CN116929819A - Device and method for testing protrusion of landing gear of carrier-based aircraft - Google Patents

Device and method for testing protrusion of landing gear of carrier-based aircraft Download PDF

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Publication number
CN116929819A
CN116929819A CN202311200200.7A CN202311200200A CN116929819A CN 116929819 A CN116929819 A CN 116929819A CN 202311200200 A CN202311200200 A CN 202311200200A CN 116929819 A CN116929819 A CN 116929819A
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China
Prior art keywords
shell
lifting
accommodating
main body
constraint
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CN202311200200.7A
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Chinese (zh)
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CN116929819B (en
Inventor
白春玉
王彬文
张志敏
胡锐
陈熠
李霄
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M99/00—Subject matter not provided for in other groups of this subclass
    • G01M99/008—Subject matter not provided for in other groups of this subclass by doing functionality tests
    • 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
    • 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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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The invention discloses a ship-borne aircraft landing gear protrusion test device and a method, wherein the device comprises a main body supporting structure, a load applying mechanism arranged on the main body supporting structure and a ship-borne lifting mechanism connected with the load applying mechanism; the main body supporting structure comprises a main body supporting base, and a plurality of main body supporting upright posts extending along the vertical direction are fixedly arranged at the top of the main body supporting base; the plurality of main body supporting upright posts are connected with a main body supporting accommodating shell with a downward opening, the load applying mechanism comprises a load applying shell which is connected in the main body supporting accommodating shell in a sliding fit manner, and the inner side of the load applying shell is connected with a lifting mechanism accommodating shell in a sliding fit manner; according to the invention, the load applying shell is driven to move along the vertical direction, so that the vertical load can be rapidly applied to the nose landing gear of the aircraft, and the ship-based aircraft landing gear protrusion test with different load requirements can be effectively adapted.

Description

Device and method for testing protrusion of landing gear of carrier-based aircraft
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a ship-based aircraft landing gear protrusion test device and method.
Background
When the carrier-based aircraft catapults and takes off, the catapulting rod is tensioned. When the catapult-assisted take-off speed is reached, the traction force is suddenly unloaded, so that the aircraft is released, the energy stored in the landing gear strut buffer and the tire is released, the nose landing gear is protruded, the aircraft is quickly lifted, and the deck edge obtains a sufficient pitch angle. If the ejection height is too small, the wing lift is insufficient, and if the ejection height is too large, the aircraft may stall or take off failure. Thus, a protrusion test of the nose landing gear of the carrier-based aircraft is required.
At present, the related technology and the device for the nose landing gear protrusion test of the carrier-based aircraft are less researched.
Disclosure of Invention
The invention aims to provide a device and a method for testing the protrusion of a landing gear of a carrier-based aircraft, which can be used for carrying out quick vertical load loading and release on the landing gear of the aircraft, simulating the protrusion process, obtaining the impact dynamic response of the landing gear, and providing test basis for the development of the landing gear of the carrier-based aircraft.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the carrier-based aircraft landing gear protrusion test device comprises a main body supporting structure, a load applying mechanism arranged on the main body supporting structure and a carrier-based lifting mechanism connected with the load applying mechanism;
the main body supporting structure comprises a main body supporting base, a plurality of main body supporting upright posts extending along the vertical direction are fixedly arranged at the top of the main body supporting base, and a main body supporting top cover is fixedly arranged at the top of the main body supporting upright posts;
the main body supporting and accommodating shell with a downward opening is connected to the main body supporting upright posts, a plurality of supporting and restraining ear plates are fixedly arranged on the outer side of the main body supporting and accommodating shell, and each supporting and restraining ear plate is provided with a supporting and restraining hole which is vertically communicated with the corresponding main body supporting upright post in a one-to-one corresponding sliding fit manner;
The top of the main body supporting and accommodating shell is provided with an accommodating shell through hole which is vertically communicated;
the load applying mechanism comprises a load applying shell which is connected in a main body supporting and accommodating shell in a sliding fit manner, the load applying shell is of a circular ring-shaped hollow shell structure, a plurality of vertically penetrating loading driving rod through holes are formed in the top of the load applying shell, a plurality of loading driving matching rods extending in the vertical direction are fixedly arranged at the top of the main body supporting and accommodating shell, the loading driving matching rods penetrate through the loading driving rod through holes and extend into the load applying shell, a loading driving ring is connected in the load applying shell in a rotating fit manner, a loading driving ring thread transmission sleeve is arranged on the loading driving matching rods, and the loading driving ring is driven by a servo motor to rotate around a vertical axis;
the airborne landing gear comprises a landing gear accommodating shell connected to the inner side of the load applying shell in a sliding fit manner, and a landing locking release mechanism arranged on the landing gear accommodating shell;
the main body support base top is fixedly provided with a force measuring platform, and the lower end of the lifting mechanism accommodating shell is fixedly provided with an aircraft nose landing gear.
Preferably, the supporting constraint lug plate is connected with the main body supporting upright post through a lifting driving mechanism, the lifting driving mechanism comprises a lifting driving ring which is connected in a rotating fit manner in the supporting constraint hole, the main body supporting upright post is a ball screw, and the lifting driving ring is in transmission connection with the main body supporting upright post in a transmission manner of the ball screw;
The periphery of the main body supporting upright post is provided with a plurality of longitudinal restraint rods parallel to the main body supporting upright post, the upper ends of the longitudinal restraint rods are fixedly connected with the main body supporting top cover, the lower ends of the longitudinal restraint rods are fixedly connected with the main body supporting top cover and the main body supporting base, a plurality of longitudinal restraint holes are formed in the supporting restraint ear plate, and the longitudinal restraint rods are in one-to-one correspondence with the longitudinal restraint holes for sliding fit connection.
Description: the lifting driving mechanism is convenient for controlling and adjusting the position height of the whole main body supporting and accommodating shell along the vertical direction.
Preferably, the lifting mechanism accommodating shell is a cylindrical hollow shell, the outer side wall of the lifting mechanism accommodating shell is provided with a plurality of lifting constraint sliding grooves extending along the vertical direction, the inner side wall of the load applying shell is fixedly provided with a plurality of lifting constraint sliding rails extending along the vertical direction, and the lifting constraint sliding rails are in sliding fit connection with the lifting constraint sliding grooves in a one-to-one correspondence manner;
the lifting locking release mechanism is arranged in the lifting constraint sliding groove, a locking mechanism accommodating hole is formed in the inner side wall of the lifting constraint sliding groove, the locking mechanism accommodating hole extends along the radial direction of the lifting mechanism accommodating shell, the lifting locking release mechanism comprises a locking release driving block which is in sliding fit in the locking mechanism accommodating hole, one end, close to the lifting constraint sliding rail, of the locking release driving block is fixedly provided with a locking wedge block, and a plurality of locking fit holes are formed in the side face of the lifting constraint sliding rail;
A locking driving telescopic rod is arranged in the locking mechanism accommodating hole, the locking driving telescopic rod is an electric control telescopic rod, the end part of an outer rod of the locking driving telescopic rod is fixedly connected with the inner end part of the locking mechanism accommodating hole, and the end part of an inner rod of the locking driving telescopic rod is fixedly connected with the locking release driving block;
the lifting constraint slide rail is connected with the inner side wall of the load application shell through a slide rail longitudinal fine adjustment mechanism, the slide rail longitudinal fine adjustment mechanism comprises a fine adjustment mechanism support shell fixed on the inner side wall of the load application shell, the fine adjustment mechanism support shell is a columnar shell extending along the vertical direction, a plurality of fixed communication grooves which are communicated inside and outside and extend along the vertical direction are formed in the side surface of the fine adjustment mechanism support shell, a plurality of longitudinal fine adjustment support columns are arranged in the fine adjustment mechanism support shell in a sliding fit manner, the longitudinal fine adjustment support columns are fixedly connected with the lifting constraint slide rail through a connecting plate, and the connecting plate penetrates through the fixed communication grooves to be fixedly connected with the lifting constraint slide rail;
the vertical fine tuning support columns are provided with fine tuning threaded holes which are vertically communicated, fine tuning threaded driving rods extending along the vertical direction are arranged in common threaded transmission of the fine tuning threaded holes on the plurality of vertical fine tuning support columns, and fine tuning driving motors used for driving the fine tuning threaded driving rods to rotate are fixedly arranged in fine tuning mechanism support shells.
