CN117125267B - Impact power performance test system and method for landing gear of carrier-based aircraft - Google Patents
Impact power performance test system and method for landing gear of carrier-based aircraft Download PDFInfo
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- CN117125267B CN117125267B CN202311400409.8A CN202311400409A CN117125267B CN 117125267 B CN117125267 B CN 117125267B CN 202311400409 A CN202311400409 A CN 202311400409A CN 117125267 B CN117125267 B CN 117125267B
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- 238000011056 performance test Methods 0.000 title claims description 14
- 238000012360 testing method Methods 0.000 claims abstract description 226
- 230000001133 acceleration Effects 0.000 claims abstract description 217
- 238000007405 data analysis Methods 0.000 claims abstract description 4
- 238000012544 monitoring process Methods 0.000 claims abstract description 4
- 230000001052 transient effect Effects 0.000 claims description 73
- 238000004146 energy storage Methods 0.000 claims description 15
- 238000013016 damping Methods 0.000 claims description 6
- 230000035939 shock Effects 0.000 claims description 6
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
Abstract
The invention discloses a system and a method for testing the impact power performance of a carrier-based aircraft landing gear, wherein the system comprises an electromagnetic acceleration track, a GTO control cabinet and a slipway trolley; the method comprises the following steps: s1, equipment homing; s2, vibration testing; s3, data monitoring; s4, data analysis. The invention can verify the test precision and test capability of test equipment before the test of the relevant working condition of the impact power performance of the formal landing gear, mainly verifies the mass of the largest wedge-shaped test piece which can be carried by the selected electromagnetic acceleration rail, can achieve the maximum acceleration, combines the mass of the wedge-shaped test piece with the maximum acceleration amplitude, determines the maximum test capability of the selected electromagnetic acceleration rail, and has important reference value for the preset parameter selection and test data processing of the formal working condition.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a system and a method for testing the impact power performance of a landing gear of a carrier-based aircraft.
Background
The landing gear of the aircraft is an important component for the aircraft to finish taking off and landing, and particularly, the landing gear is a critical structure for the carrier-based aircraft, which determines whether the carrier-based aircraft can maintain good performance in taking off and landing processes, wherein the impact power performance is one of important indexes for evaluating the performance of the landing gear (landing gear, arresting hook and arresting rope).
The impact power performance of the landing gear mainly comprises a landing performance, a shimmy prevention performance, a running obstacle crossing performance and the like, and the impact power performance of the blocking hook mainly comprises a landing impact performance, a rope collision impact performance and the like. In the existing indoor aircraft test, a high-speed impact mode is generally adopted to simulate landing gear running obstacle crossing, blocking hook landing impact, blocking hook rope impact and the like, the test is carried out by accelerating a simulated structural member of an impacted object (such as an obstacle boss, a deck wedge block, a blocking rope and the like), and then the simulated structural member impacts a test piece (landing gear or blocking hook) in a test area, so that various parameters are measured, the impact power performance and the driving force of the test piece are verified, and the electromagnetic ejection driving mode is a common indoor aircraft test driving mode in the recent field, particularly in the unit of the applicant.
However, the electromagnetic ejection driving mode has high test energy and high speed, the test environment is complex, and the test piece is difficult to accurately reach the specified speed at the specified position, so that the test precision and the test capability of the equipment are required to be verified before the test, the test piece is ensured to be accelerated to the specified speed in an acceleration area, and the acceleration performance and the like of the test piece can be ensured in what range according to the quality, the frequency and the acceleration.
Disclosure of Invention
Aiming at the problems, the invention provides a system and a method for testing the impact power performance of a landing gear of a carrier-based aircraft.
The technical scheme of the invention is as follows:
the system comprises an electromagnetic acceleration track, a GTO control cabinet and a slipway trolley;
the electromagnetic acceleration track sequentially comprises the following steps from left to right according to the functional segmentation: the device comprises a rotor parking area, an electromagnetic acceleration area, an electromagnetic deceleration area and a hydraulic braking area, wherein a linear motor rotor capable of sliding along an electromagnetic acceleration track is arranged in the rotor parking area, a sliding table trolley is borne above the linear motor rotor, a wedge-shaped test piece is arranged on the upper surface of the sliding table trolley, a strain gauge is adhered to the contact surface between the bottom of the wedge-shaped test piece and the sliding table trolley, and an acceleration sensor is arranged at the rear end of the wedge-shaped test piece;
the GTO control cabinet is characterized in that an energy storage cabinet is arranged on one side of the GTO control cabinet, the energy storage cabinet is electrically connected with the GTO control cabinet through a cable, and the energy storage cabinet is electrically connected with the linear motor rotor through a cable.
