CN117109861B - System and method for measuring ground load and simulating heading speed of full-machine landing impact - Google Patents
System and method for measuring ground load and simulating heading speed of full-machine landing impact Download PDFInfo
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- CN117109861B CN117109861B CN202311377801.5A CN202311377801A CN117109861B CN 117109861 B CN117109861 B CN 117109861B CN 202311377801 A CN202311377801 A CN 202311377801A CN 117109861 B CN117109861 B CN 117109861B
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000012360 testing method Methods 0.000 claims abstract description 40
- 238000004088 simulation Methods 0.000 claims abstract description 33
- 238000013016 damping Methods 0.000 claims description 34
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 16
- 229910052782 aluminium Inorganic materials 0.000 claims description 16
- 238000005259 measurement Methods 0.000 claims description 12
- 230000009471 action Effects 0.000 claims description 7
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Classifications
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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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- 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
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/004—Testing the effects of speed or acceleration
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- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention discloses a system and a method for measuring the ground load and simulating the course speed of the landing impact of a whole aircraft, which belong to the technical field of aircraft tests, wherein the system comprises a support frame arranged on the ground, an accelerated dropping component arranged above the inside of the support frame, a test model arranged on the lower bottom surface of the accelerated dropping component and a course speed simulation component arranged below the ground and positioned inside the support frame; the system provided by the invention has reasonable structural design, can simulate the relative motion of the machine wheel and the ground in a laboratory environment, can measure the ground impact load of the machine wheel, and has the advantages of high integration level, stability and reliability.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a system and a method for measuring the ground load of full-aircraft landing impact and simulating the heading speed.
Background
The full-aircraft structural landing impact test is a test of impact force and structural strength which can be born by a flight platform when landing to the ground under a certain distance height, and in order to verify the buffer performance of an aircraft landing gear under the action of a carrier load, the dynamic response of an aircraft body, the reliability of important parts, overload born by a driver, passengers and airborne equipment and the like, the carrier aircraft needs to pass the full-aircraft structural landing impact test, and the carrier load and the dynamic response of the aircraft body and the important equipment caused by the carrier ground load are checked in a laboratory environment.
The course speed simulation and the ground load test of the airplane wheels are important points of the landing impact test of the whole airplane structure, however, a system capable of simultaneously simulating the course speed and testing the ground load of the airplane wheels is not available in the prior art.
Disclosure of Invention
Aiming at the technical problems, the invention provides a system and a method for measuring the ground load of the landing impact of a whole machine and simulating the heading speed.
The technical scheme of the invention is as follows: the system comprises a support frame arranged on the ground, an accelerating and falling assembly arranged above the inside of the support frame, a test model arranged on the lower bottom surface of the accelerating and falling assembly, and a course speed simulation assembly arranged below the ground and positioned inside the support frame; the ground is provided with a mounting cavity for mounting the heading speed simulation component;
the accelerated falling assembly comprises a fixed plate arranged above the inside of the support frame, a movable plate which is clamped inside the support frame through a sliding rod in a sliding way and is positioned below the fixed plate, and a driving motor which is clamped on the upper end face of the fixed plate in a sliding way; the upper end face of the fixed plate is provided with a damping sleeve with an opening at the lower end, and a damping spring and a plug plate are sequentially clamped in the damping sleeve from top to bottom; the upper end surface of the movable plate is provided with a push rod which penetrates through the fixed plate and can be abutted with the plug plate; the upper end surface of the moving plate is provided with a lifting rack penetrating through the through hole; a driving gear meshed with the lifting rack is arranged on the output shaft of the driving motor;
the test model comprises a machine body connected with the lower bottom surface of the movable plate and a machine wheel connected with the lower bottom surface of the machine body through a landing gear;
the course speed simulation assembly comprises a positioning disc arranged at the bottom of the installation cavity, a flywheel arranged on the upper end surface of the positioning disc through a bearing seat and a rotating motor arranged on the bearing seat and used for providing power for the flywheel; the flywheel corresponds to the upper and lower positions of the flywheel, and a three-way load sensor is arranged on the flywheel.
Further, the switching member comprises a first switching plate connected with the driving motor, a second switching plate arranged on the upper end surface of the fixed plate and parallel to the first switching plate, and a switching motor arranged on the upper end surface of the fixed plate through a U-shaped bracket; the toothed plates are arranged on the sides, close to the first switching plate and the second switching plate, of the first switching plate and the second switching plate; the second switching plate is provided with a first electric rod at one end close to the lifting rack, and a positioning sleeve capable of being in sliding clamping connection with the first electric rod is arranged on the side wall of the lifting rack; the U-shaped bracket is positioned outside the first switching plate and the second switching plate, and guide posts which are in one-to-one corresponding sliding clamping connection with the first switching plate and the second switching plate are arranged on two sides of the inside of the U-shaped bracket; the output shaft of the switching motor penetrates through the U-shaped bracket, and switching gears in one-to-one meshed connection with toothed plates on the first switching plate and the second switching plate are arranged on the output shaft;
description: when the electric lifting rack is used, the switching motor is utilized to drive the switching gear to rotate, so that the first switching plate and the second switching plate move in opposite directions, and in the moving process of the first switching plate, the driving motor is pulled to move, so that the driving gear is separated from the lifting rack, and at the moment, the second switching plate is close to the lifting rack, and the first electric rod is inserted into the positioning sleeve on the lifting rack; when the lifting rack needs to be released, the first electric rod is contracted and separated from the positioning sleeve.
