CN117087873A - Device and method for measuring collision load of carrier-based aircraft blocking hook landing - Google Patents
Device and method for measuring collision load of carrier-based aircraft blocking hook landing Download PDFInfo
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- CN117087873A CN117087873A CN202311360064.8A CN202311360064A CN117087873A CN 117087873 A CN117087873 A CN 117087873A CN 202311360064 A CN202311360064 A CN 202311360064A CN 117087873 A CN117087873 A CN 117087873A
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000000903 blocking effect Effects 0.000 title claims description 36
- 238000002474 experimental method Methods 0.000 claims abstract description 66
- 229910000831 Steel Inorganic materials 0.000 claims description 25
- 239000010959 steel Substances 0.000 claims description 25
- 238000004804 winding Methods 0.000 claims description 18
- 230000007246 mechanism Effects 0.000 claims description 17
- 238000005096 rolling process Methods 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 9
- 230000009471 action Effects 0.000 claims description 3
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- 230000001737 promoting effect Effects 0.000 claims 1
- 238000005259 measurement Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
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- 239000000969 carrier Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
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- 238000011156 evaluation Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a carrier-based aircraft arresting hook landing impact load measuring device and a measuring method, which belong to the technical field of aircraft arresting hook measurement and comprise an experiment bench, wherein an experiment base is arranged below the experiment bench, the top of the experiment bench is fixedly connected with a lifting locking system, a hanging basket is connected below the lifting locking system, the left side and the right side of the hanging basket are respectively provided with a group of guiding devices, the left side of the bottom of the hanging basket is fixedly connected with a landing gear, the rear side of the hanging basket is provided with an arresting hook, the inside of the hanging basket is provided with a counterweight chamber, a counterweight block is placed in the counterweight chamber, the upper part of the left side of the experiment base is fixedly connected with a three-way force measuring platform, the right side of the experiment base is provided with a flywheel groove, and the flywheel groove is internally provided with a rotary flywheel.
Description
Technical Field
The invention relates to the technical field of aircraft arresting hook measurement, in particular to a device and a method for measuring the collision load of an aircraft arresting hook on a carrier-borne aircraft.
Background
As is well known, carrier-based aircraft is critical to the ability to play a fight on aircraft carriers. For the carrier-borne aircraft, the carrier landing technology is both key and difficult. When the carrier-based aircraft is blocked and landed on the ship, the aircraft enters the field along a certain lower slide track trace angle in space, and the sinking speed of the aircraft relative to the ship surface can reach 7m/s. When the aircraft is in the glide path or near deck, the hook is placed in the lowermost position waiting for the catch hook to be in the upper rope. The forward section of a typical offensive aircraft carrier is approximately 29.6m-53m in which the aircraft has been lowered to a height that can be used for the rope. When taxiing the tow hook on a pre-rope aircraft, the catch is most likely to strike the deck before the aircraft is not grounded. At this point, the arresting hooks will be impacted by the deck. Because the sinking speed of the aircraft is high, the arresting hook can generate a large rebound angular speed, and if the upward turning trend is not prevented in time, the hook is finally turned up too high to enable the hook to be in a rope state, and even the hook can be turned up to touch the airframe.
At present, research on a blocking hook carrier impact measuring device and a testing method based on a flywheel in a laboratory environment is still blank, and at present, a carrier adaptation test flight test is generally adopted for verification, but the risk is high. The test risk and cost of the blocking hook landing impact performance test in the laboratory are low, the blocking hook impact performance can be obtained rapidly, and a basis is provided for the blocking hook performance design of the carrier-based aircraft and the influence evaluation of the blocking hook impact on the body structure and the service life of the blocking hook. Therefore, research on the device and the method for measuring the impact of the arresting hook carrier based on the flywheel in the laboratory environment is extremely important.
Disclosure of Invention
In order to solve the technical problems, the invention provides a device and a method for measuring the impact load of a carrier-based aircraft arresting hook landing ship.
