CN116946386A - Front wheel angular displacement interference excitation device for aircraft ground intensity shimmy test - Google Patents
Front wheel angular displacement interference excitation device for aircraft ground intensity shimmy test Download PDFInfo
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- CN116946386A CN116946386A CN202311175124.9A CN202311175124A CN116946386A CN 116946386 A CN116946386 A CN 116946386A CN 202311175124 A CN202311175124 A CN 202311175124A CN 116946386 A CN116946386 A CN 116946386A
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- 238000006073 displacement reaction Methods 0.000 title claims abstract description 43
- 238000012360 testing method Methods 0.000 title claims abstract description 40
- 230000005284 excitation Effects 0.000 title claims abstract description 30
- 230000007246 mechanism Effects 0.000 claims abstract description 73
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 19
- 239000010959 steel Substances 0.000 claims abstract description 19
- 210000001503 joint Anatomy 0.000 claims abstract description 9
- 239000000314 lubricant Substances 0.000 claims description 24
- 238000010926 purge Methods 0.000 claims description 20
- 238000005461 lubrication Methods 0.000 claims description 18
- 230000005540 biological transmission Effects 0.000 claims description 12
- 238000007906 compression Methods 0.000 claims description 11
- 230000006835 compression Effects 0.000 claims description 10
- 230000001502 supplementing effect Effects 0.000 claims description 9
- 238000003860 storage Methods 0.000 claims description 6
- 238000007664 blowing Methods 0.000 claims description 4
- 239000003153 chemical reaction reagent Substances 0.000 claims description 4
- 230000002452 interceptive effect Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 239000011232 storage material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 description 12
- 230000008569 process Effects 0.000 description 9
- 230000033001 locomotion Effects 0.000 description 8
- 230000009471 action Effects 0.000 description 5
- 230000003139 buffering effect Effects 0.000 description 5
- 230000004044 response Effects 0.000 description 5
- 239000003795 chemical substances by application Substances 0.000 description 3
- 238000013016 damping Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000013589 supplement Substances 0.000 description 3
- 238000010408 sweeping Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000005483 Hooke's law Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000010998 test method 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a front wheel angular displacement interference excitation device for an aircraft ground intensity shimmy test, which comprises a padlock unhooking mechanism, a steel wire rope, a guide wheel and a connecting seat, wherein one end of the padlock unhooking mechanism is in butt joint with the connecting seat, the other end of the padlock unhooking mechanism is connected with the steel wire rope, the steel wire rope bypasses the guide wheel and is connected with an aircraft wheel shaft, and the padlock unhooking mechanism comprises a base, a bearing sliding table, a lock cylinder, a lock hook, a servo oil cylinder and a unhooking trigger mechanism. The device is provided with the padlock unhooking mechanism in a modularized mode, breaks through the release speed limit of the traditional hydraulic loading device, realizes the application of different amplitude angular displacements and ideal initial states of the landing gear in the landing gear shimmy test of the ground intensity of the aircraft, and provides data guidance for the shimmy stability analysis of the landing gear of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft performance tests, in particular to a front wheel angular displacement interference excitation device for an aircraft ground intensity shimmy test.
Background
In the development of an aircraft landing gear system, in order to prevent the aircraft landing gear from generating shimmy in the process of taking off and landing running under the ground load condition, a shimmy bench experiment is carried out according to GJB-5863-2006, and the stability of the aircraft landing gear system is checked by testing the dynamic response of the aircraft landing gear after the ground is initially disturbed, so that possible problems in design are found as soon as possible. According to the control theory, the stability of the system reflects the nature of the transition (zero input response) after the disturbance (initial deviation) has disappeared. Stability of an aircraft landing gear system therefore refers to: under the action of the initial deviation state, the transition process of the angular displacement of the turning system is attenuated to be zero along with time, the capability of recovering the stable running equilibrium state is provided, correspondingly, the GJB-5863-2006 requires that the aircraft landing gear is subjected to enough single impact, and the impact release speed is faster than the rebound speed of the aircraft landing gear. Therefore, the disturbance excitation device is required to generate an initial state in which the disturbance vanishing time is unconstrained, in addition to the amplitude-adjustable angular displacement.
At present, a servo oil cylinder is often adopted for the shimmy test to apply torsion excitation to an aircraft landing gear through a wire rope direct-connected wheel axle, but the release speed of interference excitation is easily limited by the capacity of a hydraulic system, so that the steering of the aircraft landing gear is limited. The rigidity and the damping of the modern aircraft landing gear turning system are matched, and meanwhile, the control performance and the anti-swing performance are both considered, and the step response shows the technical characteristics of high speed in return and small overshoot. Therefore, the traditional hydraulic loading device based on the position closed loop cannot meet the control requirement of the front wheel angular displacement interference excitation in the aircraft ground intensity shimmy test, and a front wheel angular displacement interference excitation device with adjustable stroke and reliable operation is urgently required to be designed.