Further, a hydraulic brake is arranged outside the electromagnetic acceleration track in the hydraulic braking area, and an emergency deceleration wall is arranged at the tail end of the electromagnetic acceleration track.
Description: the sliding table trolley can be ensured to smoothly brake by the double-deceleration braking of the hydraulic brake and the emergency deceleration wall.
Further, a PLC controller, a data collector and an industrial personal computer are arranged inside the GTO control cabinet, and an operating console is arranged outside the front surface of the GTO control cabinet.
Description: the control of the sliding table trolley is completed through the PLC inside the GTO control cabinet, and the operation of the staff is facilitated through the control console.
The invention also provides a method for testing the impact power performance of the landing gear of the carrier-based aircraft, which is based on the system for testing the impact power performance of the landing gear of the carrier-based aircraft and comprises the following steps:
s1, equipment homing: fixedly mounting a sliding table trolley and a linear motor rotor at the leftmost side of a rotor parking area of an electromagnetic acceleration track, wherein the mass ism 1 The wedge-shaped test piece is fixedly arranged on the sliding table trolley, and a strain gauge and an acceleration sensor are arranged on the wedge-shaped test piece;
s2, vibration test: the GTO control cabinet is used for applying sinusoidal damping shock waves to the linear motor rotor, and meanwhile the energy storage cabinet is used for releasing electric energy to drive the linear motor rotor to complete electromagnetic ejection, so that the linear motor rotor drives the sliding table trolley and the wedge-shaped test piece to move along the electromagnetic acceleration zone, and theoretical acceleration of the sliding table trolley and the wedge-shaped test piece is calculated according to the following formula:
，
in the method, in the process of the invention,yis thattTheoretical acceleration of the trolley and the wedge-shaped test piece of the moment slipway;A m the amplitude of transient wave is given in g, and the initial value is given asA m1 ；εTaking 0.025 as damping ratio;ωfor the modal circle frequency, take 2rad/s；T e For a limited duration of the shock waveform, take 2s,tthe movement time of the sliding table trolley and the wedge-shaped test piece is set;
when the moving time of the sliding table trolley exceeds 2s, the sliding table trolley enters an electromagnetic deceleration area and a hydraulic braking area to perform deceleration braking;
s3, data monitoring: obtained by data statisticstTheoretical acceleration within 0-2 syChange curve and taket=0.5s、t=1s、t=1.5 s sumtTheoretical acceleration of 4 times total of 2syThe actual measurement acceleration of the sliding table trolley and the wedge-shaped test piece, which are measured by the acceleration sensor, at the 4 moments is collected through the GTO control cabinetaAnd the measured acceleration at 4 timesaWith theoretical acceleration at 4 momentsyComparing the two images in a one-to-one correspondence manner, and calculating to obtain acceleration errors at 4 momentsE 1 =︱y-a︱/a；
S4, data analysis:
s4-1, analyzing the maximum transient wave amplitude which can be applied under the mass of the initial wedge-shaped test piece and the maximum acceleration which can be achieved by the wedge-shaped test piece under the maximum transient wave amplitude;
s4-2, analyzing the mass of the maximum wedge-shaped test piece which can be achieved under the initial transient wave amplitude and the maximum acceleration which can be achieved under the mass of the maximum wedge-shaped test piece;
s4-3, comprehensively analyzing and synchronously increasing the mass of the wedge-shaped test piece and the maximum acceleration which can be achieved by the wedge-shaped test piece after the transient wave amplitude.