Further, the number of the machine wheels is 3, and the 3 machine wheels are distributed on the lower bottom surface of the machine body in an isosceles triangle shape;
the heading speed simulation components are provided with 3 heading speed simulation components, and the 3 heading speed simulation components are in one-to-one correspondence with the upper and lower positions of the 3 wheels;
the lower bottom surface of the positioning disk is rotationally clamped with an adjusting disk, a chute is penetrated through the positioning disk, and two cross rods which are respectively and fixedly connected with the inner walls of the mounting cavity in a one-to-one correspondence manner are slidably clamped in the chute; the adjusting disc is connected with a movable frame in a sliding clamping manner, and a plurality of limiting holes are distributed on the movable frame at equal intervals; an adjusting sleeve which is in sliding clamping connection with the movable frame is sleeved in the mounting cavity; a limiting pin for clamping the adjusting disc is movably inserted into the limiting hole, and a bolt for clamping the movable frame is arranged on the adjusting sleeve;
description: the adjusting disk and the moving frame are rotated on the adjusting sleeve, the adjusting disk slides on the moving frame, and the positioning disk can only move in the front, back, left and right directions and cannot rotate at the moment due to the sliding clamping connection of the positioning disk and the cross rod, and finally the adjusting disk and the moving frame are clamped and fixed by utilizing the limiting pin, and the moving frame and the adjusting sleeve are clamped and fixed by utilizing the bolt, so that the position adjustment of the flywheel is realized, the system provided by the invention can simulate the heading speeds of different types of aircrafts, and the application range of the system is enlarged.
Further, the two ends of the movable frame are rotationally clamped with ball heads which are abutted with the inner wall of the adjusting sleeve;
description: the ball head is arranged at the end part of the movable frame, so that the smoothness of the movable frame in the process of rotating the adjusting sleeve is improved, and the convenience in flywheel position adjustment is improved.
Further, buffer grooves are formed in the ground and are connected with the front side and the rear side of the bottom end of the support frame, buffer rods which are in one-to-one corresponding sliding clamping connection with the support frame are arranged in the two buffer grooves, and buffer springs which are in butt joint with the support frame are sleeved at two ends of each buffer rod;
description: the flywheel has a certain course speed after contacting the rotating flywheel, and impact force is generated on the support frame; at the moment, the vibration of the supporting frame caused by impact can be relieved by utilizing the damping springs, and the stability of the system is improved.
Further, the upper end face of the machine body is provided with an offset seat which is in sliding clamping connection with the lower bottom face of the moving plate; the lower bottom surface of the moving plate is provided with a second electric rod connected with the offset seat; the sliding direction of the offset seat is vertical to the length direction of the machine body;
description: when the flywheel is contacted with the flywheel, the second electric rod is utilized to push the offset seat and the flywheel to move for a set distance, so that the system can perform a yaw and drop test of the aircraft, the functions are more comprehensive, and the cost of the aircraft test is reduced.
Further, an annular aluminum sleeve is sleeved on the flywheel, and a diamond grid is arranged on the surface of the annular aluminum sleeve; two sides of the flywheel are movably connected with clamping discs which are abutted with the annular aluminum sleeve through bolts;
description: the annular aluminum sleeve is arranged, so that the state of the aircraft when sailing on the runways with different roughness can be conveniently simulated; the annular aluminum sleeve is clamped and fixed by the clamping disc, so that the connection stability between the annular aluminum sleeve and the flywheel can be improved, and different annular aluminum sleeves can be replaced conveniently.
Further, the upper end face of the moving plate is provided with a balancing weight loading rod;
description: through setting up the balancing weight loading pole and being convenient for load the balancing weight to the movable plate up end, the balancing weight has avoided the movable plate whereabouts time balancing weight and movable plate to break away from and influence the running stability of system.
Further, 4 sliding rods are arranged, and the 4 sliding rods are arranged on two sides of the inside of the support frame in pairs;
the damping sleeves are arranged in number, and the 4 damping sleeves are arranged on two sides of the upper end surface of the fixed plate in pairs; the number of the ejector rods is 4, and the 4 ejector rods are in one-to-one correspondence with the upper and lower positions of the 4 damping sleeves;
description: by arranging 4 sliding rods, 4 damping sleeves and 4 ejector rods, the stability of the moving plate during falling and rebound rising is improved.