Description: fine-tuning the position of the landing constraining slide rail in the vertical direction, so as to more accurately control the vertical load applied to the nose landing gear by the landing gear accommodating shell.
Preferably, the load applying shell is provided with an orientation constraint mechanism, the top of the load applying shell is provided with a plurality of vertically penetrating orientation sliding constraint holes, the orientation constraint mechanism comprises orientation constraint cylinders which are positioned at each orientation sliding constraint hole and fixed at the top in the load applying shell, the openings of the orientation constraint cylinders are upward, the top in the main body supporting and accommodating shell is fixedly provided with a plurality of orientation constraint columns extending along the vertical direction, and the orientation constraint columns are in one-to-one corresponding sliding fit connection with the orientation constraint cylinders.
Description: the directional constraining mechanism is capable of constraining the load applying housing to maintain a more stable posture during the upward and downward movements.
Preferably, the load applying shell is internally provided with a carrier-based vibration simulation mechanism, the carrier-based vibration simulation mechanism comprises a vibration simulation accommodating column fixed in the load applying shell, the vibration simulation accommodating column is a hollow cylindrical shell, and the vibration simulation accommodating column extends along the vertical direction and is fixed in the load applying shell;
Two electromagnetic driving coils are fixedly arranged in the vibration simulation accommodating column, two permanent magnet column constraint rings are fixedly arranged between the two electromagnetic driving coils in the vibration simulation accommodating column, and permanent magnet driving columns are arranged between the two permanent magnet column constraint rings in a sliding fit manner;
one end of each of the two permanent magnet column constraint rings, which is close to each other, is fixedly provided with a rubber damping ring;
the lower end of the vibration simulation accommodating column is connected with the deflection supporting sliding block through a first damping connecting rod, the first damping connecting rod is an electromagnetic telescopic rod with adjustable damping, the end part of an outer rod of the first damping connecting rod is connected with the lower end of the vibration simulation accommodating column in a ball hinge connection mode, and the end part of an inner rod of the first damping connecting rod is connected with the deflection supporting sliding block in a ball hinge connection mode;
the upper end of the vibration simulation accommodating column is connected with the inner top of the load applying shell through a second damping connecting rod, the second damping connecting rod is an electromagnetic telescopic rod with adjustable damping, the end part of an outer rod of the second damping connecting rod is connected with the upper end of the vibration simulation accommodating column in a ball hinge connection mode, and the end part of an inner rod of the second damping connecting rod is connected with the inner top of the load applying shell in a ball hinge connection mode.
Description: environmental vibration in a take-off environment of the carrier-based aircraft is simulated through the carrier-based vibration simulation mechanism, deflection of the vibration simulation accommodating column can be controlled, and multiple vibration environments can be simulated through combination of the vibration simulation accommodating columns.
Preferably, the load is exerted the inboard supplementary orientation mechanism that rises and falls that is equipped with of casing, and the supplementary orientation mechanism that rises and falls is including fixing and exerting the inboard supplementary orientation backup pad that just is annular at the load, and supplementary orientation backup pad downside is fixed to be equipped with many supplementary orientation restraint posts that extend along vertical direction, has a plurality of supplementary orientation restraint holes that link up vertically on the mechanism accommodation shell, and a plurality of supplementary orientation restraint posts carry out slip fit connection with a plurality of supplementary orientation restraint holes one-to-one.
Description: the nose landing gear of the aircraft protrudes to drive the whole landing gear accommodating shell to move upwards, and the auxiliary directional restraining columns are connected with the auxiliary directional restraining holes in a one-to-one correspondence mode in a sliding fit mode, so that a stable restraining effect is achieved on the landing gear accommodating shell in the process of moving upwards along the axis of the load applying shell.
Preferably, the top of the main body supporting and accommodating shell is provided with a lifting and accommodating shell reset mechanism, the lifting and accommodating shell reset mechanism comprises a reset support column which is fixed at the top of the lifting and accommodating shell and extends along the vertical direction, and a reset constraint supporting cylinder with a downward opening is surrounded on the outer side of the reset support column;
The inner side wall of the reset constraint supporting cylinder is connected with a plurality of reset constraint fixing plates, the reset constraint fixing plates are connected with the inner side wall of the reset constraint supporting cylinder through a reset constraint connecting rod, and two ends of the reset constraint connecting rod are respectively connected with the reset constraint fixing plates and the inner side wall of the reset constraint supporting cylinder in a fixed hinge connection mode;
the outer side wall of the reset constraint supporting cylinder is fixedly provided with a fixed plate driving rod accommodating cylinder, the axis of the fixed plate driving rod accommodating cylinder extends along the radial direction of the reset constraint supporting cylinder, the side edge of the reset constraint supporting cylinder is provided with a driving rod communication hole communicated with the inside of the fixed plate driving rod accommodating cylinder, the fixed plate driving rod accommodating cylinder is internally provided with a fixed plate driving rod, the fixed plate driving rod is an electric control telescopic rod, the end part of an inner rod of the fixed plate driving rod passes through the driving rod communication hole and is connected with the reset constraint connecting rod in a fixed hinge connection mode, and the end part of an outer rod of the fixed plate driving rod is connected with the inner end part of the fixed plate driving rod accommodating cylinder in a fixed hinge connection mode;
the top of the main body supporting and accommodating shell is fixedly provided with a plurality of reset lifting fixed barrels with upward openings, a reset lifting driving barrel with downward openings is arranged in the reset lifting fixed barrels in a sliding fit manner, a reset lifting driving rod is arranged in the reset lifting fixed barrels, the reset lifting driving rod is an electric control telescopic rod, the outer rod end part of the reset lifting driving rod is fixedly connected with the inner bottom part of the reset lifting fixed barrel, and the inner rod end part of the reset lifting driving rod is fixedly connected with the inner top part of the reset lifting driving barrel;
The top parts of the resetting lifting driving cylinders are connected with a resetting mechanism supporting plate, and the resetting mechanism supporting plate is fixedly connected with the top part of the resetting constraint supporting cylinder.
Description: utilize the landing to hold shell canceling release mechanical system to wholly lift up and down the mechanism and hold the shell and reset the locking again, hold the fixed constraint of shell to wholly lift up and down the mechanism simultaneously, also avoid the landing to hold the shell and fall back and strike force measuring platform.
Preferably, the lifting mechanism holds the shell top and is equipped with lift simulation mechanism, lift simulation mechanism is including fixing at lifting mechanism holds the shell top and along the lift simulation actuating cylinder that vertical direction extends, lift simulation actuating cylinder lateral wall is fixed to be equipped with a plurality of lift actuating blades, lift simulation actuating cylinder outside is encircleed and is equipped with the lift simulation restraint section of thick bamboo of opening down, lift simulation restraint section of thick bamboo top is fixed to be equipped with the lift drive exhaust tube rather than inside intercommunication, lift simulation restraint section of thick bamboo is fixed continuous with the load application casing inside wall.