Disclosure of Invention
In order to solve the technical problems, the invention provides a front wheel angular displacement interference excitation device for an aircraft ground intensity shimmy test.
The technical scheme of the invention is as follows: the device comprises a padlock unhooking mechanism, a steel wire rope, a guide wheel and a connecting seat, wherein one end of the padlock unhooking mechanism is in butt joint with the connecting seat, the other end of the padlock unhooking mechanism is connected with the steel wire rope, the steel wire rope bypasses the guide wheel and is connected with a wheel shaft of an aircraft landing gear, and the padlock unhooking mechanism comprises a base, a bearing sliding table, a lock cylinder, a lock hook, a servo oil cylinder and a unhooking triggering mechanism;
the bearing sliding table is positioned in the base and is in sliding connection with the base, the base is a rectangular frame body formed by two long plates and two short plates, the inner walls of the two long plates are provided with first sliding rails, the side wall of the bearing sliding table is provided with sliding blocks which are in sliding connection with the first sliding rails,
the lock core passes through a round hole arranged on one of the short plates and is connected with a steel wire rope, two lock hooks are symmetrically arranged above the bearing sliding table by taking the lock core as a symmetry axis, the middle part of each lock hook is rotationally connected with the bearing sliding table through a pin shaft, one end of each lock hook is clamped with the lock core, the other end of each lock hook is provided with a rotating rocker arm, a compression spring is arranged between the two rotating rocker arms and is hinged with the rotating rocker arm,
the unhooking trigger mechanism is provided with two groups and corresponds to the lock hooks one by one, the unhooking trigger mechanism is composed of a spring damper, a trigger switch and a series spring, the servo oil cylinder and the spring damper are arranged on the inner wall of the other short plate, the output end of the servo oil cylinder is connected with the bearing sliding table, the trigger switch is connected with the output end of the spring damper, the trigger switch is connected with the bearing sliding table through the series spring, and a deflector rod for pulling by the trigger switch and linking the lock hook to release the lock core is arranged on the rotating rocker arm.
Further, a buffer rubber block is arranged on the round hole.
Description: impact force of the lock cylinder can be effectively buffered through the buffer rubber block, and damage to the padlock unhooking mechanism caused by direct impact of the lock cylinder and the base is prevented.
Further, the rotary rocker arm is provided with a latch hook roller, and the inner walls of the two long plates are respectively provided with a second slide rail which is used for being in sliding connection with the latch hook roller.
Description: the friction force between the lock hook and the second sliding rail can be reduced through the lock hook roller, so that the lock hook roller can freely slide along the axis direction of the servo oil cylinder without clamping stagnation on the second sliding rail.
Further, the cross section of the first sliding rail is trapezoid, and the sliding block is provided with a trapezoid groove which is matched with the first sliding rail.
Description: the first sliding rail and the sliding block with the trapezoid cross section can bear the overturning moment applied to the bearing sliding table by the action point of the interference excitation load.
Further, the outer walls of the two long plates are respectively provided with a clamping strip for being in butt joint with the connecting seat.
Description: the stability of the butt joint with the connecting seat can be improved through the clamping strip, and the connection of the padlock unhooking mechanism is facilitated.
Furthermore, a group of sweeping and lubricating mechanisms for sweeping the first sliding rail and the second sliding rail and applying lubricant are arranged on the inner walls of the two long plates between the first sliding rail and the second sliding rail,
the purging lubrication mechanism consists of a pressure gas tank, a gas transmission main pipe, a storage agent bin, a plurality of triggering pieces and a release pipe, wherein the pressure gas tank is arranged on a base, the gas transmission main pipe is embedded in an inner cavity of a long plate and is communicated with the pressure gas tank, the release pipe is embedded in inner cavities of a first sliding rail and a second sliding rail at equal intervals, the release pipe is communicated with the gas transmission main pipe through a connecting pipe, the triggering pieces are connected on the connecting pipe,
the triggering piece consists of a rod body and a sleeve, the side wall of the sleeve is provided with an air inlet and an air outlet which are used for being communicated with the connecting pipe, the rod body consists of a magnetic column used for driving the rod body to move and a piston column used for controlling the connecting pipe to be connected or disconnected, the piston column is in sliding sealing connection with the sleeve, the piston column is provided with a sleeve spring connected with the bottom of the sleeve,
the release tube consists of a tube body and a piston assembly, wherein one end face of the tube body is communicated with the connecting tube, the other end face of the tube body is provided with an agent outlet and an agent supplementing hole, the side face of the tube body is provided with an air outlet, the piston assembly is arranged in the tube body and consists of two piston sheets and a buffer rod for delay triggering of the two piston sheets, the two piston sheets are correspondingly connected with the two ends of the buffer rod, one piston sheet is provided with a tube body spring connected with the bottom of the tube body,
the lubricant outlet hole corresponds to lubricant holes formed in the first sliding rail and the second sliding rail, the air outlet hole corresponds to air blowing holes formed in the first sliding rail and the second sliding rail, the lubricant supplementing hole is communicated with the lubricant storage bin through a pipeline, and a magnetic block used for being matched with the magnetic column to drive the rod body to move is arranged on the bearing sliding table.