The invention also provides a method for measuring the ground load of the whole machine landing impact and simulating the course speed, which is based on the system for measuring the ground load of the whole machine landing impact and simulating the course speed, and comprises the following steps:
s1, connecting an external device:
the driving motor, the switching component and the rotating motor are respectively connected with an external power supply, and the three-way load sensor is connected with external data acquisition equipment;
s2, lifting a test model:
according to the test requirement, loading a balancing weight on the upper end surface of the movable plate to enable the total mass of the movable plate and the test model to be matched with the real carrier-borne aircraft; starting a driving motor, driving a driving gear to rotate by using the driving motor, enabling a moving plate to drive a test model to slide and rise along a sliding rod by using the meshing effect of the driving gear and a lifting rack, enabling an ejector rod to be abutted with a plug plate in a damping sleeve in the rising process of the moving plate, and compressing a damping spring;
s3, starting a test:
starting a rotating motor, driving a flywheel to rotate to a set rotating speed by using the rotating motor, and then pulling a driving motor by using a switching member to separate a driving gear from a lifting rack; the ejector rod pushes the movable plate and the test model to rapidly slide and descend along the sliding rod under the action of the elasticity of the damping spring, and after the flywheel is impacted by the machine wheel, the machine body drives the movable plate to slide upwards along the sliding rod under the action of the lifting-simulating force;
s4, collecting data:
and sensing impact load when the flywheel is impacted by the flywheel by using the three-way load sensor, and transmitting signals to external data acquisition equipment for data acquisition.
Compared with the prior art, the invention has the beneficial effects that:
the system has reasonable structural design, integrates the course speed simulation of the aircraft wheel and the ground load test into one set of system, has the advantages of high system integration level, stability and reliability, and provides a reliable test environment for the research of the landing gear of the carrier-based aircraft;
secondly, the flywheel of the invention is adjustable in position, so that the system of the invention can simulate the course speeds of different types of aircrafts, measure the impact loads of the different types of aircrafts on the ground, and enlarge the application range of the system; meanwhile, the annular aluminum sleeve on the flywheel is convenient to replace, so that the system can simulate take-off runways with different roughness;
the system of the invention utilizes the elasticity of the damping spring to enable the test model to obtain certain acceleration when falling, thereby overcoming the technical defect that the free falling body of the airplane can not simulate the high impulsive force when the airplane descends from high altitude in the traditional airplane test process, and the test result is not representative.
Drawings
FIG. 1 is a flow chart of the method of embodiment 2 of the present invention;
FIG. 2 is a longitudinal cross-sectional view of the system architecture of the present invention;
FIG. 3 is a graphical representation of the above ground profile of the heading speed simulation assembly of the present invention;
FIG. 4 is a schematic diagram of the connection of the offset base and the movable plate according to the present invention;
FIG. 5 is a schematic diagram showing the connection of the mobile plate and the support frame according to the present invention;
FIG. 6 is a schematic illustration of the connection of the switching member to the fixed plate of the present invention;
FIG. 7 is a schematic illustration of the connection of the U-shaped bracket to the fixed plate of the present invention;
FIG. 8 is a schematic illustration of the connection of the flywheel to the puck of the present invention;
FIG. 9 is a schematic illustration of the attachment of the conditioner disk to the puck of the present invention;
FIG. 10 is a schematic illustration of the connection of the moving frame to the adjustment plate of the present invention;
the device comprises a 1-supporting frame, a 10-mounting cavity, a 11-buffer groove, a 12-buffer rod, a 120-buffer spring, a 2-accelerating falling component, a 20-fixed plate, a 200-through hole, a 21-moving plate, a 210-sliding rod, a 211-balancing weight loading rod, a 22-driving motor, a 220-driving gear, a 23-damping sleeve, a 230-plug plate, a 231-damping spring, a 24-ejector rod, a 25-lifting rack, a 250-positioning sleeve, a 26-switching member, a 260-first switching plate, a 261-second switching plate, a 262-U-shaped bracket, a 263-switching motor, a 2630-switching gear, a 264-toothed plate, a 265-first electric rod, a 266-guiding column, a 3-test model, a 30-body, a 31-landing gear, a 32-machine wheel, a 33-offset seat, a 34-second electric rod, a 4-heading speed simulation component, a 40-positioning disc, a 400-sliding groove, a 401-cross rod, a 41-flywheel, a 410-bearing seat, a 411-clamping disc, a 42-rotating motor, a 43-ring-shaped aluminum sleeve, a 44-moving frame, a 45-adjusting disc, a 45-46-adjusting disc and a 450-adjusting disc.