Description: the lift simulation mechanism is used for providing vertical pulling force for the lifting mechanism accommodating shell, simulating the lift force in the aircraft take-off process, and the air flow velocity in the lift force simulation constraint cylinder is controlled to adjust the magnitude of the simulated lift force.
Preferably, the outer side surface of the lifting mechanism accommodating shell is provided with a plurality of counterweight accommodating holes extending along the radial direction of the lifting mechanism accommodating shell, resident counterweight columns are arranged in the counterweight accommodating holes in a sliding fit manner, counterweight adjusting threaded holes penetrating along the axes of the counterweight accommodating holes are formed in the resident counterweight columns, counterweight adjusting threaded rods are arranged in the counterweight adjusting threaded holes in a threaded transmission fit manner, and counterweight adjusting motors used for driving the counterweight adjusting threaded rods to rotate are fixedly arranged in the counterweight accommodating holes;
the counterweight accommodating hole is provided with a plurality of additional counterweight columns in a sliding fit manner, the additional counterweight columns are provided with threaded holes which are communicated along the axis of the counterweight accommodating hole, and the threaded holes of the additional counterweight columns are in threaded rotation connection with the counterweight adjusting threaded rod.
Description: the number of the additional weight columns is increased or reduced to simulate various self-weight load conditions, and the positions of the resident weight columns and the additional weight columns in the weight accommodating holes are adjusted to adjust the load gravity center balance position.
Preferably, the method for carrying out the carrier-based aircraft landing gear protrusion test by using the carrier-based aircraft landing gear protrusion test equipment comprises the following steps:
s1, stably mounting an aircraft nose landing gear:
the aircraft nose landing gear is arranged at the lower end of the landing gear accommodating shell, and the height position of the main body supporting accommodating shell is adjusted to enable the tire static pressure of the aircraft nose landing gear to be at the top of the force measuring platform;
S2, applying a vertical load to the nose landing gear of the aircraft:
the servo motor drives the loading driving ring to rotate, so that the loading driving ring moves downwards relative to the loading driving matching rod, and the loading driving ring further drives the whole load applying shell to move downwards along the axis of the main body supporting and accommodating shell;
at this time, the whole lifting mechanism accommodating case is relatively fixed in the load applying case by using the lifting lock release mechanism;
the load applying shell drives the lifting mechanism accommodating shell to move downwards together to apply a preset vertical load to the nose landing gear of the aircraft;
s3, unlocking the landing gear accommodating shell by the landing locking release mechanism, and completing the protruding process of the nose landing gear of the airplane:
the lifting locking release mechanism is used for unlocking the lifting mechanism accommodating shell, so that the lifting mechanism accommodating shell can freely slide in the load applying shell;
the whole lifting mechanism accommodating shell simulates the self-weight load of the aircraft, and after the whole lifting mechanism accommodating shell is separated from the inside of the load applying shell, the front landing gear of the aircraft protrudes to drive the whole lifting mechanism accommodating shell to move upwards along the axis of the load applying shell;
and meanwhile, the force measuring platform measures and records the stress condition of the nose landing gear of the aircraft.
Compared with the prior art, the invention has the beneficial effects that:
1. According to the invention, the load applying shell is driven to move along the vertical direction, so that the vertical load can be rapidly applied to the nose landing gear of the aircraft, and the ship-based aircraft landing gear protrusion test with different load requirements can be effectively adapted;
2. according to the invention, the number of the additional weight columns is increased or reduced to simulate various self-weight load conditions, and the positions of the resident weight columns and the additional weight columns in the weight accommodating holes are adjusted to adjust the gravity center balance position of the load;
3. the invention uses the lifting accommodating shell resetting mechanism to reset and lock the whole lifting mechanism accommodating shell, thereby facilitating the next test;
4. the device can also be used for the landing test of the nose landing gear of the carrier-based aircraft and the nose landing gear of the land-based aircraft;
5. the invention simulates the environmental vibration of the carrier-based aircraft in the take-off environment through the carrier-based vibration simulation mechanism: the vibration simulation accommodating column can be controlled to deflect, and a plurality of vibration environments can be simulated by combining the vibration simulation accommodating columns;
6. according to the invention, the lift force simulation mechanism is utilized to provide vertical pulling force for the lifting mechanism accommodating shell, the lift force in the aircraft take-off process is simulated, and the air flow velocity in the lift force simulation constraint cylinder is controlled to adjust the magnitude of the simulated lift force.
Drawings
FIG. 1 is a front view of a carrier-based aircraft landing gear protrusion test apparatus of the present invention;
FIG. 2 is a top view of FIG. 1;
FIG. 3 is a schematic structural view of the directional constraining mechanism;
FIG. 4 is a schematic diagram of a structure of a ship-borne vibration simulation mechanism;
FIG. 5 is a schematic view of the structure of the lift lock release mechanism;
FIG. 6 is a schematic view of a longitudinal fine adjustment mechanism of the slide rail;
FIG. 7 is a schematic view of the structure of the lift-and-fall housing reset mechanism;
FIG. 8 is a schematic structural view of a lift simulation mechanism;
FIG. 9 is a schematic view of the construction of a weight receiving port;
FIG. 10 is a top view of the lift mechanism containment case;
FIG. 11 is a flow chart of a method of landing gear protrusion testing for a carrier-based aircraft.
In the drawing the view of the figure, 10-main body supporting structure, 11-main body supporting base, 12-main body supporting upright post, 121-longitudinal restraining bar, 13-main body supporting top cover, 14-main body accommodating case, 141-accommodating case through hole, 15-supporting restraining ear plate, 151-restraining hole, 152-longitudinal restraining hole, 16-lifting driving mechanism, 161-lifting driving ring, 20-load applying mechanism, 21-load applying case, 211-loading driving rod through hole, 221-loading driving matching rod, 222-loading driving ring, 23-orientation restraining mechanism, 231-orientation sliding restraining hole, 232-orientation restraining cylinder, 233-orientation restraining column, 24-ship vibration simulating mechanism, 241-vibration simulating accommodating column, 242-electromagnetic driving coil 243-permanent magnet column restraining rings, 244-permanent magnet driving columns, 245-rubber damping rings, 251-deflection support sliding rails, 252-deflection support sliding blocks, 253-first damping connecting rods, 254-second damping connecting rods, 30-onboard lifting mechanisms, 31-lifting mechanism accommodating shells, 321-lifting restraint sliding grooves, 322-lifting restraint sliding rails, 33-lifting locking release mechanisms, 330-locking mechanism accommodating holes, 331-locking release driving blocks, 332-locking wedge blocks, 333-locking matching holes, 334-locking driving telescopic rods, 34-sliding rail longitudinal fine adjustment mechanisms, 341-fine adjustment mechanism supporting shells, 342-fixed communication grooves, 343-longitudinal fine adjustment supporting columns, 344-fine adjustment threaded holes, 345-fine adjustment threaded driving rods, 346-fine adjustment driving motor, 35-lifting auxiliary orientation mechanism, 351-auxiliary orientation supporting plate, 352-auxiliary orientation restraining column, 353-auxiliary orientation restraining hole, 36-lifting accommodation shell resetting mechanism, 361-resetting supporting column, 362-resetting restraint supporting cylinder, 363-resetting restraint fixing plate, 364-resetting restraint connecting rod, 365-fixing plate driving rod accommodation cylinder, 366-driving rod communication hole, 367-fixing plate driving rod, 371-resetting lifting fixing cylinder, 372-resetting lifting driving cylinder, 373-resetting lifting driving rod, 38-lifting simulation mechanism, 381-lifting simulation driving column, 382-lifting driving blade, 383-lifting simulation restraining cylinder, 384-lifting driving exhaust tube, 391-counterweight accommodation hole, 392-resident counterweight column, 393-counterweight adjusting threaded hole, 394-counterweight adjusting threaded rod, 395-counterweight adjusting motor, 396-external counterweight column and 40-force measuring platform.