The technical scheme of the invention is as follows: the utility model provides a carrier-based aircraft arresting hook carrier landing impact load measuring device, includes the experiment bench, the below of experiment bench is equipped with the experiment base, the top fixedly connected with of experiment bench promotes the locking system, the below that promotes the locking system is connected with the hanging flower basket, the left and right sides of hanging flower basket respectively is equipped with a set of guider, and every guider of group includes two leading wheels, and two leading wheels rotate respectively and are connected in the upper and lower both sides outer wall of hanging flower basket, the outside of leading wheel with experiment bench inner wall butt, hanging flower basket bottom left side fixedly connected with undercarriage, the rear side of hanging flower basket is equipped with the arresting hook, the inside of hanging flower basket is equipped with the counter weight room, place the balancing weight in the counter weight room, the left side top fixedly connected with force measuring platform of experiment base, the right side of experiment base is equipped with the flywheel groove, be equipped with rotatory flywheel in the flywheel groove, the outside parcel of rotatory flywheel has type force transducer, the right side top of experiment base is equipped with the stopper;
the lifting locking system comprises a rope rolling seat, the bottom of the rope rolling seat is fixedly connected with the top of the experiment bench, the middle part of the rope rolling seat is rotationally connected with a rotating shaft, a gear disc and a locking disc are installed on the rear side of the rotating shaft, the top of the experiment bench is provided with a sliding groove, a sliding block is slidingly connected above the sliding groove, the left side of the sliding block is provided with a first electric cylinder, the telescopic end of the first electric cylinder is fixedly connected with the sliding block, the top of the sliding block is fixedly connected with a rope rolling motor, the output shaft of the rope rolling motor is in transmission connection with a gear, the gear is in meshed transmission with the gear disc, the right side of the locking disc is provided with a locking mechanism, the locking mechanism is in butt joint with the right side of the locking disc, the side wall of the rotating shaft is fixedly connected with a steel rope, the tail end of the steel rope is fixedly connected to the right side of the experiment bench, the top of the experiment bench is provided with a lifting hole, the left side and the right side of the lifting hole are respectively provided with a fixed pulley, the bottom of the fixed pulley is fixedly connected with the top of the hanging basket, the steel rope is fixedly connected with the top of the two hanging basket, and the two fixed pulleys are respectively and are connected with the two ends of the steel rope fixedly connected with the middle part of the steel rope;
the left outer wall fixedly connected with PLC controller of experiment rack, just PLC controller and electronic jar one, rope winding motor, rotation steering wheel, rotatory flywheel, type force transducer all electric connection.
Further, the undercarriage includes the fixed block, the top of fixed block with hanging flower basket bottom rigid connection, fixed block left side below is equipped with the hinge piece, the lower extreme of hinge piece articulates there is the oil gas shock strut, the bottom rotation of oil gas shock strut is connected with the connecting cylinder, the connecting cylinder rotation is connected with the shaft, shaft both ends fixedly connected with aircraft tire, the right side below of fixed block is equipped with the rudder mount, the rear side fixedly connected with of rudder mount rotates the steering wheel, the output shaft lateral wall fixedly connected with landing rod of rotation steering wheel, the lower extreme of landing rod with the lower extreme right side of oil gas shock strut articulates.
Description: the whole device is buffered through the oil gas shock strut, the service life of the whole device can be prolonged, the lifting rod is controlled to rotate through the rotating steering engine, and then the impact angle of the oil gas shock strut is adjusted.
Further, the rotary flywheel comprises a flywheel shaft, the middle part of the flywheel shaft is fixedly connected with a rotary wheel, a plurality of embedded rods are arranged on the outer side of the rotary wheel, a flywheel baffle is arranged on the front side and the rear side of the rotary wheel respectively, the bottom of the flywheel baffle is fixedly connected with the experiment base, a flywheel motor is arranged at the front end of the flywheel shaft, and an output shaft of the flywheel motor is in transmission connection with the flywheel shaft.
Description: the type force sensor is installed on the surface of the rotating wheel through the clamping connection of the embedded rod and the type force sensor, and the impact of the aircraft on the ground under high-speed running is simulated through the rotation of the rotating wheel.
Further, the type force sensor comprises a type shell, the type shell is internally connected with a three-way force sensor, the left side and the right side of the three-way force sensor are respectively provided with a clamping groove, and the clamping grooves are clamped with the embedding rods.