Description: the purging lubrication mechanism can automatically purge and apply the lubricant to the first sliding rail and the second sliding rail when the bearing sliding table moves, so that the sliding block and the locking hook roller slide more smoothly with the first sliding rail and the second sliding rail, the influence of jamming on the accuracy of the aircraft ground strength shimmy test caused by sliding is avoided, and the purging and the lubricant application can be automatically realized by the purging lubrication mechanism, so that the use effect of the lubricant is prevented from being influenced by mixing of impurities and the lubricant.
Furthermore, the buffer rod consists of an inner pipe and an outer pipe, the inner pipe is in sliding connection with the outer pipe, a flanging and a baffle ring are correspondingly arranged on the butt joint end face of the outer pipe and the inner pipe, and magnetic sheets are respectively arranged on the end face of the inner pipe and the inner end face of the outer pipe.
Description: utilize the buffer rod can make two piston sheets delay trigger to make the release pipe realize triggering earlier to first slide rail, second slide rail sweep the processing, later apply the lubricant to first slide rail, second slide rail again, thereby improve and sweep the lubrication effect of sweeping of lubrication mechanism, make slider, latch hook gyro wheel and first slide rail, second slide rail between slide more smooth and easy.
Still further, be equipped with the buffering gasbag ring on the round hole, a plurality of reset springs are built-in to the buffering gasbag ring, and the buffering gasbag ring passes through pipeline and pressure gas jar intercommunication, and is equipped with the air supplement mouth on the buffering gasbag ring, buffering gasbag ring and pipeline junction are equipped with the check valve, be equipped with the check valve on the air supplement mouth.
Description: the buffer air bag ring can effectively buffer the impact force of the lock core, prevent the lock core from being damaged by the padlock unhooking mechanism caused by direct impact of the lock core and the base, and can recycle the impact force of the lock core, and the buffer air bag ring is used for pressurizing and inflating the pressure air tank.
Further, a pressure gauge and a booster air pump are arranged on the top surface of the pressure air tank.
Description: the pressure gauge and the booster air pump can be used for monitoring the air pressure of the pressure air tank in real time, and the booster air pump is used for compensating and controlling the air pressure of the pressure air tank, so that the stable operation of the purging lubrication mechanism is guaranteed.
The beneficial effects of the invention are as follows:
(1) According to the invention, the padlock unhooking mechanism is loaded in a modularized manner by the front wheel angular displacement disturbance excitation device for the aircraft ground intensity shimmy test, so that the release speed limit of the traditional hydraulic loading device is broken through, the application of different amplitude angular displacements and ideal initial states (step signals) of the landing gear of the aircraft in the aircraft ground intensity shimmy test is realized, the zero input response of the system is accurately obtained, the angular displacement of the landing gear of the aircraft can be ensured not to exceed the limit value required by the specification through angle calibration, and the data guidance is provided for the shimmy stability analysis of the landing gear of the aircraft;
(2) The front wheel angular displacement interference excitation device for the aircraft ground intensity shimmy test is implemented by matching the servo oil cylinder with the padlock unhooking mechanism, and the aircraft landing gear torsion direction loading is carried out through the guide pulley, so that the device has a simple structure, is easy to operate and is convenient to maintain; introducing the concept of angle calibration into the front wheel angular displacement test of the aircraft ground intensity shimmy test, and eliminating the overrun loading risk of a turning system;
(3) The padlock unhooking mechanism has the advantages of adjustable stroke, large bearing capacity and high reliability, and accurate triggering of different angular displacements is realized by using the spring damper and the series springs; aiming at the principle of controllable angle and reliable loading in the test process, a padlock unhooking mechanism is designed, and reliable loading and triggering are realized through two sets of protection mechanisms of a compression spring and a rotating rocker arm passing dead point; the angular displacement quantitative triggering function is realized by reasonably configuring the spring damper and the series spring parameters.
