CN117184443A - Device and method for slide obstacle surmounting impact test of landing gear of carrier-based aircraft - Google Patents
Device and method for slide obstacle surmounting impact test of landing gear of carrier-based aircraft Download PDFInfo
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Abstract
The invention discloses a landing gear running obstacle crossing impact test device and a test method of a ship-based aircraft, wherein the test device comprises a foundation provided with a sinking groove, a test bed, a counterweight adjusting mechanism, a lifting release mechanism, a landing gear, a flywheel and a driving mechanism, the counterweight adjusting mechanism comprises a hanging basket and a counterweight block, the landing gear comprises a support column, a supporting rod, a buffer and a machine wheel, hinge point force sensors are arranged at the hinging positions of the hanging basket and the support column and the supporting rod, strain gauges are arranged on the support column and the supporting rod, and a pressure sensor and a displacement sensor are arranged on the buffer; the driving mechanism comprises a fixed plate, a balance plate, a first extension plate, a push rod and a power mechanism; the test method comprises the following steps: s1, preparing before a test; s2, a test process; s3, post-test treatment; the invention simulates the landing gear running obstacle crossing process of the aircraft under the laboratory environment and provides necessary test data support for the performance research and the structural optimization of the landing gear running obstacle crossing process.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a device and a method for a ship-based aircraft landing gear running obstacle surmounting impact test.
Background
When the aircraft takes off and land on the ship, the landing gear can collide with the obstacle on the ship in the running process. The load on the landing gear during a collision includes heading, lateral and vertical loads. In the landing gear running obstacle crossing process, the relation among the course, the coupling effect between the lateral load and the vertical load and the relation between the obstacle crossing load and the buffer performance all need to be researched and evaluated, and the landing gear needs to be optimized based on data obtained through experiments.
At present, no mature device and method for the landing gear running obstacle crossing impact test of an airplane exist at home, and the device and the method for the landing gear running obstacle crossing impact test of the airplane are required to be provided, effective data are obtained through the test, and necessary test support is provided for the landing gear running obstacle crossing performance research and the structural optimization.
Disclosure of Invention
In order to solve the technical problems, the invention provides a device and a method for a landing gear running obstacle surmounting impact test of a ship-borne aircraft.
The technical scheme of the invention is as follows: the landing gear running obstacle crossing impact test device for the ship-based aircraft comprises a foundation provided with a sinking groove, a test bed arranged on the foundation, a balance weight adjusting mechanism arranged in the test bed and connected with the test bed in an up-down sliding manner, a lifting release mechanism connected between the balance weight adjusting mechanism and the test bed, a landing gear fixed at the bottom of the balance weight adjusting mechanism, a flywheel rotationally arranged in the sinking groove and a driving mechanism for driving the flywheel to collide with the landing gear;
the counterweight adjusting mechanism comprises a hanging basket and a counterweight block arranged in the hanging basket;
the landing gear comprises a strut and a stay bar, wherein one end of the strut is hinged with the bottom of the hanging basket, a buffer and a wheel are hinged with the other end of the strut, and the wheel is connected with the buffer in a rotating way; the hinge points of the hanging basket, the support column and the hanging basket are respectively provided with a hinge point force sensor, the support column and the support rod are respectively provided with a plurality of strain gauges for detecting the strain of the landing gear, and the buffer is provided with a pressure sensor for detecting the pressure of the buffer air cavity and a displacement sensor for detecting the stroke of the buffer in the collision process;
a sliding block sliding along the axis direction of the flywheel is arranged on the curved surface of the flywheel, and the sliding block is in sliding connection with a limiting chute arranged on the curved surface of the flywheel;
the driving mechanism comprises a fixed plate fixedly connected with the inner wall of the sinking groove, a balance plate rotationally connected with the fixed plate through a shaft rod, a push rod transversely arranged below the balance plate and vertically penetrating through the fixed plate, and a first extension plate arranged on the fixed plate and fixedly connected with the balance plate through a spring;
one end of the push rod is provided with a push plate, and the fixed plate is provided with a power mechanism for driving the push rod to toggle the sliding block.
Further, the test bed consists of two vertical plates which are arranged on the foundation along the vertical direction and a supporting plate which is horizontally arranged on the top of the two vertical plates; the two opposite side surfaces of the vertical plates are respectively provided with a sliding rail, and the side walls of the two sides of the hanging basket are respectively provided with a roller in sliding connection with the sliding rails.
Description: the sliding connection mode of the roller and the sliding rail has the advantages of simple structure and high sliding smoothness.
Further, the lifting release mechanism comprises a lifting motor arranged on the supporting plate and an electromagnetic release lock connected with the output end of the lifting motor through a lifting steel wire rope, and the electromagnetic release lock is connected with the hanging basket in a matched manner through a movable buckle arranged at the top of the hanging basket.
Description: lifting and releasing of the hanging basket can be achieved through equipment such as a lifting motor, and the lifting and releasing device is simple in structure and stable in motion state.
Further, one end of the flywheel central shaft is connected with a rotating motor arranged on the inner wall of the sink, and the other end of the flywheel central shaft is connected with the inner wall of the sink in a rotating way.
Description: the flywheel is driven to rotate in the sink through the rotating motor, so that the structure is simple, and the rotating state of the flywheel is stable.