Detailed Description
The present invention will be described in detail with reference to fig. 1 to 11, and for convenience of description, the following orientations will be defined: the vertical, horizontal, front, and rear directions described below are identical to the vertical, horizontal, front, and rear directions of the respective front views or the projection relationship of the structural schematic diagram itself.
Example 1: the carrier-based aircraft landing gear protrusion test equipment comprises a main body supporting structure 10, a load applying mechanism 20 arranged on the main body supporting structure 10, and an onboard lifting mechanism 30 connected with the load applying mechanism 20, wherein the load applying mechanism 20 comprises a lifting mechanism;
the main body supporting structure 10 comprises a main body supporting base 11, a plurality of main body supporting upright posts 12 extending along the vertical direction are fixedly arranged at the top of the main body supporting base 11, and a main body supporting top cover 13 is fixedly arranged at the top of the main body supporting upright posts 12;
the main body support upright posts 12 are commonly connected with a main body support accommodating shell 14 with a downward opening, a plurality of support constraint ear plates 15 are fixedly arranged on the outer side of the main body support accommodating shell 14, the support constraint ear plates 15 are provided with support constraint holes 151 which are vertically communicated, and the support constraint holes 151 are in one-to-one corresponding sliding fit connection with the main body support upright posts 12;
the top of the main body supporting and accommodating shell 14 is provided with an accommodating shell through hole 141 which is vertically communicated;
As shown in fig. 2, the supporting and restraining ear plate 15 is connected with the main body supporting upright post 12 through a lifting driving mechanism 16, the lifting driving mechanism 16 comprises a lifting driving ring 161 which is connected in a rotating fit manner in the supporting and restraining hole 151, the main body supporting upright post 12 is a ball screw, and the lifting driving ring 161 is in transmission connection with the main body supporting upright post 12 in a transmission manner of the ball screw;
the periphery of the main body supporting upright post 12 is provided with a plurality of longitudinal restraint rods 121 parallel to the main body supporting upright post, the upper ends of the longitudinal restraint rods 121 are fixedly connected with the main body supporting top cover 13, the lower ends of the longitudinal restraint rods 121 are fixedly connected with the main body supporting top cover 13 and the main body supporting base 11, the supporting restraint ear plates 15 are provided with a plurality of longitudinal restraint holes 152, and the longitudinal restraint rods 121 are in one-to-one corresponding sliding fit connection with the longitudinal restraint holes 152;
the load applying mechanism 20 comprises a load applying shell 21 which is connected in a sliding fit manner in the main body supporting and accommodating shell 14, the load applying shell 21 is of a circular hollow shell structure, a plurality of vertically penetrating load driving rod through holes 211 are formed in the top of the load applying shell 21, a plurality of vertically extending load driving matching rods 221 are fixedly arranged at the top of the main body supporting and accommodating shell 14, the load driving matching rods 221 penetrate through the load driving rod through holes 211 and extend into the load applying shell 21, a load driving ring 222 is connected in a rotating fit manner in the load applying shell 21, the load driving ring 222 is sleeved on the load driving matching rods 221 in a threaded transmission manner, and the load driving ring 222 is driven by a servo motor to rotate around a vertical axis; as shown in fig. 3, the load applying housing 21 is provided with an orientation constraint mechanism 23, the top of the load applying housing 21 is provided with a plurality of vertically penetrating orientation sliding constraint holes 231, the orientation constraint mechanism 23 comprises an orientation constraint cylinder 232 which is positioned at each orientation sliding constraint hole 231 and is fixed at the inner top of the load applying housing 21, the orientation constraint cylinder 232 is opened upwards, the inner top of the main body support accommodating housing 14 is fixedly provided with a plurality of orientation constraint columns 233 which extend along the vertical direction, and the orientation constraint columns 233 are in one-to-one corresponding sliding fit connection with the orientation constraint cylinders 232;
As shown in fig. 1, the on-board landing gear 30 includes a landing gear housing case 31 slidably fitted inside the load applying case 21 and a landing lock release mechanism 33 provided on the landing gear housing case 31; the lifting mechanism accommodating shell 31 is a cylindrical hollow shell, the outer side wall of the lifting mechanism accommodating shell 31 is provided with a plurality of lifting constraint sliding grooves 321 extending along the vertical direction, the inner side wall of the load applying shell 21 is fixedly provided with a plurality of lifting constraint sliding rails 322 extending along the vertical direction, and the lifting constraint sliding rails 322 are in sliding fit connection with the lifting constraint sliding grooves 321 in a one-to-one correspondence manner;
the landing locking release mechanism 33 is arranged in the landing constraint slide way 321, as shown in fig. 5, a locking mechanism accommodating hole 330 is formed on the inner side wall of the landing constraint slide way 321, the locking mechanism accommodating hole 330 extends along the radial direction of the landing mechanism accommodating shell 31, the landing locking release mechanism 33 comprises a locking release driving block 331 which is in sliding fit in the locking mechanism accommodating hole 330, one end of the locking release driving block 331, which is close to the landing constraint slide way 322, is fixedly provided with a locking wedge block 332, and a plurality of locking fit holes 333 are formed on the side surface of the landing constraint slide way 322;
a locking driving telescopic rod 334 is arranged in the locking mechanism accommodating hole 330, the locking driving telescopic rod 334 is an electric control telescopic rod, the outer rod end part of the locking driving telescopic rod 334 is fixedly connected with the inner end part of the locking mechanism accommodating hole 330, and the inner rod end part of the locking driving telescopic rod 334 is fixedly connected with the locking release driving block 331;
As shown in fig. 1, a lifting auxiliary orientation mechanism 35 is arranged on the inner side of the load application shell 21, the lifting auxiliary orientation mechanism 35 comprises an auxiliary orientation support plate 351 which is fixed on the inner side of the load application shell 21 and is annular, a plurality of auxiliary orientation restraint columns 352 which extend along the vertical direction are fixedly arranged on the lower side of the auxiliary orientation support plate 351, a plurality of auxiliary orientation restraint holes 353 which are vertically penetrated are formed in the lifting mechanism accommodating shell 31, and the auxiliary orientation restraint columns 352 are in one-to-one corresponding sliding fit connection with the auxiliary orientation restraint holes 353;
as shown in fig. 9, the outer side surface of the lifting mechanism accommodating case 31 is provided with a plurality of weight accommodating holes 391 extending along the radial direction of the lifting mechanism accommodating case 31, a resident weight column 392 is slidably matched in the weight accommodating holes 391, a weight adjusting threaded hole 393 penetrating along the axis of the weight accommodating holes 391 is arranged on the resident weight column 392, a weight adjusting threaded rod 394 is matched in a threaded transmission manner in the weight adjusting threaded hole 393, a weight adjusting motor 395 for driving the weight adjusting threaded rod 394 to rotate is fixedly arranged in the weight accommodating holes 391, and the weight adjusting motor 395 is a servo motor;
a plurality of additional weight columns 396 are arranged in sliding fit in the weight accommodating hole 391, threaded holes penetrating along the axis of the weight accommodating hole 391 are formed in the additional weight columns 396, and the threaded holes in the additional weight columns 396 are in threaded rotary connection with the weight adjusting threaded rods 394;
As shown in fig. 1, a force measuring platform 40 is fixedly arranged at the top of the main body supporting base 11, and an aircraft nose landing gear is fixed at the lower end of the landing gear accommodating shell 31;
the force platform 40 is a three-way force platform of the prior art.