Description: the clamping groove is clamped with the embedded rod, so that the type force sensor is convenient to install and replace.
Further, each group of guiding device comprises two guiding wheels, the two guiding wheels are respectively connected with the outer walls of the upper side and the lower side of the hanging basket in a rotating mode, the outer sides of the guiding wheels are in sliding connection with the inner wall of the experiment bench, and the top of the hanging basket is fixedly connected with a hanging ring which is used for being connected with a connecting piece.
Description: and the hanging ring at the top of the hanging basket is connected with the connecting piece.
Further, the terminal fixed connection of steel cable is on the right side of experiment rack, and the top of experiment rack is equipped with the lifting hole, the left and right sides of lifting hole respectively is equipped with a fixed pulley, the bottom of fixed pulley and the top fixed connection of experiment rack, the both ends of steel cable twine respectively on two fixed pulleys, and the middle part of steel cable falls into the lifting hole, the connecting piece includes the pulley shell, the inside rotation of pulley shell is connected with a movable pulley, the steel cable is walked around the movable pulley below, the below of pulley shell is equipped with the go-between, the go-between with the link is connected.
Description: the connecting ring is convenient to be connected with the hanging ring at the top of the hanging basket, and the movable pulley can reduce the force required by the rope winding motor when the hanging basket is lifted, so that the energy consumption of the rope winding motor is reduced.
Further, the arresting hook comprises a connecting block, a fixed rod is arranged below the connecting block, a rotating rod is hinged to the fixed rod, and a hook head is fixedly connected to the lower portion of the rotating rod.
Description: the hook head rotates to the right after colliding with the surface of the rotating wheel.
Further, the stopper comprises a blocking plate, the blocking plate is slidably connected with the upper right side of the experiment base, an actuator is fixedly connected to the right side of the blocking plate, the bottom of the actuator is fixedly connected with the experiment base, and the actuator is electrically connected with the PLC.
Description: after the hook head impacts the surface of the rotating wheel, the blocking plate rotates rightwards under the driving of the rotating wheel, and the blocking plate is shielded above the rotating wheel through the actuator, so that the hook head is prevented from secondarily impacting the rotating wheel.
Further, the locking mechanism comprises a hinging seat, a locking hook is hinged to the hinging seat, the left side of the locking hook is abutted to the locking disc, an electric cylinder II is arranged on the right side of the locking hook, the bottom of the electric cylinder II is fixedly connected with the top of the experiment bench, the telescopic end of the electric cylinder II is clamped with the right end of the locking hook, and the electric cylinder II is electrically connected with the PLC.
Description: the locking hook is separated from the locking disc through the electric cylinder, so that the hanging basket can do free falling motion downwards.
The invention also provides a carrier-based aircraft arresting hook carrier landing impact load measuring method, which is based on the carrier-based aircraft arresting hook carrier landing impact load measuring device and comprises the following steps:
s1, connecting the lower end of the connecting piece with the top of the hanging basket, controlling the starting of a rope winding motor through the PLC, winding a steel rope on a rotating shaft after the rope winding motor is started, further lifting the hanging basket, adding a balancing weight into a balancing weight chamber to increase the load of the hanging basket, and increasing the impact force of a blocking hook on a rotating flywheel;
s2, after lifting the hanging basket, the locking mechanism is clamped with the locking disc, the PLC controls the rope winding motor to stop, the PLC controls the rotary flywheel to rotate, then the PLC controls the locking mechanism to unlock, the hanging basket falls under the action of gravity, the arresting hook and the aircraft tire respectively smash to a type force sensor and a three-way force measuring platform on the rotary flywheel, and then the arresting hook is sprung under the reaction force of the type force sensor;
and S3, after the type force sensor detects the impact force of the blocking hook, the PLC controls the stopper to start, and after the stopper is started, the sprung blocking hook falls above the stopper.