Drawings
FIG. 1 is an overall schematic diagram of a front wheel angular displacement disturbance excitation device for an aircraft ground intensity shimmy test of the present invention;
fig. 2 is a schematic structural view of a padlock unhooking mechanism according to embodiment 1 of the present invention;
fig. 3 is a schematic view showing the internal structure of the padlock unhooking mechanism according to embodiment 1 of the present invention;
fig. 4 is a schematic view showing an assembled structure of a rotary rocker arm and a compression spring of a padlock unhooking mechanism according to embodiment 1 of the present invention;
fig. 5 is a schematic structural view of a padlock unhooking mechanism according to embodiment 2 of the present invention;
fig. 6 is a schematic view showing a partially sectional structure of a shackle mechanism for padlock according to embodiment 2 of the present invention;
fig. 7 is a schematic view of a carrying slipway structure of a padlock unhooking mechanism according to embodiment 2 of the present invention;
FIG. 8 is a schematic view showing the external structure of a trigger member of a purge lubrication mechanism according to embodiment 2 of the present invention;
FIG. 9 is a schematic view showing the internal structure of a trigger member of a purge lubrication mechanism according to embodiment 2 of the present invention;
FIG. 10 is a schematic view showing the structure of a release tube in a first slide rail of a purge lubrication mechanism according to embodiment 2 of the present invention;
FIG. 11 is a schematic view showing the structure of a release tube in a second slide rail of the purge lubrication mechanism according to embodiment 2 of the present invention;
FIG. 12 is a schematic view showing the internal structure of a release tube of the purge lubrication mechanism according to embodiment 2 of the present invention;
FIG. 13 is a schematic view showing the internal structure of a buffer rod of a purge lubrication mechanism according to embodiment 2 of the present invention;
fig. 14 is a schematic structural view of a padlock unhooking mechanism according to embodiment 3 of the present invention;
FIG. 15 is a schematic structural view of a cushion airbag ring according to embodiment 3 of the present invention;
FIG. 16 is a simplified model of the unhooking trigger mechanism of the present invention;
FIG. 17 is a schematic diagram of the operation of the unhooking trigger mechanism of the present invention wherein (a) loading and (b) unhooking;
FIG. 18 is a graph of the movement of the unhooking trigger mechanism of the present invention;
FIG. 19 is a schematic view of the trigger position (X) of the speed trigger mechanism of the present invention 1 -X 2 | (t=0) =0.1m）；
FIG. 20 is a logic block diagram of a test procedure for a nose wheel angular displacement disturbance excitation device for an aircraft ground intensity shimmy test of the present invention;
the device comprises a 1-padlock unhooking mechanism, a 11-base, a 111-long plate, a 112-short plate, a 113-first sliding rail, a 114-round hole, a 115-second sliding rail, a 116-clamping bar, a 12-bearing sliding table, a 121-sliding block, a 122-magnetic block, a 13-lock cylinder, a 14-lock hook, a 15-servo cylinder, a 16-rotating rocker arm, a 17-compression spring, a 18-spring damper, a 19-trigger switch, a 191-deflector rod, a 10-series spring, a 2-wire rope, a 3-guide wheel, a 4-connecting seat, a 5-pressure gas tank, a 51-buffer gas bag ring, a 6-gas transmission main pipe, a 61-connecting pipe, a 7-storage bin, an 8-triggering piece, a 81-rod body, a 82-sleeve, a 83-sleeve spring, a 9-releasing pipe, a 91-pipe body, a 92-pipe body spring, a 93-piston sheet, a 94-buffer rod, a 941-inner pipe, a 942-outer pipe, a 943-flanging and a 944-baffle ring.
Detailed Description
The invention will be described in further detail with reference to the following embodiments to better embody the advantages of the invention.
Example 1: the device comprises a padlock unhooking mechanism 1, a steel wire rope 2, a guide wheel 3 and a connecting seat 4, wherein the right end of the padlock unhooking mechanism 1 is in butt joint with the connecting seat 4, the left end of the padlock unhooking mechanism 1 is connected with the steel wire rope 2, the steel wire rope 2 bypasses the guide wheel 3 and is connected with a wheel axle of an undercarriage of the aircraft,
as shown in fig. 2-4, the padlock unhooking mechanism 1 comprises a base 11, a bearing sliding table 12, a lock cylinder 13, a lock hook 14, a servo oil cylinder 15 and a unhooking triggering mechanism; the bearing sliding table 12 is positioned in the base 11 and is in sliding connection with the base 11, the base 11 is a rectangular frame body formed by two long plates 111 and two short plates 112, clamping strips 116 for butting with the connecting seat 4 are arranged on the outer walls of the two long plates 111, first sliding rails 113 are arranged on the inner walls of the two long plates 111, sliding blocks 121 for sliding connection with the first sliding rails 113 are arranged on the side walls of the bearing sliding table 12, the cross section of the first sliding rails 113 is trapezoidal, trapezoidal grooves which are matched with the first sliding rails 113 are arranged on the sliding blocks 121, a lock cylinder 13 penetrates through a round hole 114 arranged on one of the short plates 112 and is connected with a steel wire rope 2, buffer rubber blocks are arranged on the round hole 114, two lock hooks 14 are symmetrically arranged above the bearing sliding table 12 by taking the lock cylinder 13 as a symmetrical axis, the middle part of each lock hook 14 is rotationally connected with the bearing sliding table 12 through a pin shaft, one end of the lock hook 14 is clamped with the lock cylinder 13, the other end of the lock hook 14 is provided with a rotary rocker arm 16, a compression spring 17 is arranged between the two rotary rocker arms 16, the compression spring 17 is hinged with the rotary rocker arm 16, lock hook idler wheels are arranged on the rotary rocker arm 16, the inner walls of the two long plates 111 are respectively provided with a second sliding rail 115 which is used for being in sliding connection with the lock hook idler wheels, the unhooking trigger mechanism is provided with two groups and corresponds to the lock hook 14 one by one, the unhooking trigger mechanism consists of a spring damper 18, a trigger switch 19 and a series spring 10, the servo cylinder 15 and the spring damper 18 are respectively arranged on the inner wall of the other short plate 112, the output end of the servo cylinder 15 is connected with lugs of the bearing sliding table 12, the trigger switch 19 is connected with the output end of the spring damper 18, and the trigger switch 19 is connected with the bearing sliding table 12 through the series spring 10, the rotary rocker arm 16 is provided with a deflector 191 for interlocking the lock hook 14 to release the lock cylinder 13 by being toggled by the trigger switch 19.