Example 2: the method for performing the carrier-based aircraft landing gear protrusion test by using the carrier-based aircraft landing gear protrusion test device of the above embodiment 1, as shown in fig. 11, includes the following steps:
s1, stably mounting an aircraft nose landing gear:
mounting the nose landing gear of the aircraft at the lower end of the landing gear accommodating shell 31, and adjusting the height position of the main body supporting accommodating shell 14 to enable the tire static pressure of the nose landing gear of the aircraft to be on the top of the force measuring platform 40;
s2, applying a vertical load to the nose landing gear of the aircraft:
the servo motor drives the loading drive ring 222 to rotate, so that the loading drive ring 222 moves downwards relative to the loading drive matching rod 221, and the loading drive ring 222 further drives the whole load applying shell 21 to move downwards along the axis of the main body supporting accommodating shell 14;
at this time, the lock wedge 332 is inserted and locked in the lock engagement hole 333, so that the entire lifting mechanism housing case 31 is relatively fixed in the load applying case 21;
the load applying housing 21 drives the landing gear accommodating housing 31 to move downward together to apply a predetermined vertical load to the nose landing gear of the aircraft;
S3, the lifting locking release mechanism 33 unlocks the lifting mechanism accommodating shell 31, and the nose landing gear of the aircraft completes the protruding process:
the inner rod of the locking driving telescopic rod 334 is retracted to drive the locking release driving block 331 to move in a direction away from the lifting constraint slide rail 322, and the locking release driving block 331 drives the locking wedge block 332 to be pulled out from the locking matching hole 333;
the whole lifting mechanism accommodating shell 31 simulates the dead weight load of the aircraft, after the whole lifting mechanism accommodating shell 31 is separated from the inside of the load applying shell 21 and fixed, the nose landing gear of the aircraft protrudes to drive the whole lifting mechanism accommodating shell 31 to move upwards, and under the restraint of the lifting restraint sliding rail 322 and the lifting restraint sliding chute 321, the lifting mechanism accommodating shell 31 moves upwards along the axis of the load applying shell 21;
while the force platform 40 performs measurement and recording of the force conditions of the nose landing gear of the aircraft.
Example 3: the present embodiment is different from embodiment 1 in that, as shown in fig. 1, a lifting-and-lowering housing-housing reset mechanism 36 is provided on the top of the main body supporting housing 14, and as shown in fig. 7, the lifting-and-lowering housing-reset mechanism 36 includes a vertically extending reset support column 361 fixed on the top of the lifting-and-lowering mechanism housing 31, and a reset-restraining-support cylinder 362 with a downward opening is surrounded on the outside of the reset support column 361;
The inner side wall of the reset constraint supporting cylinder 362 is connected with a plurality of reset constraint fixing plates 363, the reset constraint fixing plates 363 are connected with the inner side wall of the reset constraint supporting cylinder 362 through a reset constraint connecting rod 364, and two ends of the reset constraint connecting rod 364 are respectively connected with the reset constraint fixing plates 363 and the inner side wall of the reset constraint supporting cylinder 362 in a fixed hinge connection mode; the outer side wall of the reset constraint supporting cylinder 362 is fixedly provided with a fixed plate driving rod accommodating cylinder 365, the axis of the fixed plate driving rod accommodating cylinder 365 extends along the radial direction of the reset constraint supporting cylinder 362, the side edge of the reset constraint supporting cylinder 362 is provided with a driving rod communication hole 366 communicated with the inside of the fixed plate driving rod accommodating cylinder 365, the fixed plate driving rod accommodating cylinder 365 is internally provided with a fixed plate driving rod 367, the fixed plate driving rod 367 is an electric control telescopic rod, the inner rod end part of the fixed plate driving rod 367 passes through the driving rod communication hole 366 and is connected with the reset constraint connecting rod 364 in a fixed hinge connection mode, and the outer rod end part of the fixed plate driving rod 367 is connected with the inner end part of the fixed plate driving rod accommodating cylinder 365 in a fixed hinge connection mode;
as shown in fig. 1, a plurality of reset lifting fixed cylinders 371 with upward openings are fixedly arranged at the top of the main body supporting and accommodating shell 14, a reset lifting driving cylinder 372 with downward openings is slidably matched in the reset lifting fixed cylinders 371, a reset lifting driving rod 373 is arranged in the reset lifting fixed cylinders 371, the reset lifting driving rod 373 is an electric control telescopic rod, the outer rod end part of the reset lifting driving rod 373 is fixedly connected with the inner bottom part of the reset lifting fixed cylinders 371, and the inner rod end part of the reset lifting driving rod 373 is fixedly connected with the inner top part of the reset lifting driving cylinder 372;
The top parts of the plurality of reset lifting driving cylinders 372 are connected with a reset mechanism supporting plate 37, and the reset mechanism supporting plate 37 is fixedly connected with the top part of the reset constraint supporting cylinder 362.
Example 4: the embodiment describes a method for performing a landing gear protrusion test of a carrier-based aircraft based on the landing gear protrusion test apparatus of embodiment 3, which is different from embodiment 2 in that the method further includes step S4,
s4, resetting and locking the whole lifting mechanism accommodating shell 31:
after the front landing gear of the aircraft protrudes to drive the whole landing gear accommodating shell 31 to move upwards to the upper dead center, the reset support column 361 is clamped and fixed by utilizing the plurality of reset constraint fixing plates 363, so that the whole landing gear accommodating shell 31 is fixedly constrained, and the landing gear accommodating shell 31 is prevented from falling back to strike the force measuring platform 40;
the inner rod of the fixed plate driving rod 367 stretches out to drive the reset constraint link 364 to deflect, and the reset constraint link 364 deflects to drive the reset constraint fixed plate 363 to move towards the axis close to the reset constraint support cylinder 362, so that the reset support columns 361 are clamped and fixed by the reset constraint fixed plates 363;
then, the inner rod of the reset lifting driving rod 373 retracts to drive the reset lifting driving cylinder 372 to move downwards along the axis of the reset lifting fixing cylinder 371, the reset lifting driving cylinders 372 jointly drive the reset mechanism supporting plate 37 to move downwards, the reset mechanism supporting plate 37 drives the whole lifting mechanism accommodating shell 31 to move downwards through the reset supporting column 361 and the reset constraint supporting cylinder 362 which are relatively fixed, the lifting mechanism accommodating shell 31 is enabled to fall back to the initial position, and the locking wedge block 332 is utilized to insert and lock in the locking matching hole 333, so that the whole lifting mechanism accommodating shell 31 is relatively fixed in the load applying shell 21.
Example 5: the present embodiment is different from embodiment 4 in that, as shown in fig. 1, the lift mechanism housing shell 31 is provided at the top with a lift simulation mechanism 38, and as shown in fig. 8, the lift simulation mechanism 38 includes a lift simulation driving column 381 fixed at the top of the lift mechanism housing shell 31 and extending in the vertical direction, a plurality of lift driving blades 382 are fixedly provided on the outer side wall of the lift simulation driving column 381, a lift simulation restraining cylinder 383 with a downward opening is surrounded on the outer side of the lift simulation driving column 381, a lift driving exhaust tube 384 communicating with the inside of the lift simulation restraining cylinder 383 is fixedly provided at the top of the lift simulation restraining cylinder 383, and the lift simulation restraining cylinder 383 is fixedly connected with the inner side wall of the load applying housing 21.