The beneficial effects of the invention are as follows:
(1) The method comprises the steps that a blocking hook landing impact test is carried out in a special test bench, a hanging basket, a counterweight and a landing gear form an equivalent weight system, in the test process, the hanging basket is lifted and released by a lifting locking system, the landing gear touching speed of a blocking hook is simulated, when the hanging basket reaches a designated throwing height, a rotating wheel is started, the rotating speed of the rotating wheel simulates the course load relative to a ship surface when the blocking hook lands on the ship, when the rotating speed of a flywheel meets the test requirement, the hanging basket is released by the lifting locking system, the blocking hook and the landing gear touch the ground, and the dynamic responses of the landing gear system and the blocking hook system are synchronously tested;
(2) The measuring device and the measuring method thereof provided by the invention can simulate the landing impact process of the arresting hook with high precision;
(3) The invention can truly restore the impact relationship between the main landing gear and the arresting hook of the aircraft and more truly simulate the impact boundary condition of the arresting hook of the carrier-based aircraft;
(4) According to the invention, through adjusting the lifting height and the flywheel rotating speed, the landing impact dynamics response of the arresting hook under the combination of different descending speeds and different landing speeds can be tested;
(5) The single force sensor is arranged on the rotary flywheel, and after the blocking hook impacts the rotary flywheel, the blocking hook can not impact the force sensor, so that the condition of invalid impact is caused.
Drawings
FIG. 1 is a schematic view of the overall structure of the measuring device of the present invention;
FIG. 2 is an enlarged view at A in FIG. 1;
FIG. 3 is an enlarged view at B in FIG. 1;
FIG. 4 is a diagram showing the connection between the locking mechanism and the locking plate according to the present invention;
FIG. 5 is a left side view of the gear to gear plate connection of the present invention;
FIG. 6 is a left side view of the rotary flywheel of the present invention;
FIG. 7 is a perspective view of a type force sensor of the present invention;
wherein, 1-bench, 2-bench, 3-lift locking system, 4-basket, 41-guide, 42-guide wheel, 5-landing gear, 6-arresting hook, 43-counterweight chamber, 44-counterweight, 7-three-way load cell, 8-flywheel slot, 9-rotary flywheel, 91- type force sensor, 21-stopper, 31-rope seat, 32-rotary shaft, 33-toothed wheel disk, 34-locking disk, 35-slide slot, 351-slide block, 352-electric cylinder one, 353-rope motor, 354-gear, 36-locking mechanism, 37-steel rope, 11-lifting hole, 38-fixed pulley, 39-connector, 12-PLC controller, 51-fixed block, 52-hinge block, 53-hydro-pneumatic shock strut, 54-connector cylinder, 55-wheel axle, 56-aircraft tire, 57-rudder seat, 58-landing rod, 59-rotary steering engine, 92-flywheel axle, 93-rotary wheel, 94-embedded rod, 95-flywheel baffle, 96-flywheel motor housing, -slide block, 35-slide block, 352-electric cylinder one, 353-rope motor, 354-pulley housing, 12-PLC controller, 51-fixed block, 52-hinge block, 53-hydro-damping strut, 54-link, 63-hinge joint, 393, 63-link type joint, 393, connecting rod, 63-rotating ring type joint, 393, 362-rotating link, and connecting rod type joint, 63-rotating link type joint type, 63-rotating link, 63-hinge joint type, 393.