The working principle of the front wheel angular displacement interference excitation device for the aircraft ground intensity shimmy test is as follows:
the lock core 13 is pressed downwards by driving the lock hook 14 through the bearing sliding table 12, the bottom of the lock hook 14 is opened, and meanwhile, the compression spring 17 at the top of the lock hook 14 is compressed and reset, so that automatic padlock is realized, the two rotating rocker arms 16 are mutually closed by shifting the shifting lever 191 of the rotating rocker arms 16 through the trigger switch 19, the lock hook 14 can rotate around the pin shaft, and the reliable release of the lock core 13 is realized;
after padlock, the servo cylinder 15 contracts, applying the interfering excitation load and displacement transferred to the wheel axle of the landing gear of the aircraft through the load-bearing skid 12. The spring damper 18 arranged between the base 11 and the carrying slipway 12 and the compression spring 17 are simultaneously acted by axial force, and the trigger switch 19 can generate different movement displacements, so that the amplitude-adjustable angular displacement is applied to the landing gear of the aircraft. The servo cylinder 15 adopts speed grading loading, as shown in fig. 16, establishes a kinematics model of the unhooking trigger mechanism, and briefly describes the working principle of the unhooking trigger mechanism:
the motion equation of the unhooking triggering mechanism is as follows:
（1）
（2）
in the method, in the process of the invention,displacement of the trigger switch 19 (disturbance excitation displacement); />For triggering the mass of the switch 19; />Stiffness of the spring damper 18; c is the damping coefficient of the spring damper 18; />For carrying the displacement of the slide 12->An adjustable speed within the load characteristic range of the servo cylinder 15; />For carrying the mass of the sliding table 12 (comprising the locking hook 14, the compression spring 17 and the rotary rocker arm 16); />Is the stiffness of the series spring 10; t is time.
From equation (2), it can be seen thatThe initial speed is not zero, and engineering is not easy to realize. Compensating a forward speed from zero before the original speed, wherein the compensated speed is expressed by a formula (3):
（3）
designing a spring damping system, solving a second-order constant coefficient linear non-homogeneous differential equation which is formed as formula (1) by adopting a Dragon library tower method, substituting a speed signal of formula (3), and obtaining the interference excitation displacement transmitted to the lock cylinder 13. The working principle of the unhooking trigger mechanism is shown in fig. 17, the (a) in fig. 17 is the loading state of the unhooking trigger mechanism, the (b) in fig. 17 is the unhooking state of the unhooking trigger mechanism, the motion curves of the carrying slipway 12 and the trigger switch 19 are shown in fig. 18, and the trigger position is shown in fig. 19.
In the shimmy test process, a steel wire rope 2 with a large macroscopic elastic modulus is adopted, and the installation rigidity of the guide wheel 3 is controlled. The steel wire rope 2 is connected with the center of a wheel axle of the aircraft landing gear through the guide wheel 3, and the transmission servo oil cylinder 15 is pulled to interfere with excitation load and displacement in the loading process, so that the angular displacement is indirectly applied to the wheel axle of the aircraft landing gear. The connecting steel wire rope 2 obeys Hooke's law, and through reasonable selection, the elastic deformation amount borne in the test process is ensured to be less than 1.0%, and the deformation of the guide wheel 3 along the resultant force direction is less than 1mm when the excitation load is transmitted.