Detailed Description
Example 1: the system for measuring the ground load and simulating the course speed of the full-machine landing impact as shown in FIG. 2 comprises a support frame 1 arranged on the ground, an accelerating and falling component 2 arranged above the inside of the support frame 1, a test model 3 arranged on the lower bottom surface of the accelerating and falling component 2, and a course speed simulation component 4 arranged below the ground and positioned inside the support frame 1; the ground is provided with a mounting cavity 10 for mounting the heading speed simulation assembly 4;
as shown in fig. 2 and 6, the accelerated dropping component 2 comprises a fixed plate 20 arranged above the inside of the support frame 1, a movable plate 21 which is slidably clamped inside the support frame 1 by a sliding rod 210 and is positioned below the fixed plate 20, and a driving motor 22 which is slidably clamped on the upper end surface of the fixed plate 20; the upper end surface of the fixed plate 20 is provided with a through hole 200 at a position corresponding to the driving motor 22, the upper end surface of the fixed plate 20 is provided with a switching member 26 for driving the driving motor 22 to move, the upper end surface of the fixed plate 20 is provided with a damping sleeve 23 with an opening at the lower end, and a damping spring 231 and a plug plate 230 are sequentially clamped inside the damping sleeve 23 from top to bottom; the upper end surface of the movable plate 21 is provided with a push rod 24 penetrating the fixed plate 20 and capable of abutting against the plug plate 230; the upper end surface of the moving plate 21 is provided with a lifting rack 25 penetrating through the through hole 200; a driving gear 220 in meshed connection with the lifting rack 25 is arranged on the output shaft of the driving motor 22; the switching member 26 is a commercially available product;
as shown in fig. 2, the test model 3 includes a body 30 connected to the lower bottom surface of the moving plate 21 and wheels 32 connected to the lower bottom surface of the body 30 through landing gear 31; the number of the machine wheels 32 is 3, and the 3 machine wheels 32 are distributed on the lower bottom surface of the machine body 30 in an isosceles triangle shape;
as shown in fig. 2, 3 and 8, the heading speed simulation components 4 are provided with 3, and the 3 heading speed simulation components 4 are in one-to-one correspondence with the up-down positions of the 3 wheels 32; the heading speed simulation assembly 4 comprises a positioning disk 40 arranged at the inner bottom of the installation cavity 10, a flywheel 41 arranged on the upper end surface of the positioning disk 40 through a bearing seat 410 and a rotating motor 42 arranged on the bearing seat 410 and used for providing power for the flywheel 41; three-way load sensors are provided on each flywheel 41.
Example 2: this embodiment describes a method for performing machine landing impact ground load measurement and heading speed simulation by using the system of embodiment 1, as shown in fig. 1, comprising the following steps:
s1, connecting an external device:
connecting the driving motor 22, the switching member 26 and the rotating motor 42 with an external power source, respectively, and connecting the three-way load sensor with an external data acquisition device;
s2, lifting a test model 3:
according to the test requirement, loading a balancing weight on the upper end surface of the movable plate 21 to enable the total mass of the movable plate 21 and the test model 3 to be matched with the real carrier-borne aircraft; starting a driving motor 22, driving a driving gear 220 to rotate by using the driving motor 22, enabling a moving plate 21 to drive a test model 3 to slide and ascend along a sliding rod 210 by using the meshing effect of the driving gear 220 and a lifting rack 25, and enabling a push rod 24 to abut against a plug plate 230 in a damping sleeve 23 and compress a damping spring 231 in the ascending process of the moving plate 21;
s3, starting a test:
turning on the rotary motor 42, driving the flywheel 41 to rotate to a set rotation speed by using the rotary motor 42, and then pulling the driving motor 22 by using the switching member 26 to disengage the driving gear 220 from the lifting rack 25; the ejector rod 24 pushes the moving plate 21 and the test model 3 to rapidly slide and descend along the sliding rod 210 under the action of the elastic force of the damping spring 231, and after the flywheel 32 impacts the flywheel 41, the machine body 30 drives the moving plate 21 to slide upwards along the sliding rod 210 under the action of the lifting-simulating force;
s4, collecting data:
the impact load when the flywheel 32 strikes the flywheel 41 is sensed by the three-way load sensor and the signal is transmitted to an external data acquisition device for data acquisition.
Example 3: this embodiment differs from embodiment 1 in that:
as shown in fig. 6 and 7, the switching member 26 includes a first switching plate 260 connected to the driving motor 22, a second switching plate 261 disposed on the upper end surface of the fixed plate 20 and disposed in parallel with the first switching plate 260, and a switching motor 263 disposed on the upper end surface of the fixed plate 20 through a U-shaped bracket 262; the toothed plates 264 are arranged on the sides of the first switching plate 260 and the second switching plate 261, which are close to each other; a first electric rod 265 is arranged at one end of the second switching plate 261, which is close to the lifting rack 25, and a positioning sleeve 250 which can be in sliding clamping connection with the first electric rod 265 is arranged on the side wall of the lifting rack 25; the U-shaped bracket 262 is positioned outside the first switching plate 260 and the second switching plate 261, and guide posts 266 which are in one-to-one sliding clamping connection with the first switching plate 260 and the second switching plate 261 are arranged on two sides of the inside of the U-shaped bracket 262; an output shaft of the switch motor 263 penetrates through the U-shaped bracket 262, and a switch gear 2630 in one-to-one meshed connection with toothed plates 264 on the first switch plate 260 and the second switch plate 261 is arranged on the output shaft.