Example 6: the embodiment describes a method for performing a landing gear protrusion test of a carrier-based aircraft based on the landing gear protrusion test apparatus of embodiment 5, which is different from embodiment 4 in that the method further includes step S5,
s5, providing vertical pulling force for the lifting mechanism accommodating shell 31 by using the lifting force simulation mechanism 38, and simulating lifting force in the aircraft take-off process;
the lift force driving exhaust pipe 384 is connected with the input end of the air extractor through a pipeline, the air in the lift force simulation constraint cylinder 383 is extracted by the air extractor, when the outside air flows into the lift force simulation constraint cylinder 383 from the lower end to supplement the air in the lift force simulation constraint cylinder 383, the air flow impacts the lift force driving blade 382 and drives the lift force simulation driving column 381 to generate a vertical pulling force, and then the vertical pulling force is provided for the lifting mechanism accommodating shell 31, so that the lift force in the aircraft taking-off process is simulated;
The magnitude of the simulated lift force can be adjusted by controlling the air flow rate in the lift force simulation restraining cylinder 383.
Example 7: the difference between this embodiment and embodiment 5 is that, as shown in fig. 6, the lifting and lowering constraining slide rail 322 is connected to the inner side wall of the load applying housing 21 through a slide rail longitudinal fine adjustment mechanism 34, the slide rail longitudinal fine adjustment mechanism 34 includes a fine adjustment mechanism supporting housing 341 fixed on the inner side wall of the load applying housing 21, the fine adjustment mechanism supporting housing 341 is a columnar housing extending along the vertical direction, the side surface of the fine adjustment mechanism supporting housing 341 near the axis of the load applying housing 21 has a plurality of fixed communicating slots 342 penetrating inside and outside and extending along the vertical direction, a plurality of longitudinal fine adjustment supporting columns 343 are slidably fitted in the fine adjustment mechanism supporting housing 341, the longitudinal fine adjustment supporting columns 343 are fixedly connected to the lifting and lowering constraining slide rail 322 through a connecting plate, and the connecting plate passes through the fixed communicating slots 342 and is fixedly connected to the lifting and lowering constraining slide rail 322;
the vertical fine tuning support columns 343 are provided with fine tuning threaded holes 344 which are vertically communicated, fine tuning threaded holes 344 on the plurality of vertical fine tuning support columns 343 are in common threaded transmission and provided with a fine tuning threaded driving rod 345 which extends along the vertical direction, and a fine tuning driving motor 346 for driving the fine tuning threaded driving rod 345 to rotate is fixedly arranged in the fine tuning mechanism support shell 341 and is a servo motor.
Example 8: the embodiment describes a method for performing a landing gear protrusion test of a carrier-based aircraft based on the landing gear protrusion test apparatus of embodiment 7, which is different from embodiment 6 in that the method further includes step S6,
s6, fine adjustment is carried out on the position of the landing restriction sliding rail 322 in the vertical direction by utilizing the sliding rail longitudinal fine adjustment mechanism 34, so that the vertical load applied to the nose landing gear of the aircraft by the landing gear accommodating shell 31 can be controlled more accurately;
the fine adjustment driving motor 346 drives the fine adjustment screw driving rod 345 to rotate, the fine adjustment screw driving rod 345 drives the longitudinal fine adjustment supporting columns 343 to move in the vertical direction in the fine adjustment mechanism supporting shell 341, and the plurality of longitudinal fine adjustment supporting columns 343 jointly drive the lifting constraint sliding rail 322 to move in the vertical direction;
the stroke of the longitudinal fine adjustment support post 343 is larger than the center distance of the adjacent two lock engagement holes 333 in the vertical direction and smaller than twice the center distance of the adjacent two lock engagement holes 333 in the vertical direction.
Example 9: the present embodiment is different from embodiment 7 in that, as shown in fig. 4, a carrier-based vibration simulation mechanism 24 is provided inside the load applying housing 21, the carrier-based vibration simulation mechanism 24 includes a vibration simulation accommodating column 241 fixed inside the load applying housing 21, the vibration simulation accommodating column 241 is a hollow cylindrical housing, and the vibration simulation accommodating column 241 extends in the vertical direction and is fixed inside the load applying housing 21;
Two electromagnetic driving coils 242 are fixedly arranged in the vibration simulation accommodating column 241, two permanent magnet column constraint rings 243 are fixedly arranged between the two electromagnetic driving coils 242 in the vibration simulation accommodating column 241, and permanent magnet driving columns 244 are arranged between the two permanent magnet column constraint rings 243 in a sliding fit manner;
one end of the two permanent magnet column restraining rings 243, which are close to each other, is fixedly provided with a rubber damping ring 245;
the inner bottom of the load applying shell 21 is fixedly provided with a deflection support sliding rail 251, the deflection support sliding rail 251 is provided with a deflection support sliding block 252 in a sliding fit manner, the lower end of the vibration simulation accommodating column 241 is connected with the deflection support sliding block 252 through a first damping connecting rod 253, the first damping connecting rod 253 is an electromagnetic telescopic rod with adjustable damping, the outer rod end of the first damping connecting rod 253 is connected with the lower end of the vibration simulation accommodating column 241 in a ball hinge connection mode, and the inner rod end of the first damping connecting rod 253 is connected with the deflection support sliding block 252 in a ball hinge connection mode;
the upper end of the vibration simulation accommodating column 241 is connected with the inner top of the load applying shell 21 through a second damping connecting rod 254, the second damping connecting rod 254 is an electromagnetic telescopic rod with adjustable damping, the outer rod end of the second damping connecting rod 254 is connected with the upper end of the vibration simulation accommodating column 241 in a ball hinge connection mode, and the inner rod end of the second damping connecting rod 254 is connected with the inner top of the load applying shell 21 in a ball hinge connection mode.
Example 10: the embodiment describes a method for performing a landing gear protrusion test of a carrier-based aircraft based on the landing gear protrusion test apparatus of embodiment 9, which is different from embodiment 8 in that the method further includes step S7,
s7, simulating environmental vibration in a take-off environment of the carrier-based aircraft through the carrier-based vibration simulation mechanism 24:
the two electromagnetic driving coils 242 generate magnetic fields opposite to the permanent magnetic driving columns 244, so that the electromagnetic driving coils 242 repel each other with the permanent magnetic driving columns 244, the permanent magnetic driving columns 244 are restrained between the two electromagnetic driving coils 242, the permanent magnetic driving columns 244 can be driven to move along the axes of the vibration simulation accommodating columns 241 in the vibration simulation accommodating columns 241 by periodically changing the magnetic field intensity generated by the two electromagnetic driving coils 242, vibration generated by the periodic movement of the permanent magnetic driving columns 244 is transmitted to the load applying shell 21 through the vibration simulation accommodating columns 241, the first damping connecting rod 253 and the second damping connecting rod 254, and then the vibration is transmitted to the nose landing gear of the aircraft through the lifting mechanism accommodating shell 31;
the deflection support slide block 252 is driven by a servo motor to move along the deflection support slide rail 251, the deflection support slide block 252 drives the vibration simulation accommodating column 241 to deflect through the first damping connecting rod 253, and the combination of the vibration simulation accommodating columns 241 can simulate various vibration environments.