As shown in fig. 20, the method steps for testing using the aircraft ground intensity shimmy test front wheel angular displacement disturbance excitation device are as follows:
(1) Test preparation: the center hinge point of the wheel axle of the aircraft landing gear passes through the guide wheel 3 through the steel wire rope 2 to be connected with the padlock unhooking mechanism 1, so that the center of the wheel axle of the aircraft landing gear, the guide wheel 3 are installed, the lock cylinder 13 is connected and positioned at the same horizontal height, the lock cylinder 13 is coaxial with the steel wire rope 2 and is in a locking state, the steel wire rope 2 is adjusted to be in a loosening state, and the initial position is recorded;
(2) And (3) angle calibration: and calibrating the maximum angular displacement according to the test installation. Firstly, vertically compressing an aircraft landing gear to a shutdown load, loading a wheel shaft of the aircraft landing gear through a servo oil cylinder 15, wherein the loading speed is not more than 5mm/s (quasi-static loading) until a lock cylinder 13 is separated from a lock hook 14, recording the maximum angular displacement at the unhooking moment, and adjusting the length of a steel wire rope 2 to ensure that the maximum angular displacement is not more than 6 degrees;
(3) And (3) testing: the large flywheel is controlled to simulate the ground speed, different test working conditions such as take-off and landing are completed for the undercarriage of the aircraft, the calculation result of the model is simplified according to the unhooking trigger mechanism, the servo cylinder 15 is loaded in a speed grading manner, the dynamic response signal of the angular displacement after triggering is collected, the padlock waits after the single test is completed, whether the interference excitation meets the requirement is judged, and the excitation process is repeated in the follow-up test until the test is finished normally.
Example 2: this embodiment differs from embodiment 1 in that, as shown in fig. 5 to 13, a set of purge lubrication mechanisms for purging and applying lubricant to the first rail 113 and the second rail 115 are provided on the inner walls of the two long plates 111 located between the first rail 113 and the second rail 115, the purge lubrication mechanism is composed of a pressure gas tank 5, a gas transmission main pipe 6, a storage tank 7, seven triggering pieces 8 and seven release pipes 9, the pressure gas tank 5 is provided on a base 11, the gas transmission main pipe 6 is buried in the inner cavity of the long plates 111 and communicates with the pressure gas tank 5, the release pipes 9 are buried in the inner cavities of the first rail 113 and the second rail 115 at equal intervals, and since the width of the first rail 113 is twice the width of the second rail 115, the diameter of the release pipe 9 buried in the first rail 113 is twice the diameter of the release pipe 9 buried in the second rail 115, in contrast to fig. 10 and 11, the release tube 9 is connected to the gas transmission main tube 6 through the connecting tube 61, the trigger 8 is connected to the connecting tube 61, the trigger 8 is composed of a rod 81 and a sleeve 82, the side wall of the sleeve 82 is provided with a gas inlet and a gas outlet for communicating with the connecting tube 61, the rod 81 is composed of a magnetic column for driving the rod 81 to move and a piston column for controlling the connecting tube 61 to be connected or disconnected, the piston column is in sliding sealing connection with the sleeve 82, the piston column is provided with a sleeve spring 83 connected with the bottom of the sleeve 82, the release tube 9 is composed of a tube 91 and a piston assembly, one end face of the tube 91 is communicated with the connecting tube 61, the other end face of the tube 91 is provided with a reagent outlet and a reagent supplementing hole, the side face of the tube 91 is provided with a gas outlet, the piston assembly is arranged in the tube 91, as shown in fig. 12, the piston assembly comprises two piston sheets 93 and a buffer rod 94 for delayed triggering of the two piston sheets 93, the two piston sheets 93 are correspondingly connected with the left end and the right end of the buffer rod 94, a tube body spring 92 connected with the bottom of the tube body 91 is arranged on the right end face of the piston sheet 93 positioned on the right side, the buffer rod 94 comprises an inner tube 941 and an outer tube 942, the inner tube 941 and the outer tube 942 are in sliding connection, a flanging 943 and a baffle ring 944 are correspondingly arranged on the butt joint end face of the outer tube 942 and the inner tube 941, the end face of the inner tube 941 and the inner end face of the outer tube 942 are respectively provided with a magnetic sheet, an air outlet hole corresponds to a lubricant hole arranged on the first sliding rail 113 and the second sliding rail 115, an air blowing hole arranged on the first sliding rail 113 and the second sliding rail 115, the supplement hole is communicated with the air storage bin 7 through a pipeline, a magnetic block 122 for matching with the movement of the magnetic column driving rod body 81 is arranged on the bearing sliding table 12, a pressure gauge and a pressurizing air pump are arranged on the top face of the pressure air tank 5, and the pressurizing air pump are selected from a commercially available pressure gauge and an air pump.