Example 4: this example describes a method for machine landing impact ground load measurement and heading speed simulation using the system of example 3, which differs from example 2 in that:
in step S1, the switch motor 263 and the first electric lever 265 are connected to an external power source, respectively;
after step S2 is completed, the switching motor 263 is utilized to drive the switching gear 2630 to rotate, so that the first switching plate 260 and the second switching plate 261 move in opposite directions, and in the moving process of the first switching plate 260, the driving motor 22 is pulled to move, so that the driving gear 220 is separated from the lifting rack 25, at this time, the second switching plate 261 is close to the lifting rack 25, and the first electric rod 265 is inserted into the positioning sleeve 250 on the lifting rack 25 after being extended;
in step S3, the first electric rod 265 is retracted and then separated from the positioning sleeve 250.
Example 5: this embodiment differs from embodiment 3 in that;
as shown in fig. 8, 9 and 10, an adjusting disc 44 is rotatably clamped on the lower bottom surface of the positioning disc 40, a chute 400 is arranged on the positioning disc 40 in a penetrating manner, and two cross bars 401 which are respectively and fixedly connected with the inner walls of the mounting cavity 10 in a one-to-one correspondence manner are slidably clamped in the chute 400; the adjusting disc 44 is slidably clamped with a movable frame 45, and a plurality of limiting holes 450 are distributed on the movable frame 45 at equal intervals; an adjusting sleeve 46 which is in sliding clamping connection with the movable frame 45 is sleeved in the mounting cavity 10; a limiting pin for clamping the adjusting disc 44 is movably inserted into the limiting hole 450, and a bolt for clamping the movable frame 45 is arranged on the adjusting sleeve 46; both ends of the movable frame 45 are rotatably clamped with ball heads 451 which are abutted against the inner wall of the adjusting sleeve 46; the flywheel 41 is sleeved with an annular aluminum sleeve 43, and the surface of the annular aluminum sleeve 43 is provided with diamond grids; the two sides of the flywheel 41 are movably connected with clamping discs 411 which are abutted with the annular aluminum sleeve 43 through bolts.
Example 6: this example describes a method for machine landing impact ground load measurement and heading speed simulation using the system of example 5, which differs from example 4 in that:
after step S4 is completed, the adjusting disc 44 and the moving frame 45 rotate on the adjusting sleeve 46, and the adjusting disc 44 slides on the moving frame 45, and since the positioning disc 40 is clamped with the cross bar 401 in a sliding manner, the positioning disc 40 can only move in four directions, namely front, back, left and right, but not rotate, and finally the adjusting disc 44 and the moving frame 45 are clamped and fixed by using the limiting pins, the moving frame 45 and the adjusting sleeve 46 are clamped and fixed by using the bolts, and the positions of the flywheels 41 are adjusted; then, the annular aluminum sleeves 43 with different roughness were replaced, and the next model test was performed.
Example 7: this embodiment differs from embodiment 5 in that:
as shown in fig. 2 and 3, buffer grooves 11 are formed in the ground and in the connection with the front side and the rear side of the bottom end of the support frame 1, buffer rods 12 in sliding clamping connection with the support frame 1 in one-to-one correspondence are arranged in the two buffer grooves 11, and buffer springs 120 in butt joint with the support frame 1 are sleeved at two ends of each buffer rod 12.
Example 8: this example describes a method for machine landing impact ground load measurement and heading speed simulation using the system of example 7, which differs from example 6 in that:
in step S3, when the flywheel 32 contacts the rotating flywheel 41 and has a certain heading speed, an impact force is generated on the support frame 1, and the vibration of the support frame 1 caused by the impact is relieved by the damping spring 120.
Example 9: this embodiment differs from embodiment 7 in that:
as shown in fig. 2 and 4, the upper end surface of the body 30 is provided with an offset seat 33 which is slidably engaged with the lower bottom surface of the moving plate 21; the lower bottom surface of the movable plate 21 is provided with a second electric rod 34 connected with the offset seat 33; the sliding direction of the offset seat 33 is perpendicular to the longitudinal direction of the body 30.
Example 10: this example describes a method for machine landing impact ground load measurement and heading speed simulation using the system of example 9, which differs from example 8 in that:
in step S1, the second electric lever 34 is connected to an external power source;
in step S3, when the flywheel 41 is contacted by the wheel 32, the second electric lever 34 is used to push the offset seat 33 and the wheel 32 to move a set distance, and a yaw and shock test of the aircraft is performed.
Example 11: this embodiment differs from embodiment 9 in that:
as shown in fig. 5, the upper end surface of the moving plate 21 is provided with a weight loading lever 211; the number of the sliding rods 210 is 4, and the 4 sliding rods 210 are arranged on two sides of the inside of the support frame 1; the damping sleeves 23 are arranged in number, and the 4 damping sleeves 23 are arranged on two sides of the upper end face of the fixed plate 20; the number of the ejector rods 24 is 4, and the 4 ejector rods 24 are in one-to-one correspondence with the upper and lower positions of the 4 damping sleeves 23;
example 12: this example describes a method for machine landing impact ground load measurement and heading speed simulation using the system of example 11, which differs from example 10 in that:
in step S2, the weight is inserted into the weight loading lever 211 on the upper end surface of the moving plate 21.