Further, the method of the step S4-1 is as follows:
s4-1-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-1-2, if any acceleration error exists at any timeE 1 More than 3%, the corresponding mass ism 1 The transient wave amplitude of the wedge-shaped test piece isA m1 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that the wedge-shaped test piece can reach in the real test process;
s4-1-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the amplitude of transient wave is increased toA m2 The operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, the corresponding mass ism 1 The transient wave amplitude of the wedge-shaped test piece isA m2 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that the wedge-shaped test piece can reach in the real test process;
s4-1-4, acceleration error at 4 timesE 2 All are less than or equal to 3 percent, the transient wave amplitude is improved againA m And repeating the process of S4-1-3 until the transient wave amplitudeA mn Acceleration errors of corresponding 4 momentsE n At least one measured acceleration of > 3% at 4 momentsaThe maximum value of (i) is massm 1 The maximum acceleration that can be achieved by the wedge-shaped test piece during the actual test,A mn =1.5*A mn-1 。
description: the quality of the wedge-shaped test piece is controlled to be unchanged, and the transient wave amplitude is gradually improved, so that the maximum acceleration which can be achieved by the wedge-shaped test piece with the quality is obtained, and the accuracy of the test on the transient wave amplitude is ensured by optimizing the amplitude of the transient wave which is increased each time.
Further, the method of the step S4-2 is as follows:
s4-2-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-2-2, if any acceleration error exists at any timeE 1 More than 3%, corresponding to transient wave amplitudeA m1 The maximum mass of the lower alternative wedge-shaped test piece ism 1 At this time, the measured acceleration at 4 moments is screened outaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism 1 ；
S4-2-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece is improved tom 2 The operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, corresponding to transient wave amplitudeA m1 The maximum mass of the lower alternative wedge-shaped test piece ism 2 At this time, the measured acceleration at 4 moments is screened outaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism 2 ；
S4-2-4, acceleration error at 4 timesE 2 And the quality of the wedge-shaped test piece is improved again and the process of S4-2-3 is repeated until the quality of the wedge-shaped test piece is reachedm n Acceleration errors of corresponding 4 momentsE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA m1 The maximum mass of the lower alternative wedge-shaped test piece ism n At this time, the measured acceleration at 4 moments is screened outaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism n ，m n =2*m n-1 。
Description: the quality of the wedge-shaped test piece is gradually improved by controlling the transient wave amplitude to be unchanged, so that the maximum quality of the alternative wedge-shaped test piece under a certain maximum acceleration condition is obtained, and the accuracy of the test on the quality of the wedge-shaped test piece is ensured by optimizing the quality of the wedge-shaped test piece which is increased each time.
Further, the method of the step S4-3 is as follows:
S4-3-1, analyzing the acceleration errors at 4 moments calculated in step S3E 1 ；
S4-3-2, if any acceleration error exists at any timeE 1 More than 3%, the measured acceleration at 4 times is selectedaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism 1 ；
S4-3-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece is improved tom 2 ' simultaneously increasing transient wave amplitude toA m2 ' the operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, corresponding to transient wave amplitudeA m2 Maximum mass of the' lower alternative wedge test piece ism 2 ' at this time, the measured accelerations at 4 moments are screened outaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism 2 ′；
S4-3-4, acceleration error at 4 timesE 2 If the two values are less than or equal to 3 percent, the quality of the wedge-shaped test piece is improved again, the transient wave amplitude is improved, and the process of S4-3-3 is repeated until the quality of the wedge-shaped test piece is reachedm n ' at transient wave amplitudeA mn Acceleration error at corresponding 4 moments under' conditionE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA mn Maximum mass of the' lower alternative wedge test piece ism n ' at this time, the measured accelerations at 4 moments are screened outaMaximum value of (2) for which the maximum mass of the alternative wedge test piece under the maximum acceleration condition ism n ′，A mn ′=1.2*A mn-1 ′，m n ′=1.6*m n-1 ′。
Description: the mass and the transient wave amplitude of the wedge-shaped test piece are improved, and the magnitude of the transient wave amplitude and the mass of the wedge-shaped test piece which are added each time are optimized, so that the optimal critical value of the test device can be reasonably judged, and the maximum achievable mass and acceleration of the wedge-shaped test piece are obtained.