The working principle of the purging lubrication mechanism is as follows: when the carrying slipway 12 moves along the first slide rail 113, the magnetic blocks 122 and the magnetic columns of the rod body 81 of the trigger piece 8 perform mutual magnetic repulsion, so that the rod body 81 moves inwards along the sleeve 82 and compresses the sleeve spring 83, the piston columns are dislocated from the air inlet and the air outlet after the rod body 81 moves, the connecting pipe 61 is connected, the pressure gas enters the release pipe 9 embedded in the first slide rail 113 and the second slide rail 115 respectively under the action of the pressure gas tank 5 and the gas transmission main pipe 6, and the piston assembly moves under the pushing of the pressure gas;
the piston assembly moves in a specific mode that firstly, one piston piece 93 close to the connecting pipe 61 is pushed to enable the piston piece 93 to be close to the other piston piece 93, during the movement, the piston piece 93 and the air outlet holes are staggered to enable pressure air to be blown out of the air blowing holes along the air passages, the first sliding rail 113 and the second sliding rail 115 are purged, when the piston piece 93 cannot be close to the other piston piece 93 under the action of the buffer rod 94, the other piston piece 93 moves towards the direction of the agent outlet holes, and the lubricant is extruded out, so that the lubricant is discharged through the lubricant holes of the first sliding rail 113 and the second sliding rail 115, and the lubricant is entrained in the movement process of the sliding block 121 and the locking hook roller, so that the smoothness of the movement of the sliding block 121 and the locking hook roller is improved;
when the single test is completed, the magnetic block 122 does not act on the rod body 81 of the trigger piece 8, the piston assembly moves to the side of the connecting pipe 61 under the restoring force of the sleeve spring 83, during the resetting, the piston plate 93 moves to the side of the connecting pipe 61, and the air outlet hole is positioned at the end part of the sleeve 82, so that the residual pressure air in the sleeve 82 is discharged through the air outlet hole during the resetting, then the other piston plate 93 moves backwards under the pulling of the buffer rod 94, and the lubricant in the lubricant storage bin 7 is pumped into the sleeve 82 through the lubricant supplementing hole and the pipeline, so that the resetting of the purging lubrication mechanism is completed; during which the pressure value in the pressure tank 5 can be monitored by means of a pressure gauge and the pressure in the pressure tank 5 can be compensated by means of a booster air pump.
Example 3: the difference between this embodiment and embodiment 2 is that, as shown in fig. 14 and 15, a buffer air bag ring 51 is provided on the round hole 114, six return springs are provided in the buffer air bag ring 51, the buffer air bag ring 51 is communicated with the pressure air tank 5 through a pipe, an air compensating port is provided on the buffer air bag ring 51, a one-way valve is provided at the joint of the buffer air bag ring 51 and the pipe, and a one-way valve is provided on the air compensating port.
The working principle of the buffer air bag ring 51 is as follows: when the lock hook 14 releases the lock core 13, the lock core 13 rapidly presses the buffer air bag ring 51 under pulling, so that the air in the buffer air bag ring 51 is pressed into the pressure air tank 5, and under the action of the one-way valve, the buffer air bag ring 51 carries out one-way air intake to the pressure air tank 5, and at the same time, the air intake recovery of the buffer air bag ring 51 is carried out through the air supplementing port.
Claims (9)
1. The utility model provides an aircraft ground intensity shimmy test front wheel angular displacement interferes excitation device, includes padlock unhooking mechanism (1), wire rope (2), guide pulley (3) and connecting seat (4), padlock unhooking mechanism (1) one end with connecting seat (4) butt joint, padlock unhooking mechanism (1) the other end with wire rope (2) are connected, and wire rope (2) bypass guide pulley (3) and with the wheel shaft connection of aircraft landing gear, characterized in that padlock unhooking mechanism (1) include base (11), bear slip table (12), lock core (13), latch hook (14), servo cylinder (15) and unhook trigger mechanism;
the bearing sliding table (12) is positioned in the base (11) and is in sliding connection with the base (11), the base (11) is a rectangular frame body formed by two long plates (111) and two short plates (112), the inner walls of the two long plates (111) are respectively provided with a first sliding rail (113), the side wall of the bearing sliding table (12) is provided with a sliding block (121) which is in sliding connection with the first sliding rails (113),
the lock core (13) passes through a round hole (114) arranged on one of the short plates (112) and is connected with the steel wire rope (2), two lock hooks (14) are symmetrically arranged above the bearing sliding table (12) by taking the lock core (13) as a symmetrical axis, the middle part of each lock hook (14) is rotationally connected with the bearing sliding table (12) through a pin shaft, one end of each lock hook (14) is clamped with the lock core (13), the other end of each lock hook (14) is provided with a rotating rocker arm (16), a compression spring (17) is arranged between the two rotating rocker arms (16), the compression springs (17) are hinged with the rotating rocker arms (16),
the unhooking trigger mechanism is provided with two groups and corresponds with the latch hook (14) one by one, the unhooking trigger mechanism comprises a spring damper (18), a trigger switch (19) and a series spring (10), the servo oil cylinder (15) and the spring damper (18) are both arranged on the other inner wall of the short plate (112), the output end of the servo oil cylinder (15) is connected with the bearing sliding table (12), the trigger switch (19) is connected with the output end of the spring damper (18), the trigger switch (19) is connected with the bearing sliding table (12) through the series spring (10), and a deflector rod (191) for pulling and linking the latch hook (14) to release the latch core (13) by using the trigger switch (19) is arranged on the rotating rocker arm (16).
2. An aircraft ground intensity shimmy test front wheel angular displacement interference excitation device according to claim 1, wherein the round hole (114) is provided with a buffer rubber block.