Further, the power mechanism comprises a first transmission component arranged on one side of the fixed plate and a second transmission component arranged on the other side of the fixed plate, one end of the balance plate is provided with a notch for the sliding block to pass through, the bottom of one end of the balance plate is provided with a first toothed plate hinged with the balance plate, and the first toothed plate is in sliding connection with a vertical sliding groove arranged on the fixed plate;
the first transmission assembly comprises a central shaft, a rotating wheel and a ratchet wheel, wherein the rotating wheel and the ratchet wheel are fixedly sleeved on the central shaft, the central shaft is rotationally connected with the inner wall of the sinking groove, the rotating wheel is in friction transmission with the push rod, the first transmission assembly and the second transmission assembly are identical in structure, the central shaft of the first transmission assembly is arranged above the push rod, the central shaft of the second transmission assembly is arranged below the push rod, and the first toothed plate is used for driving the second transmission assembly to rotate after the sliding block collides with the balance plate;
the ratchet wheel of the first transmission assembly is meshed with the first toothed plate for transmission;
the other side of the fixed plate is provided with a second toothed plate, one end of the second toothed plate is fixedly connected with a second extension plate arranged on the fixed plate through a spring rod, the second extension plate is in sliding connection with a transverse sliding chute arranged on the other side of the fixed plate, and one side of the second toothed plate facing the flywheel is provided with a first meshing tooth; the flywheel at the rear side of the sliding block in the rotating direction is provided with an arc-shaped rack which is used for driving the second toothed plate to move downwards after the sliding block passes through the balance plate;
the ratchet wheel of the second transmission assembly is used for meshing transmission with the second toothed plate when the second toothed plate moves downwards;
and the fixed plate is provided with a switching mechanism for enabling the second toothed plate to transversely move when the sliding block is reset.
Description: after the surface line speed of the outer edge of the flywheel reaches the standard, the first meshing teeth of the second toothed plate are meshed with the arc-shaped racks on the flywheel for transmission, so that the sliding block can trigger the second transmission assembly to be pushed by the push plate on the push rod after passing through the notch, and the sliding block is pushed to the position right below the flywheel from the side of the flywheel, thereby realizing the position switching of the sliding block; when the collided sliding block impacts the balance plate, the first transmission assembly is triggered to be pushed to the initial position by the push plate on the push rod, so that the sliding block position is automatically switched before and after the collision.
Further, the switching mechanism comprises a rotating shaft, a gear and a driving belt, wherein one end of the rotating shaft is rotatably connected with the fixed plate, the gear is sleeved on the rotating shaft and is close to one end of the fixed plate, the driving belt is sleeved on the rotating shaft, and the shaft rod penetrates through the fixed plate and is sleeved with the driving belt; and the second extension plate is provided with second meshing teeth which are meshed with the gear for transmission.
Description: the transmission belt drives the gear to rotate through the movement of the shaft rod, so that the gear drives the second extension plate to transversely move, and the second toothed plate moves towards the gear to be far away from the flywheel, thereby avoiding interference with the movement of the push rod during resetting.
Further, fixed plate bottom fixedly connected with horizontal plate, be equipped with the liquid bag that is equipped with lubricating oil and the shower nozzle towards the flywheel on the horizontal plate, the liquid bag is located under the second pinion rack, the shower nozzle set up with on the horizontal plate that limit chute position corresponds, just the liquid bag passes through the connecting pipe and communicates with the shower nozzle.
Description: through setting up sac and shower nozzle for when the flywheel that will collide rotates the process in the past, drive the second pinion rack and move down and extrude the sac because of the arc rack, thereby spray the lubricating oil to spacing spout through the shower nozzle, thereby reduce the wearing and tearing of slider, improve the life of slider.
Further, the hinge point force sensor is provided with a controller, and the controller is electrically connected with the hinge point force sensor and the rotating motor.
Description: after the hinge point force sensor senses collision, the rotating motor is decelerated through the controller, so that the speed of the flywheel is automatically slowed down to 0.
The invention also provides a landing gear running obstacle-surmounting impact test method for the carrier-based aircraft, which is based on the landing gear running obstacle-surmounting impact test device for the carrier-based aircraft, and comprises the following steps:
s1, preparation before test:
adjusting the balancing weight on the hanging basket to ensure that the quality of a system formed by the hanging basket and the balancing weight meets the test requirement; then controlling the lifting release mechanism to lift the balance weight adjusting mechanism and the landing gear to the upper part of the flywheel and avoid contact with the flywheel; at this time, the sliding block is positioned at the side of the machine wheel;
s2, a test process:
the lifting release mechanism is controlled to drive the balance weight adjusting mechanism and the landing gear to synchronously descend, the flywheel of the landing gear is pressed onto the flywheel, and then the lifting release mechanism is separated from the hanging basket, so that the electromagnetic release lock moves upwards to reset;
starting the flywheel to rotate in a reverse course, and enabling the surface line speed of the outer edge of the flywheel to reach 240km/h within 3s, wherein after the surface line speed of the outer edge reaches the standard, the sliding block passes through the balance plate, the power mechanism drives the push rod and the push plate to slide in a direction away from the fixed plate, and the sliding block is stirred to the position right below the flywheel from the side of the flywheel, so that the sliding block collides with the flywheel in the rotation process along with the flywheel;
the sliding block passes through the balance plate after colliding with the machine wheel, and the power mechanism drives the push rod and the push plate to slide in the direction close to the fixed plate, so that the sliding block is shifted to the side of the machine wheel from the right lower part of the machine wheel;
controlling the surface line speed of the outer edge of the flywheel to be slowed down to 0, and completing a single running obstacle surmounting impact test of the undercarriage;
s3, test post-treatment:
after the single running obstacle surmounting impact test of the landing gear is completed, obtaining the travel data of the buffer collected by the displacement sensorsStrain data of landing gear collected by strain gaugeεAir cavity pressure data of buffer collected by pressure sensorPAnd a time course corresponding to each datat，
Obtained from a single testεAnd calculating the impact load to which the landing gear is subjected by using the formula (1):
F=εEA （1）
wherein,Fis the impact load applied to the landing gear, and has the unit of kN;εthe strain data of the landing gear collected for the strain gauge,Eis the elastic modulus of the landing gear material, the unit is GPa,Athe section area of the strut or stay bar positioned at the attaching position of one strain gauge is in mm;
according toObtained by a single tests、F、PAnd correspondingtDrawing outs-tGraph chart(s),F-tGraph diagramP-tA graph;
and then the weight of the weight adjusting mechanism is adjusted, and the weight adjusting mechanism and the landing gear are moved upwards and reset through the lifting release mechanism, so that the next test is prepared.