Claims (10)

1. The landing gear protrusion test device of the carrier-based aircraft is characterized by comprising a main body supporting structure (10), a load applying mechanism (20) arranged on the main body supporting structure (10), and an aircraft-based lifting mechanism (30) connected with the load applying mechanism (20);
the main body supporting structure (10) comprises a main body supporting base (11), a plurality of main body supporting upright posts (12) extending along the vertical direction are fixedly arranged at the top of the main body supporting base (11), and a main body supporting top cover (13) is fixedly arranged at the top of the main body supporting upright posts (12);
a main body supporting accommodating shell (14) with a downward opening is commonly connected to the main body supporting upright posts (12), a plurality of supporting and restraining ear plates (15) are fixedly arranged on the outer side of the main body supporting accommodating shell (14), a plurality of supporting and restraining ear plates (15) are provided with supporting and restraining holes (151) which are vertically communicated, and the supporting and restraining holes (151) are in one-to-one corresponding sliding fit connection with the main body supporting upright posts (12);
the top of the main body supporting and accommodating shell (14) is provided with an accommodating shell through hole (141) which is vertically communicated;
the load applying mechanism (20) comprises a load applying shell (21) which is connected in a sliding fit manner in the main body supporting and accommodating shell (14), the load applying shell (21) is of a circular hollow shell structure, a plurality of vertically penetrating load driving rod through holes (211) are formed in the top of the load applying shell (21), a plurality of vertically extending load driving matching rods (221) are fixedly arranged on the top of the main body supporting and accommodating shell (14), the load driving matching rods (221) penetrate through the load driving rod through holes (211) and extend into the load applying shell (21), a load driving ring (222) is connected in a rotating fit manner in the load applying shell (21), and the load driving ring (222) is sleeved on the load driving matching rods (221) in a threaded transmission manner and is driven by a servo motor to rotate around a vertical axis;
The on-board landing gear (30) comprises a landing gear accommodating shell (31) connected to the inner side of the load applying shell (21) in a sliding fit manner and a landing locking release mechanism (33) arranged on the landing gear accommodating shell (31);
the top of the main body supporting base (11) is fixedly provided with a force measuring platform (40), and the lower end of the lifting mechanism accommodating shell (31) is fixedly provided with an aircraft nose landing gear.
2. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the supporting and restraining ear plate (15) is connected with the main body supporting upright post (12) through a lifting driving mechanism (16), the lifting driving mechanism (16) comprises a lifting driving ring (161) which is connected in the supporting and restraining hole (151) in a rotating fit manner, the main body supporting upright post (12) is a ball screw, and the lifting driving ring (161) is in transmission connection with the main body supporting upright post (12) in a ball screw transmission manner;
the main body supporting column (12) is characterized in that a plurality of longitudinal restraining rods (121) parallel to the main body supporting column are arranged on the periphery of the main body supporting column, the upper ends of the longitudinal restraining rods (121) are fixedly connected with the main body supporting top cover (13), the lower ends of the longitudinal restraining rods are fixedly connected with the main body supporting base (11), a plurality of longitudinal restraining holes (152) are formed in the supporting restraining lug plate (15), and the longitudinal restraining rods (121) are in one-to-one corresponding sliding fit connection with the longitudinal restraining holes (152).
3. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the lifting mechanism accommodating shell (31) is a cylindrical hollow shell, a plurality of lifting constraint sliding grooves (321) extending along the vertical direction are formed in the outer side wall of the lifting mechanism accommodating shell (31), a plurality of lifting constraint sliding rails (322) extending along the vertical direction are fixedly arranged on the inner side wall of the load applying shell (21), and the lifting constraint sliding rails (322) are in sliding fit connection with the lifting constraint sliding grooves (321) in a one-to-one correspondence manner;
the lifting locking and releasing mechanism (33) is arranged in the lifting constraint slide way (321), a locking mechanism accommodating hole (330) is formed in the inner side wall of the lifting constraint slide way (321), the locking mechanism accommodating hole (330) extends along the radial direction of the lifting mechanism accommodating shell (31), the lifting locking and releasing mechanism (33) comprises a locking and releasing driving block (331) which is in sliding fit in the locking mechanism accommodating hole (330), a locking wedge block (332) is fixedly arranged at one end of the locking and releasing driving block (331) close to the lifting constraint slide way (322), and a plurality of locking and matching holes (333) are formed in the side face of the lifting constraint slide way (322);
A locking driving telescopic rod (334) is arranged in the locking mechanism accommodating hole (330), the locking driving telescopic rod (334) is an electric control telescopic rod, the outer rod end part of the locking driving telescopic rod (334) is fixedly connected with the inner end part of the locking mechanism accommodating hole (330), and the inner rod end part of the locking driving telescopic rod (334) is fixedly connected with the locking release driving block (331);
the lifting constraint sliding rail (322) is connected with the inner side wall of the load application shell (21) through a sliding rail longitudinal fine adjustment mechanism (34), the sliding rail longitudinal fine adjustment mechanism (34) comprises a fine adjustment mechanism supporting shell (341) fixed on the inner side wall of the load application shell (21), the fine adjustment mechanism supporting shell (341) is a columnar shell extending along the vertical direction, a plurality of fixed communication grooves (342) which penetrate through the inside and outside and extend along the vertical direction are formed in the side surface, close to the axis of the load application shell (21), of the fine adjustment mechanism supporting shell (341), a plurality of longitudinal fine adjustment supporting columns (343) are arranged in a sliding fit manner in the fine adjustment mechanism supporting shell (341), the longitudinal fine adjustment supporting columns (343) are fixedly connected with the lifting constraint sliding rail (322) through a connecting plate, and the connecting plate penetrates through the fixed communication grooves (342) to be fixedly connected with the lifting constraint sliding rail (322).
The vertical fine adjustment support column (343) is provided with a fine adjustment threaded hole (344) which is vertically communicated, a plurality of fine adjustment threaded holes (344) on the vertical fine adjustment support column (343) are in common threaded transmission and provided with a fine adjustment threaded driving rod (345) which extends along the vertical direction, and a fine adjustment driving motor (346) which is used for driving the fine adjustment threaded driving rod (345) to rotate is fixedly arranged in the fine adjustment mechanism support shell (341).
4. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the utility model discloses a load is applied to casing (21) and is equipped with directional restraint mechanism (23), the load is applied casing (21) top and is had a plurality of vertical directional slip restraint hole (231) that link up, directional restraint mechanism (23) are including being located every directional slip restraint hole (231) department is fixed directional restraint section of thick bamboo (232) at the top in the casing (21) is applyed to the load, directional restraint section of thick bamboo (232) opening up, the main part supports the fixed directional restraint post (233) that are equipped with of top in holding shell (14) along vertical direction extension, many directional restraint post (233) and a plurality of directional restraint section of thick bamboo (232) carry out sliding fit connection one-to-one.
5. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the load applying shell (21) is internally provided with a carrier-based vibration simulation mechanism (24), the carrier-based vibration simulation mechanism (24) comprises a vibration simulation accommodating column (241) fixed inside the load applying shell (21), the vibration simulation accommodating column (241) is a hollow cylindrical shell, and the vibration simulation accommodating column (241) extends along the vertical direction and is fixed inside the load applying shell (21);
two electromagnetic driving coils (242) are fixedly arranged in the vibration simulation accommodating column (241), two permanent magnet column constraint rings (243) are fixedly arranged between the two electromagnetic driving coils (242) in the vibration simulation accommodating column (241), and permanent magnet driving columns (244) are arranged between the two permanent magnet column constraint rings (243) in a sliding fit manner;
one ends of the two permanent magnet column constraint rings (243) close to each other are fixedly provided with rubber damping rings (245);
a deflection support sliding rail (251) is fixedly arranged at the inner bottom of the load applying shell (21), a deflection support sliding block (252) is arranged on the deflection support sliding rail (251) in a sliding fit manner, the lower end of the vibration simulation accommodating column (241) is connected with the deflection support sliding block (252) through a first damping connecting rod (253), the first damping connecting rod (253) is an electromagnetic telescopic rod with adjustable damping, the end part of an outer rod of the first damping connecting rod (253) is connected with the lower end of the vibration simulation accommodating column (241) in a ball hinge connection mode, and the end part of an inner rod of the first damping connecting rod (253) is connected with the deflection support sliding block (252) in a ball hinge connection mode;
The upper end of the vibration simulation accommodating column (241) is connected with the inner top of the load application shell (21) through a second damping connecting rod (254), the second damping connecting rod (254) is an electromagnetic telescopic rod with adjustable damping, the outer rod end of the second damping connecting rod (254) is connected with the upper end of the vibration simulation accommodating column (241) in a ball hinge connection mode, and the inner rod end of the second damping connecting rod (254) is connected with the inner top of the load application shell (21) in a ball hinge connection mode.
6. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the utility model discloses a load is applied to casing (21) inboard is equipped with auxiliary orientation mechanism (35) that rises and falls, auxiliary orientation mechanism (35) are including fixing auxiliary orientation backup pad (351) that is annular that casing (21) inboard was applied to the load, auxiliary orientation backup pad (351) downside is fixed to be equipped with many auxiliary orientation restraint posts (352) that extend along vertical direction, have a plurality of auxiliary orientation restraint holes (353) that link up vertically on the mechanism accommodation shell (31), a plurality of auxiliary orientation restraint posts (352) and a plurality of auxiliary orientation restraint holes (353) are corresponding to one-to-one and are carried out sliding fit and are connected.
7. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the top of the main body supporting and accommodating shell (14) is provided with a lifting and accommodating shell reset mechanism (36), the lifting and accommodating shell reset mechanism (36) comprises a reset support column (361) which is fixed at the top of the lifting and accommodating shell (31) and extends along the vertical direction, and a reset constraint supporting cylinder (362) with a downward opening is surrounded on the outer side of the reset support column (361);
the inner side wall of the reset constraint supporting cylinder (362) is connected with a plurality of reset constraint fixing plates (363), the reset constraint fixing plates (363) are connected with the inner side wall of the reset constraint supporting cylinder (362) through a reset constraint connecting rod (364), and two ends of the reset constraint connecting rod (364) are respectively connected with the reset constraint fixing plates (363) and the inner side wall of the reset constraint supporting cylinder (362) in a fixed hinge connection mode;
the device is characterized in that a fixed plate driving rod accommodating cylinder (365) is fixedly arranged on the outer side wall of the reset constraint supporting cylinder (362), the axis of the fixed plate driving rod accommodating cylinder (365) extends along the radial direction of the reset constraint supporting cylinder (362), a driving rod communication hole (366) communicated with the inside of the fixed plate driving rod accommodating cylinder (365) is formed in the side edge of the reset constraint supporting cylinder (362), a fixed plate driving rod (367) is arranged in the fixed plate driving rod accommodating cylinder (365), the fixed plate driving rod (367) is an electric control telescopic rod, the inner rod end part of the fixed plate driving rod (367) penetrates through the driving rod communication hole (366) and is connected with the reset constraint connecting rod (364) in a fixed hinge connection mode, and the outer rod end part of the fixed plate driving rod (367) is connected with the inner end part of the fixed plate driving rod accommodating cylinder (365) in a fixed hinge connection mode;
The main body support holds a plurality of reset lifting fixed barrels (371) with upward openings, reset lifting drive barrels (372) with downward openings are arranged in the reset lifting fixed barrels (371) in a sliding fit mode, reset lifting drive rods (373) are arranged in the reset lifting fixed barrels (371), the reset lifting drive rods (373) are electric control telescopic rods, the outer rod ends of the reset lifting drive rods (373) are fixedly connected with the inner bottoms of the reset lifting fixed barrels (371), and the inner rod ends of the reset lifting drive rods (373) are fixedly connected with the inner tops of the reset lifting drive barrels (372);
the tops of the resetting lifting driving cylinders (372) are connected with a resetting mechanism supporting plate (37) together, and the resetting mechanism supporting plate (37) is fixedly connected with the tops of the resetting constraint supporting cylinders (362).
8. The carrier aircraft landing gear protrusion test device of claim 1, wherein: lifting mechanism holds shell (31) top and is equipped with lift simulation mechanism (38), lift simulation mechanism (38) are including fixing lifting mechanism holds shell (31) top and lift simulation drive post (381) that extend along vertical direction, lift simulation drive post (381) lateral wall is fixed to be equipped with a plurality of lift drive blades (382), lift simulation drive post (381) outside is encircleed and is equipped with lift simulation constraint cylinder (383) that the opening is down, lift simulation constraint cylinder (383) top is fixed to be equipped with lift drive exhaust tube (384) rather than inside intercommunication, lift simulation constraint cylinder (383) with load is applyed the fixed link to each other of casing (21) inside wall.
9. The carrier aircraft landing gear protrusion test device of claim 1, wherein: the outer side surface of the lifting mechanism accommodating shell (31) is provided with a plurality of counterweight accommodating holes (391) extending along the radial direction of the lifting mechanism accommodating shell (31), a resident counterweight column (392) is arranged in sliding fit in the counterweight accommodating holes (391), a counterweight adjusting threaded hole (393) penetrating along the axis of the counterweight accommodating holes (391) is formed in the resident counterweight column (392), a counterweight adjusting threaded rod (394) is arranged in the counterweight adjusting threaded hole (393) in a threaded transmission fit manner, and a counterweight adjusting motor (395) for driving the counterweight adjusting threaded rod (394) to rotate is fixedly arranged in the counterweight accommodating holes (391);
the counterweight accommodating hole (391) is provided with a plurality of additional counterweight columns (396) in a sliding fit manner, threaded holes penetrating along the axis of the counterweight accommodating hole (391) are formed in the additional counterweight columns (396), and the threaded holes in the additional counterweight columns (396) are in threaded rotation connection with the counterweight adjusting threaded rods (394).
10. The method for carrying out the ship-borne aircraft landing gear protrusion test by using the ship-borne aircraft landing gear protrusion test equipment according to any one of claims 1-9, which is characterized by comprising the following steps:
S1, stably mounting an aircraft nose landing gear:
mounting the nose landing gear of the aircraft at the lower end of a landing gear accommodating shell (31), and adjusting the height position of a main body supporting accommodating shell (14) to enable the tire static pressure of the nose landing gear of the aircraft to be on the top of a force measuring platform (40);
s2, applying a vertical load to the nose landing gear of the aircraft:
the servo motor drives the loading drive ring (222) to rotate, so that the loading drive ring (222) moves downwards relative to the loading drive matching rod (221), and the loading drive ring (222) further drives the whole load applying shell (21) to move downwards along the axis of the main body supporting accommodating shell (14);
at this time, the entire lifting mechanism accommodating case (31) is relatively fixed in the load applying case (21) by means of the lifting lock release mechanism (33);
the load applying shell (21) drives the lifting mechanism accommodating shell (31) to move downwards together to apply a preset vertical load to the nose landing gear of the aircraft;
s3, unlocking a lifting mechanism accommodating shell (31) by a lifting locking release mechanism (33), and completing a protruding process of the nose landing gear of the aircraft:
the lifting locking release mechanism (33) is used for unlocking the lifting mechanism accommodating shell (31) so that the lifting mechanism accommodating shell (31) can freely slide in the load applying shell (21);
The whole lifting mechanism accommodating shell (31) simulates the dead weight load of the aircraft, and after the whole lifting mechanism accommodating shell (31) is separated from the inside of the load applying shell (21), the nose landing gear of the aircraft protrudes to drive the whole lifting mechanism accommodating shell (31) to move upwards along the axis of the load applying shell (21);
and meanwhile, the force measuring platform (40) measures and records the stress condition of the nose landing gear of the aircraft.
CN202311200200.7A 2023-09-18 2023-09-18 Device and method for testing protrusion of landing gear of carrier-based aircraft Active CN116929819B (en)

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