3. The device for the interference excitation of the angular displacement of the front wheel of the aircraft ground intensity shimmy test according to claim 1, characterized in that the rotating rocker arm (16) is provided with a latch hook roller, and the inner walls of the two long plates (111) are respectively provided with a second slide rail (115) for sliding connection with the latch hook roller.
4. The device for interfering with the angular displacement of the front wheel of the aircraft ground intensity shimmy test according to claim 1, wherein the cross section of the first sliding rail (113) is trapezoidal, and the sliding block (121) is provided with a trapezoidal groove which is matched with the first sliding rail (113).
5. An aircraft ground intensity shimmy test front wheel angular displacement interference excitation device according to claim 1, characterized in that the outer walls of both long plates (111) are provided with clamping strips (116) for interfacing with the connection seats (4).
6. An aircraft ground intensity shimmy test front wheel angular displacement interference excitation device according to claim 3, wherein a group of purging lubrication mechanisms for purging the first slide rail (113) and the second slide rail (115) and applying lubricant are arranged on the inner walls of the two long plates (111) between the first slide rail (113) and the second slide rail (115),
the purging lubrication mechanism consists of a pressure gas tank (5), a gas transmission main pipe (6), a storage agent bin (7), a plurality of trigger pieces (8) and a release pipe (9), wherein the pressure gas tank (5) is arranged on a base (11), the gas transmission main pipe (6) is buried in an inner cavity of a long plate (111) and is communicated with the pressure gas tank (5), the release pipe (9) is buried in inner cavities of a first sliding rail (113) and a second sliding rail (115) at equal intervals, the release pipe (9) is communicated with the gas transmission main pipe (6) through a connecting pipe (61), the trigger pieces (8) are connected to the connecting pipe (61),
the triggering piece (8) is composed of a rod body (81) and a sleeve (82), an air inlet and an air outlet which are used for being communicated with the connecting pipe (61) are arranged on the side wall of the sleeve (82), the rod body (81) is composed of a magnetic column used for driving the rod body (81) to move and a piston column used for controlling the connecting pipe (61) to be connected or closed, the piston column is in sliding sealing connection with the sleeve (82), a sleeve spring (83) connected with the bottom of the sleeve (82) is arranged on the piston column,
the release pipe (9) is composed of a pipe body (91) and a piston assembly, one end face of the pipe body (91) is communicated with the connecting pipe (61), the other end face of the pipe body (91) is provided with a reagent outlet hole and a reagent supplementing hole, the side face of the pipe body (91) is provided with a gas outlet hole, the piston assembly is arranged in the pipe body (91) and consists of two piston sheets (93) and a buffer rod (94) for delay triggering of the two piston sheets (93), the two piston sheets (93) are correspondingly connected with two ends of the buffer rod (94), one piston sheet (93) is provided with a pipe body spring (92) connected with the bottom of the pipe body (91),
the lubricant outlet hole corresponds to lubricant holes formed in the first sliding rail (113) and the second sliding rail (115), the air outlet hole corresponds to air blowing holes formed in the first sliding rail (113) and the second sliding rail (115), the lubricant supplementing hole is communicated with the lubricant storage bin (7) through a pipeline, and the bearing sliding table (12) is provided with a magnetic block (122) used for being matched with the magnetic column to drive the rod body (81) to move.
7. The device for exciting the angular displacement interference of the front wheel of the aircraft ground intensity shimmy test according to claim 6, wherein the buffer rod (94) consists of an inner tube (941) and an outer tube (942), the inner tube (941) is slidably connected with the outer tube (942), a flange (943) and a baffle ring (944) are correspondingly arranged on the butt joint end surface of the outer tube (942) and the inner end surface of the inner tube (941) and the inner end surface of the outer tube (942) are respectively provided with a magnetic sheet.
8. The device for interfering and exciting the angular displacement of the front wheel for the aircraft ground intensity shimmy test according to claim 6, wherein the round hole (114) is provided with a buffer air bag ring (51), a plurality of return springs are arranged in the buffer air bag ring (51), the buffer air bag ring (51) is communicated with the pressure air tank (5) through a pipeline, the buffer air bag ring (51) is provided with an air supplementing port, the joint of the buffer air bag ring (51) and the pipeline is provided with a one-way valve, and the air supplementing port is provided with the one-way valve.
9. An aircraft ground intensity shimmy test front wheel angular displacement interference excitation device according to claim 6, characterized in that the top surface of the pressure gas tank (5) is provided with a pressure gauge and a booster air pump.
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| CN202311175124.9A CN116946386B (en) | 2023-09-13 | 2023-09-13 | Front wheel angular displacement interference excitation device for aircraft ground intensity shimmy test |
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| CN202311175124.9A CN116946386B (en) | 2023-09-13 | 2023-09-13 | Front wheel angular displacement interference excitation device for aircraft ground intensity shimmy test |
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| CN116946386B (en) | 2023-12-12 |
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