The driving motor 22, the switching motor 263, the first electric rod 265, the second electric rod 34, the rotary motor 42, and the three-way load sensor used in the present invention are all related art, and are not particularly limited herein, and corresponding products may be selected according to actual needs.
Claims (9)
1. The system is characterized by comprising a support frame (1) arranged on the ground, an accelerating and falling component (2) arranged above the inside of the support frame (1), a test model (3) arranged on the lower bottom surface of the accelerating and falling component (2) and a course speed simulation component (4) arranged below the ground and positioned inside the support frame (1); the ground is provided with a mounting cavity (10) for mounting the heading speed simulation assembly (4);
the accelerating and falling assembly (2) comprises a fixed plate (20) arranged above the inside of the support frame (1), a movable plate (21) which is slidably clamped inside the support frame (1) through a sliding rod (210) and is positioned below the fixed plate (20), and a driving motor (22) which is slidably clamped on the upper end face of the fixed plate (20); the damping device is characterized in that a through hole (200) is formed in the upper end face of the fixed plate (20) and corresponds to the position of the driving motor (22), a switching member (26) for driving the driving motor (22) to move is arranged on the upper end face of the fixed plate (20), a damping sleeve (23) with an opening at the lower end is arranged on the upper end face of the fixed plate (20), and a damping spring (231) and a plug plate (230) are sequentially clamped inside the damping sleeve (23) from top to bottom; an ejector rod (24) penetrating through the fixed plate (20) and being capable of being abutted against the plug plate (230) is arranged on the upper end surface of the movable plate (21); a lifting rack (25) penetrating through the through hole (200) is arranged on the upper end surface of the moving plate (21); a driving gear (220) which is in meshed connection with the lifting rack (25) is arranged on an output shaft of the driving motor (22);
the test model (3) comprises a machine body (30) connected with the lower bottom surface of the movable plate (21) and a machine wheel (32) connected with the lower bottom surface of the machine body (30) through a landing gear (31);
the course speed simulation assembly (4) comprises a positioning disc (40) arranged at the inner bottom of the installation cavity (10), a flywheel (41) arranged on the upper end surface of the positioning disc (40) through a bearing seat (410) and a rotating motor (42) arranged on the bearing seat (410) and used for providing power for the flywheel (41); the flywheel (41) corresponds to the upper and lower positions of the flywheel (32); the flywheel (41) is provided with a three-way load sensor;
the switching member (26) comprises a first switching plate (260) connected with the driving motor (22), a second switching plate (261) arranged on the upper end surface of the fixed plate (20) and parallel to the first switching plate (260), and a switching motor (263) arranged on the upper end surface of the fixed plate (20) through a U-shaped bracket (262); a toothed plate (264) is arranged on one side, close to the first switching plate (260) and the second switching plate (261); a first electric rod (265) is arranged at one end, close to the lifting rack (25), of the second switching plate (261), and a positioning sleeve (250) capable of being in sliding clamping connection with the first electric rod (265) is arranged on the side wall of the lifting rack (25); the U-shaped support (262) is positioned outside the first switching plate (260) and the second switching plate (261), and guide posts (266) which are in one-to-one corresponding sliding clamping connection with the first switching plate (260) and the second switching plate (261) are arranged on two sides of the inside of the U-shaped support (262); an output shaft of the switching motor (263) penetrates through the U-shaped bracket (262) and is provided with switching gears (2630) which are in one-to-one meshed connection with toothed plates (264) on the first switching plate (260) and the second switching plate (261).
2. The full-aircraft landing impact ground load measurement and heading speed simulation system according to claim 1, wherein 3 wheels (32) are arranged, and the 3 wheels (32) are distributed in an isosceles triangle on the lower bottom surface of the machine body (30);
the heading speed simulation components (4) are provided with 3, and the 3 heading speed simulation components (4) are in one-to-one correspondence with the upper and lower positions of the 3 wheels (32);
the lower bottom surface of the positioning disc (40) is rotationally clamped with an adjusting disc (44), a chute (400) is arranged on the positioning disc (40) in a penetrating manner, and two cross bars (401) which are respectively and fixedly connected with the inner walls of the mounting cavity (10) in a one-to-one correspondence manner are slidably clamped in the chute (400); a movable frame (45) is connected to the adjusting disc (44) in a sliding clamping manner, and a plurality of limiting holes (450) are distributed on the movable frame (45) at equal intervals; an adjusting sleeve (46) which is in sliding clamping connection with the movable frame (45) is sleeved in the mounting cavity (10); limiting pins for clamping the adjusting disc (44) are movably inserted into the limiting holes (450), and bolts for clamping the movable frame (45) are arranged on the adjusting sleeve (46).
