder (3) is formed by splicing two symmetrically arranged semicircular arc plates (30), bosses (31) are arranged at the bottom ends of the side walls of the two semicircular arc plates (30), the two semicircular arc plates (30) are connected in a sliding and clamping mode in the flange plate (23) after being spliced, and the two semicircular arc plates (30) are respectively abutted to positioning screws (231) on the lower bottom surface of the flange plate (23) through the bosses (31) on the side walls of the two semicircular arc plates; the outer walls of the two semicircular arc plates (30) are respectively provided with a hoop (32), and the two hoops (32) are fixedly connected through a fixing bolt (320); auxiliary clamping plates (33) are arranged on the inner walls of the two semicircular arc plates (30), and pushing screw rods (330) which are rotationally clamped with the auxiliary clamping plates (33) on the corresponding sides are in threaded connection with the two semicircular arc plates (30);
a rotary sleeve (24) is rotatably clamped in the flange plate (23) through a shaft sleeve (240), the threaded hole (230) is positioned on the rotary sleeve (24), a gear ring (241) is sleeved on the outer wall of the rotary sleeve (24), a driving gear (242) in meshed connection with the gear ring (241) is rotatably clamped in the flange plate (23), and a driving rod (243) penetrating through the flange plate (23) is arranged on the driving gear (242);
an angle adjusting plate (13) is movably clamped on the bottom plate (1), the bottom end of the inner barrel (3) is abutted against the angle adjusting plate (13), arc-shaped grooves (130) are respectively arranged at the upper end and the lower end of one side, close to the bottom plate (1), of the angle adjusting plate (13), auxiliary sliding grooves (14) are respectively arranged at positions, corresponding to the two arc-shaped grooves (130), of the upper end surface of the bottom plate (1), and adjusting balls (15) are slidably clamped between the two groups of auxiliary sliding grooves (14) and the arc-shaped grooves (130) which are oppositely arranged; the adjusting ball is characterized in that the adjusting through grooves (16) are formed in the positions, corresponding to the arc-shaped grooves (130), of the angle adjusting plate (13) and the pressing plate (2) in a penetrating mode, and adjusting push rods (17) which sequentially penetrate through the adjusting through grooves (16) in the angle adjusting plate (13) and the pressing plate (2) are arranged on the adjusting balls (15).
2. The aircraft structure discrete source impact damage resistance test system according to claim 1, wherein a plurality of positioning clamping grooves (12) are arranged on each of the two second fixing grooves (11), and a positioning sleeve (210) which can be movably clamped with the positioning clamping grooves (12) is sleeved on each long bolt (21).
3. The aircraft structure discrete source impact damage resistance test system according to claim 1, wherein a plurality of auxiliary clamping plates (33) are arranged on the inner walls of the two semicircular arc plates (30), each auxiliary clamping plate (33) is hinged to each other, a pushing screw (330) is arranged at a position corresponding to each auxiliary clamping plate (33) on each semicircular arc plate (30), a pushing block (331) is slidably clamped on the side wall of each auxiliary clamping plate (33), a connecting head (332) is rotatably clamped on the pushing block (331), and each pushing screw (330) is movably hinged to the connecting head (332) on the corresponding side.
4. The aircraft structure discrete source impact damage resistance test system according to claim 3, wherein a guide sliding rod (34) is arranged at a position corresponding to each auxiliary clamping plate (33) at the bottom in the two semicircular plates (30), a sliding block (340) is slidably clamped on each guide sliding rod (34), an adapter (341) is rotatably clamped on each sliding block (340), and each adapter (341) is slidably clamped with the bottom end of the corresponding auxiliary clamping plate (33).
5. The aircraft structure discrete source impact damage resistance test system of claim 1, wherein the lower end of the driving rod (243) penetrates through the driving gear (242) and then is rotationally clamped with the inner wall of the flange plate (23), a return spring (2430) which is respectively abutted against the lower end face of the driving gear (242) and the inner wall of the flange plate (23) is sleeved outside the driving rod (243), and a locking tooth block (2431) which can be meshed with the driving gear (242) is arranged inside the flange plate (23) and located at the upper end of the driving gear (242).
6. The aircraft structure discrete source impact damage resistance test system of claim 1, wherein the number of the fixing bolts (320) on both sides of the hoop (32) is 2-6, and is even.
7. The method for testing the aircraft structure impact damage resistance test system according to any one of claims 1 to 6, characterized by comprising the following steps:
s1, splicing the two semicircular arc plates (30), placing the spliced two semicircular arc plates on the bottom plate (1), sleeving the flange plate (23) outside the two semicircular arc plates (30), and enabling the flange plate (23) to be respectively abutted against the two bosses (31); at the moment, the adjusting groove (20) on the pressing plate (2) is superposed with the second fixing groove (11) on the bottom plate (1); finally, the two anchor ears (32) are sleeved outside the two semicircular arc plates (30) through fixing bolts (320);
s2, inserting the test piece between the two semicircular arc plates (30), adjusting the position of the test piece, screwing the fixing bolt (320) on the hoop (32), pushing the auxiliary clamping plate (33) to move on the semicircular arc plate (30) on the corresponding side by using the pushing screw (330), and secondarily fixing the test piece by using the auxiliary clamping plate (33);
s3, fixing the pressure plate (2) and the bottom plate (1) through the long bolt (21), then connecting the positioning screw rods (231) on the threaded holes (230) on the flange plate (23) in a threaded manner, and enabling the lower end parts of the positioning screw rods (231) to be abutted against the upper end surface of the boss (31);
s4, inserting bolts into the two first fixing grooves (10) on the bottom plate (1), and fixing the bottom plate (1) on a bearing wall by using the bolts; transmitting a discrete source to the surface of the test piece by using an air cannon, and carrying out an anti-discrete source impact damage test on the airplane blade structure;
s5, testing the impact damage resistance of the aircraft blade structure under different impact angles and different impact positions by adjusting the height of the pressing plate (2) on the bottom plate (1) and the rotating angle of the test piece in the semi-circular arc plate (30).
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