Further, in the step S1m 1 10kg, in the step S2A m1 5g, 9.8 gm/s 2 。
Description: by preference ofm 1 The size of (2) indicates that the minimum mass of the wedge-shaped test piece is not less than 10kg, and the wedge-shaped test piece is preferableA m1 The wedge-shaped test piece can be ensured to be subjected to transient wave amplitude, and the problem that the test error is overlarge due to overlarge transient wave amplitude is avoided.
The beneficial effects of the invention are as follows:
(1) The impact power performance test system of the carrier-based aircraft landing gear accelerates the slipway trolley through the electromagnetic ejection technology, has the advantages of large energy storage capacity and controllable speed, can rapidly accelerate the slipway trolley to a preset speed in a short time, has high speed precision, and only needs to adjust the energy storage capacity if the waveform amplitude is to be adjusted;
(2) According to the impact power performance test system of the carrier-based aircraft landing gear, three layers of deceleration areas are arranged behind the electromagnetic acceleration track, so that potential safety hazards in the test process can be effectively reduced, the three layers of deceleration areas are buckled, the electromagnetic deceleration areas are conventional deceleration areas, and the linear motor rotor and the slipway trolley are decelerated to 0 from a high-speed motion state through reverse electromagnetic force; if the electromagnetic speed reduction fails or the rotor is not completely decelerated, the hydraulic braking system starts to work; if the hydraulic braking system still does not completely brake the rotor, the sliding table trolley can strike an emergency speed reducing wall to carry out emergency braking, the impact strength of the emergency speed reducing device can meet the braking requirement, and the test system is not damaged on the premise of completely braking the sliding table trolley;
(3) The test method for the impact power performance of the carrier-based aircraft landing gear can verify the test precision and the test capability of test equipment before the test of the relevant working conditions of the impact power performance of the formal landing gear, mainly verifies the mass of the largest wedge-shaped test piece which can be carried by the selected electromagnetic acceleration track, the maximum acceleration which can be achieved, and the combination of the mass of the wedge-shaped test piece and the maximum acceleration amplitude, determines the maximum test capability of the selected electromagnetic acceleration track, and has important reference value for the preset parameter selection and test data processing of the formal working conditions;
(4) According to the method for testing the impact power performance of the carrier-based aircraft landing gear, the quality of the wedge-shaped test piece is controlled to be unchanged, and the transient wave amplitude is gradually improved, so that the maximum acceleration which can be achieved by the wedge-shaped test piece with the quality is obtained; the quality of the wedge-shaped test piece is gradually improved by controlling the transient wave amplitude to be unchanged, so that the maximum quality of the alternative wedge-shaped test piece under a certain maximum acceleration condition is obtained; the quality and the transient wave amplitude of the wedge-shaped test piece are improved at the same time, and the amplitude of the transient wave and the quality of the wedge-shaped test piece which are increased each time are optimized, so that the optimal critical value of the test device can be reasonably judged, the maximum achievable quality and acceleration of the wedge-shaped test piece are obtained, and the three analysis modes can be cross-referenced, so that a more accurate test result can be obtained in the impact power performance test of the formal landing gear.
Drawings
FIG. 1 is a schematic diagram of the overall structure of an impact power performance test system of a landing gear of a carrier-based aircraft;
FIG. 2 is a schematic diagram of the structure of a slipway trolley in the impact power performance test system of the carrier-based aircraft landing gear of the invention;
FIG. 3 is a side view of an electromagnetic acceleration rail in the impact power performance test system of the landing gear of the carrier-based aircraft of the present invention;
FIG. 4 is a front view and an electromagnetic acceleration orbit division diagram of the carrier-based aircraft landing gear impact power performance test system of the present invention in a formal test;
FIG. 5 is a flow chart of a method for testing the impact power performance of the landing gear of the carrier-based aircraft of the invention;
the device comprises a 1-electromagnetic acceleration track, a 11-rotor parking area, a 12-electromagnetic acceleration area, a 13-electromagnetic deceleration area, a 14-hydraulic braking area, a 15-linear motor rotor, a 16-hydraulic brake, a 17-emergency deceleration wall, a 2-GTO control cabinet, a 3-sliding table trolley, a 4-wedge-shaped test piece, a 41-strain gauge, a 42-acceleration sensor and a 5-energy storage cabinet.