3. The system for measuring the ground load and simulating the heading speed of the full-machine landing impact according to claim 2, wherein the two ends of the movable frame (45) are rotatably clamped with a ball head (451) which is abutted against the inner wall of the adjusting sleeve (46).
4. The full-machine landing impact ground load measurement and course speed simulation system according to claim 1, wherein buffer grooves (11) are formed in the ground and at the joints of the ground and the front side and the rear side of the bottom end of the support frame (1), buffer rods (12) which are in one-to-one corresponding sliding clamping connection with the support frame (1) are arranged in the buffer grooves (11), and buffer springs (120) which are in butt joint with the support frame (1) are sleeved at two ends of each buffer rod (12).
5. The full-aircraft landing impact ground load measurement and heading speed simulation system according to claim 1, wherein an offset seat (33) which is in sliding clamping connection with the lower bottom surface of the moving plate (21) is arranged on the upper end surface of the machine body (30); the lower bottom surface of the moving plate (21) is provided with a second electric rod (34) connected with the offset seat (33); the sliding direction of the offset seat (33) is perpendicular to the length direction of the machine body (30).
6. The full-machine landing impact ground load measurement and heading speed simulation system according to claim 1, wherein an annular aluminum sleeve (43) is sleeved on the flywheel (41), and a diamond grid is arranged on the surface of the annular aluminum sleeve (43); two sides of the flywheel (41) are movably connected with clamping discs (411) which are abutted with the annular aluminum sleeve (43) through bolts.
7. The full-machine landing impact ground load measurement and heading speed simulation system according to claim 1, wherein a counterweight loading rod (211) is arranged on the upper end surface of the moving plate (21).
8. The full-machine landing impact ground load measurement and heading speed simulation system according to claim 1, wherein 4 sliding rods (210) are arranged, and the 4 sliding rods (210) are arranged on two sides of the inside of the support frame (1);
the damping sleeves (23) are arranged in number, and the 4 damping sleeves (23) are arranged on two sides of the upper end face of the fixed plate (20) in pairs; the number of the ejector rods (24) is 4, and the 4 ejector rods (24) are in one-to-one correspondence with the upper and lower positions of the 4 damping sleeves (23).
9. The method for measuring the ground load of the whole machine landing impact and simulating the heading speed is based on the system for measuring the ground load of the whole machine landing impact and simulating the heading speed according to any one of claims 1 to 8, and is characterized by comprising the following steps:
s1, connecting an external device:
connecting the driving motor (22), the switching member (26) and the rotating motor (42) with an external power supply respectively, and connecting the three-way load sensor with external data acquisition equipment;
s2, lifting a test model (3):
according to the test requirement, loading a balancing weight on the upper end surface of the movable plate (21) to enable the total mass of the movable plate (21) and the test model (3) to be matched with the real carrier-borne aircraft; starting a driving motor (22), driving a driving gear (220) to rotate by using the driving motor (22), enabling a moving plate (21) to drive a test model (3) to slide and ascend along a sliding rod (210) by using the meshing effect of the driving gear (220) and a lifting rack (25), enabling a push rod (24) to be abutted with a plug plate (230) in a damping sleeve (23) and compressing a damping spring (231) in the ascending process of the moving plate (21);
s3, starting a test:
starting a rotating motor (42), driving a flywheel (41) to rotate to a set rotating speed by using the rotating motor (42), and then pulling a driving motor (22) by using a switching member (26) to separate a driving gear (220) from a lifting rack (25); the ejector rod (24) pushes the movable plate (21) and the test model (3) to rapidly slide down along the sliding rod (210) under the action of the elastic force of the damping spring (231), and after the flywheel (41) is impacted by the machine wheel (32), the machine body (30) drives the movable plate (21) to slide upwards along the sliding rod (210) under the action of the imitation lifting force;
s4, collecting data:
the three-way load sensor is used for sensing the impact load when the flywheel (32) impacts the flywheel (41), and transmitting signals to the external data acquisition equipment for data acquisition.