The beneficial effects of the invention are as follows:
(1) The invention provides a carrier-based aircraft running obstacle crossing test device and a test method, which can simulate the landing gear running obstacle crossing process in a laboratory, provide a verification way for checking the carrier-based aircraft running obstacle crossing performance, and reduce the technical risk of real aircraft landing adaptation test flight verification;
(2) According to the test device, the driving mechanism is arranged, so that the power mechanism in the driving mechanism converts rotation into translation, the sliding block is driven to shift, the position of the sliding block can be switched before and after the flywheel speed reaches the standard, the position of the sliding block can be timely adjusted before and after collision with the flywheel, and the next test can be prevented from being influenced while a single test is completed.
Drawings
FIG. 1 is an overall external view of a test apparatus according to example 1 of the present invention;
FIG. 2 is a plan view of a sink in the test apparatus of example 1 of the present invention;
FIG. 3 is a schematic view showing the internal structure of the front surface of the sink in the test apparatus according to example 1 of the present invention;
FIG. 4 is an enlarged schematic view of FIG. 3 at I;
FIG. 5 is a view showing the internal structure of the back surface of the sink of the test device according to example 1 of the present invention;
FIG. 6 is a view showing the construction of a fixing plate of the test device according to embodiment 1 of the present invention;
FIG. 7 is a view showing the construction of a fixing plate of the test device according to embodiment 3 of the present invention;
FIG. 8 is a graph of the test examples of the present invention according to Table 1F-tA graph;
FIG. 9 is a graph of the test examples of the present invention according to Table 1s-tA graph;
FIG. 10 is a graph of the test examples of the present invention according to Table 1P-tA graph;
FIG. 11 is a flow chart of the test method of example 2 of the present invention;
the device comprises a foundation 1-part, a supporting plate 11-part, a vertical plate 12-part, a lifting motor 13-part, a lifting wire rope 14-part, an electromagnetic release lock 15-part, a landing gear 2-part, a hanging basket 21-part, a roller 211-part, a balancing weight 212-part, a hinge point force sensor 22-part, a hinge point force sensor 23-part, a buffer 231-part, a strut 232-part, a strut 233-part, a supporting plate 3-part, a sliding block 31-part, an arc-shaped rack 32-part, a rotating motor 33-part, a fixed plate 4-part, a balancing plate 41-part, a spring 411-part, a shaft rod 412-part, a driving belt 413-part, a gear 414-part, a rotating shaft 415-part, a push rod 42-part, a push plate 421-part, a first extension plate 43-part, a ratchet wheel 44-part, a rotating wheel 441-part, a first toothed plate 46-part, a second toothed plate 461-first-part, a second extension plate 462-part, a second toothed part 463-part, a spring rod 464-part 47-part, a liquid bag 471-part, a nozzle 472-part, and a horizontal plate 48-part.
Detailed Description
The invention will be described in further detail with reference to the following embodiments to better embody the advantages of the invention.
Example 1: the landing gear running obstacle crossing impact test device for the ship-borne aircraft comprises a foundation 1 provided with a sinking groove, a test bench arranged on the foundation 1, a counterweight adjusting mechanism arranged in the test bench and connected with the test bench in an up-down sliding manner, a lifting release mechanism connected between the counterweight adjusting mechanism and the test bench, a landing gear 2 fixed at the bottom of the counterweight adjusting mechanism, a flywheel 3 rotatably arranged in the sinking groove and a driving mechanism for driving the flywheel 3 to collide with the landing gear 2, wherein the lifting release mechanism is arranged between the counterweight adjusting mechanism and the test bench;
as shown in fig. 2, one end of the central shaft of the flywheel 3 is connected with a rotating motor 33 arranged on the inner wall of the sink, and the other end of the central shaft of the flywheel 3 is connected with the inner wall of the sink in a rotating way;
as shown in fig. 1, the test stand is composed of two vertical plates 12 installed on a foundation 1 in a vertical direction and a support plate 11 horizontally installed on top of the two vertical plates 12;
as shown in fig. 1, the weight adjusting mechanism includes a basket 21 and a weight 212 provided in the basket 21; the opposite side surfaces of the two vertical plates 12 are respectively provided with a sliding rail, and the side walls of the two sides of the hanging basket 21 are respectively provided with a roller 211 which is in sliding connection with the sliding rails;
as shown in fig. 1, the lifting release mechanism comprises a lifting motor 13 arranged on a supporting plate 11 and an electromagnetic release lock 15 connected with the output end of the lifting motor 13 through a lifting steel wire rope 14, wherein the electromagnetic release lock 15 is in matched connection with a hanging basket 21 through a movable buckle arranged at the top of the hanging basket 21;
as shown in fig. 1, the landing gear 2 comprises a strut 232 and a strut 233, one end of which is respectively hinged with the bottom of the hanging basket 21, a buffer 231 hinged with the other end of the strut 232, and a wheel 23 rotatably connected with the buffer 231, wherein the other end of the strut 233 is hinged with the middle part of the strut 232; hinge point force sensors 22 are arranged at the hinge positions of the hanging basket 21 and the support column 232 and the hinge positions of the hanging basket 21 and the support rod 233, 50 strain gauges for detecting the strain of the landing gear 2 are arranged on the support column 232 and the support rod 233, and a pressure sensor for detecting the pressure of an air cavity of the buffer 231 and a displacement sensor for detecting the stroke of the buffer 231 in the collision process are arranged on the buffer 231;