Detailed Description
Example 1: as shown in fig. 1, the device for measuring the collision load of the carrier-based aircraft on the blocking hook comprises an experiment bench 1, wherein an experiment base 2 is arranged below the experiment bench 1, a lifting locking system 3 is fixedly connected to the top of the experiment bench 1, a hanging basket 4 is connected below the lifting locking system 3, a group of guide devices 41 are respectively arranged on the left side and the right side of the hanging basket 4, each group of guide devices 41 comprises two guide wheels 42, the two guide wheels 42 are respectively and rotatably connected to the outer walls of the upper side and the lower side of the hanging basket 4, the outer sides of the guide wheels 42 are in sliding connection with the inner wall of the experiment bench 1, a landing gear 5 is fixedly connected to the left side of the bottom of the hanging basket 4, a blocking hook 6 is arranged on the rear side of the hanging basket 4, a counterweight chamber 43 is arranged in the counterweight chamber 43, a balancing weight 44 is arranged in the upper side of the experiment base 2, a three-way force measuring platform 7 is fixedly connected to the left side of the experiment base 2, a flywheel groove 8 is arranged on the right side of the experiment base 2, a rotating flywheel 9 is arranged in the flywheel groove 8, a type force sensor 91 is wrapped on the outer side of the rotating flywheel 9, and a stopper 21 is arranged on the upper right side of the experiment base 2;
as shown in fig. 3-5, the lifting locking system 3 comprises a rope rolling seat 31, the bottom of the rope rolling seat 31 is fixedly connected with the top of the experiment table 1, the middle part of the rope rolling seat 31 is rotatably connected with a rotating shaft 32, the rear side of the rotating shaft 32 is provided with a gear disc 33 and a locking disc 34, the top of the experiment table 1 is provided with a sliding groove 35, the upper side of the sliding groove 35 is slidingly connected with a sliding block 351, the left side of the sliding block 351 is provided with an electric cylinder one 352, the telescopic end of the electric cylinder one 352 is fixedly connected with the sliding block 351, the top of the sliding block 351 is fixedly connected with a rope rolling motor 353, the output shaft of the rope rolling motor 353 is in transmission connection with a gear 354, the gear 354 is in meshed transmission with the gear disc 33, the right side of the locking disc 34 is provided with a locking mechanism 36, the locking mechanism 36 is in abutting connection with the right side of the locking disc 34, the side wall of the rotating shaft 32 is fixedly connected with a steel rope 37, the tail end of the steel rope 37 is fixedly connected to the right side of the experiment table 1, the top of the experiment table 1 is provided with a lifting hole 11, the left side and right side of the sliding block 351 are respectively provided with a fixed pulley 38, the bottom of the fixed pulley 38 is fixedly connected with the top of the hanging basket 37 and two ends of the fixed pulley 37 are fixedly connected with the lifting pulleys 37 in the middle part of the experiment table 37, and the lifting hole 37 are fixedly connected with the two ends of the steel rope 37 in the middle part 37, and the lifting hole 37 are respectively, and the lifting hole is fixedly connected with the lifting rope 37 and the lifting hole 37 is in the middle part and the lifting 4 is in the lifting position;
the left outer wall of the experiment bench 1 is fixedly connected with a PLC 12, and the PLC 12 is electrically connected with an electric cylinder one 352, a rope winding motor 353, a rotary steering engine 59, a rotary flywheel 9 and a type force sensor 91.
The landing gear 5 comprises a fixed block 51, the top of the fixed block 51 is rigidly connected with the bottom of the hanging basket 4, a hinge block 52 is arranged below the left side of the fixed block 51, the lower end of the hinge block 52 is hinged with an oil-gas shock-absorbing support 53, the bottom of the oil-gas shock-absorbing support 53 is rotationally connected with a connecting cylinder 54, the connecting cylinder 54 is rotationally connected with a wheel shaft 55, two ends of the wheel shaft 55 are fixedly connected with an airplane tire 56, a rudder mount 57 is arranged below the right side of the fixed block 51, the rear side of the rudder mount 57 is fixedly connected with a rotary steering engine 59, the side wall of an output shaft of the rotary steering engine 59 is fixedly connected with a lifting rod 58, and the lower end of the lifting rod 58 is hinged with the right side of the lower end of the oil-gas shock-absorbing support 53.
As shown in fig. 6, the rotary flywheel 9 includes a flywheel shaft 92, a rotary wheel 93 is fixedly connected to the middle of the flywheel shaft 92, a plurality of embedded rods 94 are arranged on the outer side of the rotary wheel 93, a flywheel baffle 95 is respectively arranged on the front side and the rear side of the rotary wheel 93, the bottom of the flywheel baffle 95 is fixedly connected with the experiment base 2, a flywheel motor 96 is arranged at the front end of the flywheel shaft 92, and an output shaft of the flywheel motor 96 is in transmission connection with the flywheel shaft 92.
As shown in fig. 7, the type force sensor 91 includes a type housing 911, and a three-way force sensor 912 is connected to the inside of the type housing 911, and two clamping grooves 913 are provided on the left and right sides of the three-way force sensor 912, respectively, and the clamping grooves 913 are engaged with the clamping bars 94.