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Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN102854129A (en) * | 2012-08-06 | 2013-01-02 | 中国民航科学技术研究院 | Verification testing experiment device and experiment method for aircraft arresting systems |
| CN105138805A (en) * | 2015-09-29 | 2015-12-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Load simulation method for cataplane landing gear |
| CN105157973A (en) * | 2015-11-06 | 2015-12-16 | 南京航空航天大学 | Arresting hook dynamic fatigue testing device and testing method |
| CN110243564A (en) * | 2019-06-12 | 2019-09-17 | 南京航空航天大学 | Arrester hook hanging cable shock loading test and experiment device and test method |
| CN111169653A (en) * | 2019-12-11 | 2020-05-19 | 中国飞机强度研究所 | Hinge point force testing device of nose landing gear and load calibration method |
| KR20200101707A (en) * | 2019-02-20 | 2020-08-28 | 경상대학교산학협력단 | Combined Aircraft and Ship Simulation Training Control Device |
| CN112733277A (en) * | 2021-03-30 | 2021-04-30 | 江苏普旭科技股份有限公司 | Simulation method and system for simulation of aircraft landing gear |
| CN112924126A (en) * | 2021-01-20 | 2021-06-08 | 南京航空航天大学 | Aircraft tire landing impact test device and test method thereof |
| CN113340573A (en) * | 2021-01-29 | 2021-09-03 | 西安航空制动科技有限公司 | Sidesway loading rolling device and test method for aircraft wheel fatigue test bed |
| CN215573665U (en) * | 2021-05-18 | 2022-01-18 | 浙江鸿鹄翼航空科技有限公司 | Small landing gear drop test bed |
| CN114379817A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Shipboard aircraft nose landing gear catapulting and protruding test device and test method |
| CN114572421A (en) * | 2022-03-14 | 2022-06-03 | 中国商用飞机有限责任公司 | Drop test device, drop test system and drop test method |
| CN115824550A (en) * | 2022-11-25 | 2023-03-21 | 中航飞机起落架有限责任公司 | Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method |
| CN115924121A (en) * | 2023-01-17 | 2023-04-07 | 哈尔滨工业大学 | Comprehensive loading test device and method for aircraft landing gear system in multi-motion state |
| KR102527736B1 (en) * | 2023-02-10 | 2023-05-03 | 윈다스 주식회사 | Pendulum suspension system with membrane air spring considering the asymmetrical kinematic movement of aircraft landing gear |
| CN116443266A (en) * | 2023-03-29 | 2023-07-18 | 中国飞机强度研究所 | Emergent breaking dynamic test device of undercarriage |
| CN116902221A (en) * | 2023-09-13 | 2023-10-20 | 中国飞机强度研究所 | Aeroplane tire dynamics test device and method under composite working condition |
-
2023
- 2023-10-24 CN CN202311377801.5A patent/CN117109861B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN102854129A (en) * | 2012-08-06 | 2013-01-02 | 中国民航科学技术研究院 | Verification testing experiment device and experiment method for aircraft arresting systems |
| CN105138805A (en) * | 2015-09-29 | 2015-12-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Load simulation method for cataplane landing gear |
| CN105157973A (en) * | 2015-11-06 | 2015-12-16 | 南京航空航天大学 | Arresting hook dynamic fatigue testing device and testing method |
| KR20200101707A (en) * | 2019-02-20 | 2020-08-28 | 경상대학교산학협력단 | Combined Aircraft and Ship Simulation Training Control Device |
| CN110243564A (en) * | 2019-06-12 | 2019-09-17 | 南京航空航天大学 | Arrester hook hanging cable shock loading test and experiment device and test method |
| CN111169653A (en) * | 2019-12-11 | 2020-05-19 | 中国飞机强度研究所 | Hinge point force testing device of nose landing gear and load calibration method |
| CN112924126A (en) * | 2021-01-20 | 2021-06-08 | 南京航空航天大学 | Aircraft tire landing impact test device and test method thereof |
| CN113340573A (en) * | 2021-01-29 | 2021-09-03 | 西安航空制动科技有限公司 | Sidesway loading rolling device and test method for aircraft wheel fatigue test bed |
| CN112733277A (en) * | 2021-03-30 | 2021-04-30 | 江苏普旭科技股份有限公司 | Simulation method and system for simulation of aircraft landing gear |
| CN215573665U (en) * | 2021-05-18 | 2022-01-18 | 浙江鸿鹄翼航空科技有限公司 | Small landing gear drop test bed |
| CN114379817A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Shipboard aircraft nose landing gear catapulting and protruding test device and test method |
| CN114572421A (en) * | 2022-03-14 | 2022-06-03 | 中国商用飞机有限责任公司 | Drop test device, drop test system and drop test method |
| CN115824550A (en) * | 2022-11-25 | 2023-03-21 | 中航飞机起落架有限责任公司 | Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method |
| CN115924121A (en) * | 2023-01-17 | 2023-04-07 | 哈尔滨工业大学 | Comprehensive loading test device and method for aircraft landing gear system in multi-motion state |
| KR102527736B1 (en) * | 2023-02-10 | 2023-05-03 | 윈다스 주식회사 | Pendulum suspension system with membrane air spring considering the asymmetrical kinematic movement of aircraft landing gear |
| CN116443266A (en) * | 2023-03-29 | 2023-07-18 | 中国飞机强度研究所 | Emergent breaking dynamic test device of undercarriage |
| CN116902221A (en) * | 2023-09-13 | 2023-10-20 | 中国飞机强度研究所 | Aeroplane tire dynamics test device and method under composite working condition |
Non-Patent Citations (2)
| Title |
|---|
| 极端环境模拟装置在考虑温度影响的起落架落震性能研究中的应用;张飞 等;《机械科学与技术》;全文 * |
| 舰载机弹射起飞前起落架牵制载荷突卸动力学分析;于浩;聂宏;魏小辉;;航空学报;第32卷(第8期);全文 * |
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