as shown in fig. 1 and 2, a sliding block 31 sliding along the axis direction of the flywheel 3 is arranged on the curved surface of the flywheel 3, and the sliding block 31 is in sliding connection with a limit chute arranged on the curved surface of the flywheel 3;
as shown in fig. 3, 5 and 6, the driving mechanism comprises a fixed plate 4 fixedly connected with the inner wall of the sink, a balance plate 41 rotatably connected with the fixed plate 4 through a shaft lever 412, a push rod 42 transversely arranged below the balance plate 41 and vertically penetrating through the fixed plate 4, and a first extension plate 43 arranged on the fixed plate 4 and fixedly connected with the balance plate 41 through a spring 411;
as shown in fig. 5 and 6, a push plate 421 is disposed at one end of the push rod 42, and a power mechanism for driving the push rod 42 to toggle the slider 31 is disposed on the fixed plate 4;
as shown in fig. 3 and 6, the power mechanism comprises a first transmission assembly arranged on one side of the fixed plate 4 and a second transmission assembly arranged on the other side of the fixed plate 4, one end of the balance plate 41 is provided with a notch for the sliding block 31 to pass through, the bottom of one end of the balance plate 41 is provided with a first toothed plate 45 hinged with the balance plate, and the first toothed plate 45 is in sliding connection with a vertical sliding groove arranged on the fixed plate 4;
as shown in fig. 3 and 6, the first transmission assembly includes a central shaft disposed below the push rod 42, and a runner 441 and a ratchet 44 fixedly sleeved on the central shaft, where the central shaft is rotationally connected with the inner wall of the sink, the runner 441 is in friction transmission with the push rod 42, the first transmission assembly and the second transmission assembly have the same structure, the central shaft of the first transmission assembly is disposed above the push rod 42, the central shaft of the second transmission assembly is disposed below the push rod 42, and the first toothed plate 45 is used to drive the second transmission assembly to rotate after the sliding block 31 collides with the balance plate 41;
as shown in fig. 6, the ratchet wheel 44 of the first transmission assembly is meshed with the first toothed plate 45 for transmission;
as shown in fig. 3 and 4, a second toothed plate 46 is disposed on the other side of the fixed plate 4, one end of the second toothed plate 46 is fixedly connected with a second extension plate 462 disposed on the fixed plate 4 through a spring rod 464, the second extension plate 462 is slidably connected with a transverse chute disposed on the other side of the fixed plate 4, and a first engaging tooth 461 is disposed on one side of the second toothed plate 46 facing the flywheel 3; an arc-shaped rack 32 is arranged on the flywheel 3 at the rear side of the rotation direction of the sliding block 31, and the arc-shaped rack 32 is used for driving the second toothed plate 46 to move downwards after the sliding block 31 passes through the balance plate 41;
as shown in fig. 3 and 4, the ratchet wheel 44 of the second transmission assembly is used for meshing transmission with the second toothed plate 46 when the second toothed plate 46 moves downward;
as shown in fig. 3 and 4, the fixed plate 4 is provided with a switching mechanism for laterally moving the second toothed plate 46 when the slider 31 is reset;
as shown in fig. 3 and fig. 4, the switching mechanism includes a rotating shaft 415 with one end rotatably connected to the fixed plate 4, a gear 414 sleeved on the rotating shaft 415 and close to one end of the fixed plate 4, and a driving belt 413 sleeved on the rotating shaft 415, the rotating shaft 415 is used for tensioning and guiding the driving belt 413, and the shaft lever 412 penetrates through the fixed plate 4 and is sleeved with the driving belt 413; the second extension plate 462 is provided with second meshing teeth 463 which are meshed with the gear 414 for transmission;
the rotating motor 33 is a commercially available rotating motor, the hinge point force sensor 22 is a commercially available force sensor, the controller is a commercially available controller, the lifting motor 13 is a commercially available lifting motor, and the displacement sensor, the strain gauge and the pressure sensor are commercially available devices.
Example 2: the embodiment describes a method for performing a landing gear running obstacle-surmounting impact test on a carrier-based aircraft, based on the landing gear running obstacle-surmounting impact test device in embodiment 1, as shown in fig. 1 to 6 and 11, comprising the following steps:
s1, preparation before test:
the balancing weight 212 on the hanging basket 21 is regulated, so that the system quality formed by the hanging basket 21 and the balancing weight 212 meets the test requirement, namely 5 tons; the lifting motor 13 is controlled, the lifting steel wire rope 14 is driven to drive the electromagnetic release lock 15 to move upwards, so that the counterweight adjusting mechanism and the landing gear 2 are driven to lift 40 cm above the flywheel 3 to avoid contact with the flywheel 3; at this time, the slider 31 is located at the side of the wheel 23;
s2, a test process:
controlling a lifting motor 13, driving a lifting steel wire rope 14 to drive an electromagnetic release lock 15 to move downwards, driving a counterweight adjusting mechanism and a landing gear 2 to synchronously descend, pressing a wheel 23 of the landing gear 2 onto a flywheel 3, and separating the electromagnetic release lock 15 from a hanging basket 21 to enable the electromagnetic release lock 15 to move upwards and reset;
starting the rotating motor 33 to enable the flywheel 3 to reversely heading (namely clockwise rotation), enabling the surface linear speed of the outer edge of the flywheel 3 to reach 240km/h within 3s, and enabling the second toothed plate 46 to do small-amplitude up-down reciprocating motion under the opposite action of the arc-shaped rack 32 and the spring rod 464 when the surface linear speed of the outer edge of the flywheel 3 does not reach the standard, so that the ratchet wheel 44 of the second transmission assembly cannot be driven to rotate, and enabling the sliding block 31 to be out of contact with the balance plate 41 through a notch on the balance plate 41 during rotation;
after the surface line speed of the outer edge of the flywheel 3 reaches the standard, the arc-shaped rack 32 on the flywheel 3 overcomes the acting force of the spring rod 464 to greatly drive the second toothed plate 46 to downwards, so that the second toothed plate 46 drives the ratchet wheel 44 and the rotating wheel 441 of the second transmission assembly to anticlockwise rotate, and drives the push rod 42 and the push plate 421 to move away from the fixed plate 4, so that the push plate 421 contacts with the slide block 31 and pushes the slide block 31 to the position right below the machine wheel 23, and the slide block 31 collides with the machine wheel 23 in the process of rotating along with the flywheel 3; at this time, the runner 441 of the first transmission assembly drives the ratchet 44 to rotate clockwise, the first toothed plate 45 is kept still, the balance plate 41 is kept still, and finally the position of the push plate 421 stays at the front side of the slide block 31;
after the sliding block 31 collides with the machine wheel 23, the sliding block 31 impacts the balance plate 41 during rotation, so that the impact end of the balance plate 41 is driven to move downwards, at the moment, the first toothed plate 45 moves downwards, the ratchet wheel 44 and the rotating wheel 441 of the first transmission assembly keep motionless, after the sliding block 31 is separated from the balance plate 41, the balance plate 41 swings upwards under the action of the spring 411 to recover, the first toothed plate 45 moves upwards, the ratchet wheel 44 and the rotating wheel 441 of the first transmission assembly are driven to rotate anticlockwise, and the push rod 42 and the push plate 421 are reset, so that the sliding block 31 is pushed to return to the side of the machine wheel 23;
during the collision of the sliding block 31 and the balance plate 41, the shaft lever 412 drives the gear 414 to rotate clockwise, the gear 414 drives the second extension plate 462 to horizontally translate in the direction away from the flywheel 3, after the sliding block 31 is separated from the balance plate 41, the shaft lever 412 rotates reversely, the second extension plate 462 drives the second toothed plate 46 to reset, and during the resetting of the second toothed plate 46, the arc-shaped rack 32 on the flywheel 3 also rotates to pass through, so that the gear 414 and the second extension plate 462 are not meshed, and the resetting of the push rod 42 is not influenced;
after the sliding block 31 collides, the hinge point force sensor 22 transmits signals to the controller, so that the linear speed of the outer edge surface of the flywheel 3 is controlled to be reduced to 0, and the single-run obstacle crossing impact test of the landing gear 2 is completed;
s3, test post-treatment:
after the single running over obstacle impact test of the landing gear 2 is completed, the travel data of the buffer 231 collected by the displacement sensor is obtainedsStrain data of landing gear 2 collected by strain gaugeεAir cavity pressure data of buffer 231 collected by pressure sensorPAnd a time course corresponding to each datat，
Obtained from a single testεThe impact load to which the landing gear 2 is subjected is calculated using equation (1)F：
F=εEA （1）
Wherein,Fis the impact load to which the landing gear 2 is subjected, in kN;εthe strain data of the landing gear 2 collected for the strain gauge,Ethe elastic modulus of the landing gear 2 material, in GPa,Athe cross-sectional area of the strut 232 or the stay 233 at one strain gauge attaching position is in mm;
obtained from a single tests、F、PAnd correspondingtDrawing outs-tGraph chart(s),F-tGraph diagramP-tA graph;
and then the weight of the weight adjusting mechanism is adjusted, and the weight adjusting mechanism and the landing gear 2 are moved upwards and reset through the lifting and releasing mechanism, so that the next test preparation is carried out.
Example 3: the difference between this embodiment and embodiment 1 is that, as shown in fig. 7, the bottom of the fixing plate 4 is fixedly connected with a horizontal plate 48, the horizontal plate 48 is provided with a liquid bag 47 filled with lubricating oil and a nozzle 471 facing the flywheel 3, the liquid bag 47 is located right below the second toothed plate 46, the nozzle 471 is disposed on the horizontal plate 48 corresponding to the position of the limiting chute, and the liquid bag 47 is communicated with the nozzle 471 through a connecting pipe 472.