Each group of guide devices 41 comprises two guide wheels 42, the two guide wheels 42 are respectively connected to the outer walls of the upper side and the lower side of the hanging basket 4 in a rotating mode, the outer sides of the guide wheels 42 are in sliding connection with the inner wall of the experiment table 1, and hanging rings 45 used for being connected with connecting pieces 39 are fixedly connected to the top of the hanging basket 4.
As shown in fig. 2, the tail end of the steel rope 37 is fixedly connected to the right side of the experiment bench 1, the top of the experiment bench 1 is provided with a lifting hole 11, the left side and the right side of the lifting hole 11 are respectively provided with a fixed pulley 38, the bottom of the fixed pulley 38 is fixedly connected with the top of the experiment bench 1, two ends of the steel rope 37 are respectively wound on the two fixed pulleys 38, the middle of the steel rope 37 falls into the lifting hole 11, the connecting piece 39 comprises a pulley shell 391, a movable pulley 392 is rotatably connected to the inside of the pulley shell 391, the steel rope 37 bypasses the lower side of the movable pulley 392, a connecting ring 393 is arranged below the pulley shell 391, and the connecting ring 393 is connected with the hanging ring 45.
The arresting hook 6 comprises a connecting block 61, a fixed rod 62 is arranged below the connecting block 61, a rotating rod 63 is hinged to the fixed rod 62, and a hook head 64 is fixedly connected to the lower side of the rotating rod 63.
The stopper 21 comprises a stopper plate 211, the stopper plate 211 is slidably connected with the upper right side of the experiment base 2, an actuator 212 is fixedly connected to the right side of the stopper plate 211, the bottom of the actuator 212 is fixedly connected with the experiment base 2, and the actuator 212 is electrically connected with the PLC 12.
The locking mechanism 36 comprises a hinging seat 361, a locking hook 362 is hinged on the hinging seat 361, the left side of the locking hook 362 is abutted against the locking disc 34, an electric cylinder II 363 is arranged on the right side of the locking hook 362, the bottom of the electric cylinder II 363 is fixedly connected with the top of the experiment bench 1, the telescopic end of the electric cylinder II 363 is clamped with the right end of the locking hook 362, and the electric cylinder II 363 is electrically connected with the PLC 12.
Example 2: on the basis of embodiment 1, the embodiment provides a method for measuring the impact load of a carrier-based aircraft arresting hook carrier landing, and the device for measuring the impact load of the carrier-based aircraft arresting hook carrier landing on the basis of embodiment 1 comprises the following steps:
s1, connecting the lower end of a connecting piece 39 with the top of a hanging basket 4, controlling a rope winding motor 353 to start through a PLC (programmable logic controller) 12, winding a steel rope 37 on a rotating shaft 32 after the rope winding motor 353 is started, further lifting the hanging basket 4, adding a balancing weight 44 into a balancing weight chamber 43 to increase the load on the hanging basket 4, and increasing the impact force of a blocking hook 6 on a rotating flywheel 9;
s2, after lifting the hanging basket 4, the locking mechanism 36 is clamped with the locking disc 34, the PLC 12 controls the rope winding motor 353 to stop, the PLC 12 controls the rotary flywheel 9 to rotate, then the PLC 12 controls the locking mechanism 36 to unlock, the hanging basket 4 falls under the action of gravity, the arresting hook 6 and the aircraft tire 56 respectively smash to a type force sensor 91 and a three-way force measuring platform 7 on the rotary flywheel 9, and then the arresting hook 6 is sprung up under the reaction force of the type force sensor 91;
and S3, when the type force sensor 91 detects the impact force of the blocking hook 6, the PLC 12 controls the stopper 21 to start, and after the stopper 21 starts, the sprung blocking hook 6 falls above the stopper 21.
The three-way force measuring platform 7, the three-way force sensor 912, the rope winding motor 353, the PLC controller 12, the rotary steering engine 59, the flywheel motor 96, the first electric cylinder 352, the second electric cylinder 363 and the actuator 212 adopted in the above embodiment are all commercially available products, so long as the functions of the present invention can be realized, and the person skilled in the art can select and use the three-way force measuring platform according to the conventional general knowledge, and no special limitation is made herein.