When the surface line speed of the outer edge of the flywheel 3 does not reach the standard, when the flywheel 3 passes through the balance plate 41, the arc-shaped rack 32 is meshed with the first meshing teeth 461 to drive the second toothed plate 46 to move downwards, the second toothed plate 46 moves downwards to touch the liquid bag 47 and squeeze the liquid bag 47, lubricating oil is sequentially squeezed into the spray head 471 from the liquid bag 47 and the connecting pipe 472, and the spray head 471 sprays the lubricating oil to the limiting sliding groove, so that the abrasion of the sliding block 31 is reduced.
Test example: a single test was performed according to the test method of example 2 to obtain the stroke data s of the buffer 231 and the strain data of the landing gear 2εAir cavity pressure data of buffer 231PAnd calculate the impact load to which the landing gear 2 is subjected using equation (1)FAnd a time course corresponding to each datatSpecific data are shown in table 1;
table 1 buffer from a single testTravel data of 231sAir cavity pressure data of buffer 231PThe landing gear 2 is subjected to impact loadsFAnd a time course corresponding to each datat
| t/s | F/kN | t/s | s/mm | t/s | P/Mpa |
| 0.0005925 | 2.59413 | 0.0023625 | 277.2672 | 0.00534 | 3.1828375 |
| 0.001515 | 5.0318625 | 0.029425 | 365.100715 | 0.033585 | 3.2393125 |
| 0.002445 | 8.0641925 | 0.04385 | 424.188695 | 0.054885 | 3.51035 |
| 0.0028425 | 11.5127075 | 0.0709125 | 510.42523 | 0.07293 | 3.7814 |
| 0.004035 | 16.9530375 | 0.1160125 | 603.04965 | 0.092385 | 4.1315 |
| 0.0052275 | 22.482565 | 0.184575 | 680.6625175 | 0.11322 | 4.5493625 |
| 0.0065475 | 28.27965 | 0.2423 | 740.0699075 | 0.136365 | 5.1253375 |
| 0.0080025 | 33.868625 | 0.2693625 | 756.0396375 | 0.161835 | 5.865075 |
| 0.0097275 | 39.6656925 | 0.296425 | 763.3857175 | 0.181515 | 6.565275 |
| 0.0106575 | 41.50888 | 0.35235 | 764.343895 | 0.201645 | 7.4235875 |
| 0.0129075 | 42.371 | 0.3992625 | 753.48448 | 0.222945 | 8.4626 |
| 0.0150225 | 43.976345 | 0.494875 | 684.4952625 | 0.23892 | 9.4395 |
| 0.016215 | 45.4033125 | 0.5670375 | 617.7417925 | 0.26046 | 10.902025 |
| 0.0175425 | 47.7518825 | 0.604925 | 586.441135 | 0.27504 | 12.042675 |
| 0.018735 | 50.2193475 | 0.7330125 | 493.4973225 | 0.28893 | 13.14945 |
| 0.02019 | 52.68683 | 0.8430625 | 442.7135825 | 0.30351 | 14.5837375 |
| 0.0229725 | 54.767825 | 0.9206375 | 420.67536 | 0.31578 | 15.7865125 |
| 0.02535 | 55.60023 | 0.9495125 | 418.439595 | 0.326895 | 17.0288125 |
| 0.02853 | 55.60023 | 0.9928125 | 418.439595 | 0.338475 | 18.1864 |
| 0.0306525 | 56.135345 | 1.046925 | 426.1050675 | 0.35097 | 19.4456375 |
| 0.0344925 | 56.75964 | 1.1371375 | 455.1699775 | 0.36024 | 20.3209 |
| 0.0383325 | 55.68941 | 1.241775 | 503.3985425 | 0.3762 | 21.4389625 |
| 0.04164 | 54.5597325 | 1.36265 | 562.8059325 | 0.39102 | 22.043175 |
| 0.0460125 | 53.1922125 | 1.508775 | 611.6733 | 0.40329 | 22.34245 |
| 0.05025 | 52.151715 | 1.5556875 | 619.3387725 | 0.421575 | 22.3763375 |
| 0.054885 | 50.6652825 | 1.636875 | 618.6999875 | 0.444495 | 22.07705 |
| 0.0581925 | 49.08967 | 1.71625 | 603.688435 | 0.470655 | 21.6196625 |
| 0.061905 | 48.1383525 | 1.8245 | 573.98474 | 0.495195 | 20.9646375 |
| 0.0636225 | 48.2869975 | 2.033775 | 501.80158 | 0.51441 | 20.3039625 |
| 0.067065 | 49.2680475 | 2.1492375 | 478.48577 | 0.539415 | 19.248 |
| 0.0690525 | 50.0409875 | 2.2051625 | 473.375455 | 0.573225 | 17.717725 |
| 0.071835 | 51.4382225 | 2.2809375 | 474.0142575 | 0.59382 | 16.7125875 |
| 0.0751425 | 53.0138525 | 2.342275 | 479.7633575 | 0.617205 | 15.504175 |
| 0.0770025 | 54.05435 | 2.4577375 | 505.6343075 | 0.63411 | 14.65715 |
| 0.0808425 | 55.065115 | 2.6219125 | 550.030145 | 0.66027 | 13.34145 |
| 0.0836175 | 55.9569675 | 2.72655 | 572.70717 | 0.68526 | 12.2403125 |
| 0.086535 | 56.8488375 | 2.77165 | 583.566585 | 0.7098 | 11.11095 |
| 0.088785 | 57.294755 | 2.8889125 | 587.3993125 | 0.734805 | 10.094525 |
| 0.091965 | 57.65151 | 2.9845375 | 579.4144475 | 0.762825 | 9.044225 |
| 0.094215 | 58.573095 | 3.1054125 | 555.14046 | 0.78528 | 8.2762625 |
| 0.0962025 | 60.3568175 | 3.30205 | 510.7446225 | 0.817455 | 7.361475 |
| 0.0985875 | 61.8135175 | 3.3922625 | 497.33005 | 0.86538 | 6.384575 |
| 0.1005675 | 62.764835 | 3.444575 | 491.58095 | 0.90774 | 5.7352 |
| 0.10428 | 63.38913 | 3.554625 | 492.5391275 | 0.96075 | 5.0801625 |
| 0.10785 | 64.54854 | 3.641225 | 502.1209725 | 1.00197 | 4.66795 |
| 0.110505 | 64.6674525 | 3.816225 | 534.6992175 | 1.032525 | 4.4194875 |
| 0.1139475 | 64.37018 | 3.9461125 | 558.6538125 | 1.047345 | 4.3291375 |
| 0.1177875 | 65.083655 | 3.994825 | 567.9162475 | ||
| 0.120435 | 64.1918025 | ||||
| 0.1230825 | 61.93243 | ||||
| 0.125595 | 59.19739 | ||||
| 0.12732 | 56.819105 | ||||
| 0.129705 | 54.23271 | ||||
| 0.1315575 | 51.854425 | ||||
| 0.133545 | 49.0599375 | ||||
| 0.135795 | 46.324915 | ||||
| 0.13818 | 43.7979675 | ||||
| 0.140295 | 41.3305025 | ||||
| 0.1424175 | 38.8035725 | ||||
| 0.1448025 | 35.8901725 | ||||
| 0.147975 | 34.1361825 | ||||
| 0.1500975 | 33.3929575 | ||||
| 0.1552575 | 34.0767175 | ||||
| 0.1601625 | 32.9173075 | ||||
| 0.163605 | 31.133585 | ||||
| 0.1662525 | 29.6174375 | ||||
| 0.171285 | 27.4175125 | ||||
| 0.17685 | 25.3662325 | ||||
| 0.182805 | 23.166325 | ||||
| 0.191145 | 20.6096625 | ||||
| 0.2002875 | 18.1719125 | ||||
| 0.208095 | 16.3287425 | ||||
| 0.2163075 | 14.7233975 | ||||
| 0.22677 | 13.236965 | ||||
| 0.2396175 | 12.077555 | ||||
| 0.250605 | 11.3640625 | ||||
| 0.262125 | 10.9181275 | ||||
| 0.2727225 | 10.85868 | ||||
| 0.2842425 | 10.7694825 | ||||
| 0.293115 | 10.8289475 | ||||
| 0.3051675 | 10.8289475 | ||||
| 0.3152325 | 10.799215 | ||||
| 0.3219825 | 10.7694825 | ||||
| 0.331515 | 10.65057 | ||||
| 0.3403875 | 10.7397675 | ||||
| 0.350985 | 10.7397675 | ||||
| 0.361845 | 10.85868 | ||||
| 0.3680625 | 11.4532425 | ||||
| 0.3715125 | 12.166735 | ||||
| 0.375615 | 13.0288725 |
According to Table 1, the graph shown in FIG. 8 is drawnF-tGraph, it can be seen that: a gas peak of 0.04s appears and an oil peak of 0.12s appears.