Claims (10)
1. The utility model provides a carrier-based aircraft arresting hook carrier landing impact load measuring device, its characterized in that, including experiment bench (1), the below of experiment bench (1) is equipped with experiment base (2), the top fixedly connected with of experiment bench (1) promotes locking system (3), the below of promoting locking system (3) is connected with hanging flower basket (4), the left and right sides of hanging flower basket (4) respectively is equipped with a set of guider (41), the left side fixedly connected with undercarriage (5) in hanging flower basket (4) bottom, the rear side of hanging flower basket (4) is equipped with arresting hook (6), the inside of hanging flower basket (4) is equipped with counter weight room (43), placed balancing weight (44) in counter weight room (43), the left side top fixedly connected with three-way force measuring platform (7) of experiment base (2), the right side of experiment base (2) is equipped with flywheel groove (8), be equipped with rotatory flywheel (9) in the flywheel groove (8), the outside parcel of rotatory flywheel (9) has type force sensor (91), the right side top of blocking base (2) is equipped with ware (21);
the lifting locking system (3) comprises a rope rolling seat (31), the bottom of the rope rolling seat (31) is fixedly connected with the top of the experiment bench (1), the middle part of the rope rolling seat (31) is rotationally connected with a rotating shaft (32), a gear disc (33) and a locking disc (34) are installed on the rear side of the rotating shaft (32), a sliding groove (35) is formed in the top of the experiment bench (1), a sliding block (351) is slidingly connected above the sliding groove (35), an electric cylinder I (352) is arranged on the left side of the sliding block (351), a rope rolling motor (353) is fixedly connected with the top of the sliding block (351), a gear (354) is in transmission connection with the output shaft of the rope rolling motor (353), the gear (354) is in transmission engagement with the gear disc (33), a locking mechanism (36) is arranged on the right side of the locking disc (34), and the locking mechanism (36) is in contact with the rotating shaft (37) on the right side of the locking disc (34), and is fixedly connected with the side wall (37) of the steel rope (37) of the middle part (37) of the hanging basket (4);
the left outer wall of the experiment bench (1) is fixedly connected with a PLC (programmable logic controller) 12, and the PLC 12 is electrically connected with an electric cylinder I (352), a rope winding motor 353, a rotating steering engine 59, a rotating flywheel 9 and a type force sensor 91.
2. The ship-based aircraft arresting hook landing impact load measuring device according to claim 1, wherein the landing gear (5) comprises a fixed block (51), the top of the fixed block (51) is rigidly connected with the bottom of the hanging basket (4), a hinging block (52) is arranged below the left side of the fixed block (51), an oil-gas shock strut (53) is hinged to the lower end of the hinging block (52), a connecting cylinder (54) is rotatably connected to the bottom of the oil-gas shock strut (53), an axle (55) is rotatably connected to the connecting cylinder (54), aircraft tires (56) are fixedly connected to two ends of the axle (55), a rudder stand (57) is arranged below the right side of the fixed block (51), a rotary steering engine (59) is fixedly connected to the rear side of the steering engine stand (57), a lifting rod (58) is fixedly connected to the side wall of an output shaft of the rotary steering engine (59), and the lower end of the lifting rod (58) is hinged to the right side of the lower end of the oil-gas shock strut (53).
3. The ship-based aircraft arresting hook carrier landing impact load measuring device according to claim 1, wherein the rotary flywheel (9) comprises a flywheel shaft (92), a rotary wheel (93) is fixedly connected to the middle of the flywheel shaft (92), a plurality of embedded rods (94) are arranged on the outer side of the rotary wheel (93), flywheel baffles (95) are respectively arranged on the front side and the rear side of the rotary wheel (93), the bottom of each flywheel baffle (95) is fixedly connected with the experimental base (2), a flywheel motor (96) is arranged at the front end of the flywheel shaft (92), and an output shaft of the flywheel motor (96) is in transmission connection with the flywheel shaft (92).
4. A ship-borne aircraft arresting hook carrier impact load measuring device as claimed in claim 3, wherein the type force sensor (91) comprises a type shell (911), a three-way force sensor (912) is connected to the interior of the type shell (911), a clamping groove (913) is respectively formed in the left side and the right side of the three-way force sensor (912), and the clamping groove (913) is clamped with the clamping rod (94).