According to Table 1, the graph shown in FIG. 9 is drawns-tThe graph shows that the buffer 231 stroke reaches a maximum of 750mm at 0.35 s; the damper 231 then begins to release energy, the damper 231 stroke begins to rebound, and when rebound to 420mm, the first round trip is completed and the second round trip is started, wherein the round trip time is 0.9s.
According to Table 1, the graph shown in FIG. 10 is plottedP-tThe graph shows that, near 0.4s, the air cavity pressure of the buffer 231 reaches a maximum value, and the positive stroke of the buffer 231 ends; when the back stroke of the buffer 231 starts, the oil return chamber pressure of the buffer 231 increases, and the main oil chamber pressure of the buffer 231 starts to decrease.
As can be seen from table 1 and fig. 8 to 10, the landing gear 2 used at present can keep a good state during impact resistance, and the situation of large damage and deformation does not occur, so that the landing gear 2 has normal performance and can be continuously used.
Claims (9)
1. The landing gear running obstacle crossing impact test device for the ship-based aircraft is characterized by comprising a foundation (1) provided with a sinking groove, a test bench arranged on the foundation (1), a balance weight adjusting mechanism arranged in the test bench and connected with the test bench in an up-down sliding manner, a lifting release mechanism connected between the balance weight adjusting mechanism and the test bench, a landing gear (2) fixed at the bottom of the balance weight adjusting mechanism, a flywheel (3) rotatably arranged in the sinking groove and a driving mechanism for driving the flywheel (3) to collide with the landing gear (2);
the counterweight adjusting mechanism comprises a hanging basket (21) and a counterweight (212) arranged in the hanging basket (21);
the landing gear (2) comprises a strut (232) and a strut (233), wherein one end of the strut is hinged with the bottom of the hanging basket (21), a buffer (231) is hinged with the other end of the strut (232), and a wheel (23) is rotatably connected with the buffer (231), and the other end of the strut (233) is hinged with the middle of the strut (232); hinge point force sensors (22) are arranged at the hinge positions of the hanging basket (21) and the support column (232) and the hinge points of the hanging basket (21) and the support rod (233), a plurality of strain gauges for detecting the strain of the landing gear (2) are arranged on the support column (232) and the support rod (233), and a pressure sensor for detecting the pressure of an air cavity of the buffer (231) and a displacement sensor for detecting the stroke of the buffer (231) in the collision process are arranged on the buffer (231);
a sliding block (31) sliding along the axial direction of the flywheel (3) is arranged on the curved surface of the flywheel (3), and the sliding block (31) is in sliding connection with a limiting chute arranged on the curved surface of the flywheel (3);
the driving mechanism comprises a fixed plate (4) fixedly connected with the inner wall of the sinking groove, a balance plate (41) rotationally connected with the fixed plate (4) through a shaft lever (412), a push rod (42) transversely arranged below the balance plate (41) and vertically penetrating through the fixed plate (4), and a first extension plate (43) arranged on the fixed plate (4) and fixedly connected with the balance plate (41) through a spring (411);
one end of the push rod (42) is provided with a push plate (421), and the fixed plate (4) is provided with a power mechanism for driving the push rod (42) to stir the sliding block (31).
2. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 1, wherein the test bed consists of two vertical plates (12) which are arranged on a foundation (1) along the vertical direction and a supporting plate (11) which is horizontally arranged on the top of the two vertical plates (12); the two opposite side surfaces of the vertical plates (12) are respectively provided with a sliding rail, and the side walls of the two sides of the hanging basket (21) are respectively provided with a roller (211) which is in sliding connection with the sliding rails.
3. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 2, wherein the lifting release mechanism comprises a lifting motor (13) arranged on a supporting plate (11) and an electromagnetic release lock (15) connected with the output end of the lifting motor (13) through a lifting steel wire rope (14), and the electromagnetic release lock (15) is connected with a hanging basket (21) in a matched mode through a movable buckle arranged at the top of the hanging basket (21).
4. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 1, wherein one end of a central shaft of the flywheel (3) is connected with a rotating motor (33) arranged on the inner wall of the sink, and the other end of the central shaft of the flywheel (3) is rotatably connected with the inner wall of the sink.
5. The landing gear running obstacle crossing impact test device for the ship-based aircraft according to claim 1, wherein the power mechanism comprises a first transmission assembly arranged on one side of a fixed plate (4) and a second transmission assembly arranged on the other side of the fixed plate (4), one end of the balance plate (41) is provided with a notch for a sliding block (31) to pass through, the bottom of one end of the balance plate (41) is provided with a first toothed plate (45) hinged with the balance plate, and the first toothed plate (45) is in sliding connection with a vertical sliding groove arranged on the fixed plate (4);
the first transmission assembly comprises a central shaft, a rotating wheel (441) and a ratchet wheel (44), wherein the rotating wheel (441) and the ratchet wheel (44) are fixedly sleeved on the central shaft, the central shaft is rotationally connected with the inner wall of the sinking groove, the rotating wheel (441) and the push rod (42) are in friction transmission, the first transmission assembly and the second transmission assembly are identical in structure, the central shaft of the first transmission assembly is arranged above the push rod (42), the central shaft of the second transmission assembly is arranged below the push rod (42), and the first toothed plate (45) is used for driving the second transmission assembly to rotate after the sliding block (31) collides with the balance plate (41);
the ratchet wheel (44) of the first transmission assembly is meshed with the first toothed plate (45) for transmission;
the other side of the fixed plate (4) is provided with a second toothed plate (46), one end of the second toothed plate (46) is fixedly connected with a second extension plate (462) arranged on the fixed plate (4) through a spring rod (464), the second extension plate (462) is slidably connected with a transverse sliding groove arranged on the other side of the fixed plate (4), and one side of the second toothed plate (46) facing the flywheel (3) is provided with a first meshing tooth (461); an arc-shaped rack (32) is arranged on the flywheel (3) at the rear side of the sliding block (31) in the rotating direction, and the arc-shaped rack (32) is used for driving the second toothed plate (46) to move downwards after the sliding block (31) passes through the balance plate (41);
the ratchet wheel (44) of the second transmission assembly is used for meshing transmission with the second toothed plate (46) when the second toothed plate (46) moves downwards;
the fixed plate (4) is provided with a switching mechanism for transversely moving the second toothed plate (46) when the sliding block (31) is reset.
6. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 5, wherein the switching mechanism comprises a rotating shaft (415) with one end rotatably connected with the fixed plate (4), a gear (414) sleeved on the rotating shaft (415) and close to one end of the fixed plate (4), and a transmission belt (413) sleeved on the rotating shaft (415), and the shaft lever (412) penetrates through the fixed plate (4) and is sleeved with the transmission belt (413); the second extension plate (462) is provided with second meshing teeth (463) which are meshed with the gear (414) for transmission.
7. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 5, wherein a horizontal plate (48) is fixedly connected to the bottom of the fixed plate (4), a liquid bag (47) filled with lubricating oil and a spray nozzle (471) facing the flywheel (3) are arranged on the horizontal plate (48), the liquid bag (47) is located under the second toothed plate (46), the spray nozzle (471) is arranged on the horizontal plate (48) corresponding to the position of the limiting chute, and the liquid bag (47) is communicated with the spray nozzle (471) through a connecting pipe (472).
8. The landing gear running obstacle surmounting impact test device for the ship-based aircraft according to claim 1, wherein the hinge point force sensor (22) is provided with a controller, and the controller is electrically connected with the hinge point force sensor (22) and the rotating motor (33).
9. The method for the landing gear running obstacle crossing impact test of the carrier-based aircraft is based on the landing gear running obstacle crossing impact test device of the carrier-based aircraft according to any one of claims 1-8, and is characterized by comprising the following steps:
s1, preparation before test:
the balancing weight (212) on the hanging basket (21) is regulated, so that the quality of a balancing weight regulating mechanism consisting of the hanging basket (21) and the balancing weight (212) meets the test requirement; then controlling the lifting release mechanism to synchronously lift the balance weight adjusting mechanism and the landing gear (2) to the upper part of the flywheel (3) and avoid contacting with the flywheel (3); at this time, the slide block (31) is positioned at the side of the machine wheel (23);
s2, a test process:
the lifting release mechanism is controlled to drive the balance weight adjusting mechanism and the landing gear (2) to synchronously descend, a wheel (23) of the landing gear (2) is pressed onto the flywheel (3), and then the lifting release mechanism is separated from the hanging basket (21), so that the electromagnetic release lock (15) moves upwards to reset;
starting the flywheel (3) to rotate in a reverse course, and enabling the surface line speed of the outer edge of the flywheel (3) to reach 240km/h within 3s, wherein after the surface line speed of the outer edge reaches the standard, the sliding block (31) passes through the balance plate (41), the power mechanism drives the push rod (42) and the push plate (421) to slide in a direction away from the fixed plate (4), and the sliding block (31) is stirred to be right below the flywheel (23) from the side of the flywheel (23), so that the sliding block (31) collides with the flywheel (23) in the rotating process along with the flywheel (3);
the sliding block (31) passes through the balance plate (41) after colliding with the machine wheel (23), and the power mechanism drives the push rod (42) and the push plate (421) to slide towards the direction close to the fixed plate (4), so that the sliding block (31) is shifted to the side of the machine wheel (23) from the right lower part of the machine wheel (23);
controlling the linear speed of the outer edge surface of the flywheel (3) to be reduced to 0, and finishing a single-run obstacle-crossing impact test of the landing gear (2);
s3, test post-treatment:
after the single running obstacle surmounting impact test of the landing gear (2) is completed, the travel data of the buffer (231) collected by the displacement sensor is obtainedsStrain data of landing gear (2) collected by strain gaugeεAir cavity pressure data of buffer (231) collected by pressure sensorPAnd a time course corresponding to each datat，
Obtained from a single testεAnd calculates the impact load to which the landing gear (2) is subjected by using the formula (1)F：
F=εEA （1）
Wherein,Fimpact load in kN for the landing gear (2);ε-strain data of the landing gear (2) collected for the strain gauge;Ethe elastic modulus of the material of the landing gear (2) is GPa;Athe cross section area of the strut (232) or the stay bar (233) positioned at one strain gauge pasting position is expressed in mm;
obtained from a single tests、F、PAnd correspondingtDrawing outs-tGraph chart(s),F-tGraph diagramP-tA graph;
and then the weight of the weight adjusting mechanism is adjusted, and the weight adjusting mechanism and the landing gear (2) are moved upwards and reset through the lifting and releasing mechanism, so that the next test preparation is carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311465427.4A CN117184443B (en) | 2023-11-07 | 2023-11-07 | Device and method for slide obstacle surmounting impact test of landing gear of carrier-based aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311465427.4A CN117184443B (en) | 2023-11-07 | 2023-11-07 | Device and method for slide obstacle surmounting impact test of landing gear of carrier-based aircraft |
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| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| 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 |
| KR20220050311A (en) * | 2020-10-16 | 2022-04-25 | (주)지브이엔지니어링 | A Landing Gear Testing Apparatus |
| CN114739619A (en) * | 2022-06-09 | 2022-07-12 | 中国飞机强度研究所 | Combined loading test system and loading test method for airplane pneumatic impact test |
| CN116986012A (en) * | 2023-09-25 | 2023-11-03 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
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| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| KR20220050311A (en) * | 2020-10-16 | 2022-04-25 | (주)지브이엔지니어링 | A Landing Gear Testing Apparatus |
| 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 |
| CN114739619A (en) * | 2022-06-09 | 2022-07-12 | 中国飞机强度研究所 | Combined loading test system and loading test method for airplane pneumatic impact test |
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