5. The ship-based aircraft arresting hook carrier landing impact load measuring device according to claim 1, wherein each group of guide devices (41) comprises two guide wheels (42), the two guide wheels (42) are respectively connected with the outer walls of the upper side and the lower side of the hanging basket (4) in a rotating mode, the outer sides of the guide wheels (42) are in sliding connection with the inner wall of the experiment bench (1), and hanging rings (45) used for being connected with connecting pieces (39) are fixedly connected to the top of the hanging basket (4).
6. The ship-based aircraft arresting hook landing impact load measuring device according to claim 5, wherein the tail end of the steel rope (37) is fixedly connected to the right side of the experiment bench (1), the top of the experiment bench (1) is provided with a lifting hole (11), the left side and the right side of the lifting hole (11) are respectively provided with a fixed pulley (38), the bottom of the fixed pulley (38) is fixedly connected with the top of the experiment bench (1), the two ends of the steel rope (37) are respectively wound on the two fixed pulleys (38), the middle part of the steel rope (37) falls into the lifting hole (11), the connecting piece (39) comprises a pulley shell (391), a movable pulley (392) is rotatably connected to the inside of the pulley shell (391), the steel rope (37) bypasses the lower part of the movable pulley (392), a connecting ring (393) is arranged below the pulley shell (391), and the connecting ring (393) is connected with the hanging ring (45).
7. The ship-based aircraft arresting hook carrier landing impact load measuring device according to claim 1, wherein the arresting hook (6) comprises a connecting block (61), a fixed rod (62) is arranged below the connecting block (61), a rotating rod (63) is hinged on the fixed rod (62), and a hook head (64) is fixedly connected below the rotating rod (63).
8. The ship-based aircraft arresting hook ship landing impact load measuring device according to claim 1, wherein the blocking device (21) comprises a blocking plate (211), the blocking plate (211) is slidably connected with the upper right side of the experiment base (2), an actuator (212) is fixedly connected to the right side of the blocking plate (211), the bottom of the actuator (212) is fixedly connected with the experiment base (2), and the actuator (212) is electrically connected with the PLC controller (12).
9. The ship-based aircraft arresting hook ship landing impact load measuring device according to claim 1, wherein the locking mechanism (36) comprises a hinging seat (361), a locking hook (362) is hinged to the hinging seat (361), the left side of the locking hook (362) is abutted to the locking disc (34), an electric cylinder II (363) is arranged on the right side of the locking hook (362), the bottom of the electric cylinder II (363) is fixedly connected with the top of the experiment bench (1), the telescopic end of the electric cylinder II (363) is clamped with the right end of the locking hook (362), and the electric cylinder II (363) is electrically connected with the PLC (12).
10. A method for measuring the impact load of a carrier-based aircraft arresting hook landing, based on the device for measuring the impact load of a carrier-based aircraft arresting hook landing as claimed in any one of claims 1 to 9, comprising the following steps:
s1, connecting the lower end of the connecting piece (39) with the top of the hanging basket (4), controlling a rope winding motor (353) to start through the PLC (12), winding a steel rope (37) on a rotating shaft (32) after the rope winding motor (353) is started, further lifting the hanging basket (4), adding a balancing weight (44) into a balancing weight chamber (43) to increase the load on the hanging basket (4), and increasing the impact force of a blocking hook (6) on a rotating flywheel (9);
s2, after lifting the hanging basket (4), the locking mechanism (36) is clamped with the locking disc (34), the PLC (12) controls the rope winding motor (353) to stop, the PLC (12) controls the rotary flywheel (9) to rotate, then the PLC (12) controls the locking mechanism (36) to unlock, the hanging basket (4) falls under the action of gravity, the arresting hook (6) and the aircraft tire (56) respectively smash to a type force sensor (91) and a three-way force measuring platform (7) on the rotary flywheel (9), and then the arresting hook (6) is sprung under the reaction force of the type force sensor (91);
and S3, after the type force sensor (91) detects the impact force of the blocking hook (6), the PLC (12) controls the stopper (21) to start, and after the stopper (21) is started, the sprung blocking hook (6) falls above the stopper (21).
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