Detailed Description
Example 1: as shown in FIG. 1, the impact power performance test system of the carrier-based aircraft landing gear comprises an electromagnetic acceleration track 1, a GTO control cabinet 2 and a slipway trolley 3;
as shown in fig. 2 to 4, the electromagnetic acceleration track 1 is sequentially from left to right according to the functional segmentation: the device comprises a rotor parking area 11, an electromagnetic acceleration area 12, an electromagnetic deceleration area 13 and a hydraulic braking area 14, wherein a linear motor rotor 15 capable of sliding along an electromagnetic acceleration track 1 is arranged in the rotor parking area 11, a hydraulic brake 16 is arranged outside the electromagnetic acceleration track 1 in the hydraulic braking area 14, an emergency deceleration wall 17 is arranged at the tail end of the electromagnetic acceleration track 1, a sliding table trolley 3 is borne above the linear motor rotor 15, a wedge-shaped test piece 4 is arranged on the upper surface of the sliding table trolley 3, a strain gauge 41 is stuck to the contact surface between the bottom of the wedge-shaped test piece 4 and the sliding table trolley 3, and an acceleration sensor 42 is arranged at the rear end of the wedge-shaped test piece 4;
as shown in fig. 1, an energy storage cabinet 5 is arranged on one side of the GTO control cabinet 2, the energy storage cabinet 5 is electrically connected with the GTO control cabinet 2 through a cable, the energy storage cabinet 5 is electrically connected with a linear motor rotor 15 through a cable, a PLC controller, a data collector and an industrial personal computer are arranged inside the GTO control cabinet 2, and an operation console is arranged outside the front surface of the GTO control cabinet 2.
Example 2: the embodiment describes a method for testing the impact power performance of a landing gear of a carrier-based aircraft, and a system for testing the impact power performance of the landing gear of the carrier-based aircraft based on embodiment 1, as shown in fig. 5, comprises the following steps:
s1, equipment homing: fixedly mounting the sliding table trolley 3 and the linear motor rotor 15 at the leftmost side of the rotor parking area 11 of the electromagnetic acceleration track 1, wherein the mass ism 1 The wedge-shaped test piece 4 of the test piece is fixedly arranged on the sliding table trolley 3, the strain gauge 41 and the acceleration sensor 42 are arranged on the wedge-shaped test piece 4,m 1 10kg;
s2, vibration test: sinusoidal damping shock waves are applied to the linear motor rotor 15 through the GTO control cabinet 2, meanwhile, the energy storage cabinet 5 releases electric energy to drive the linear motor rotor 15 to complete electromagnetic ejection, so that the linear motor rotor 15 drives the sliding table trolley 3 and the wedge-shaped test piece 4 to move along the electromagnetic acceleration zone 12, and theoretical acceleration of the sliding table trolley 3 and the wedge-shaped test piece 4 is calculated according to the following formula:
，
in the method, in the process of the invention,yis thattTheoretical acceleration of the sliding table trolley 3 and the wedge-shaped test piece 4 at the moment;A m the amplitude of transient wave is given in g, and the initial value is given asA m1 ，A m1 5g, 9.8 gm/s 2 ；εTaking 0.025 as damping ratio;ωfor the modal circle frequency, take 2rad/s；T e For a limited duration of the shock waveform, take 2s,tthe movement time of the sliding table trolley 3 and the wedge-shaped test piece 4 is set;
when the movement time of the sliding table trolley 3 exceeds 2s, the sliding table trolley enters an electromagnetic deceleration area 13 and a hydraulic braking area 14 to perform deceleration braking;
s3, data monitoring: obtained by data statisticstTheoretical acceleration within 0-2 syChange curve and taket=0.5s、t=1s、t=1.5 s sumtTheoretical acceleration of 4 times total of 2syThe actual measurement acceleration of the sliding table trolley 3 and the wedge-shaped test piece 4 measured by the acceleration sensor 42 at the 4 moments is collected by the GTO control cabinet 2aAnd the measured acceleration at 4 timesaWith theoretical acceleration at 4 momentsyComparing the two images in a one-to-one correspondence manner, and calculating to obtain acceleration errors at 4 momentsE 1 =︱y-a︱/a；
S4, data analysis:
s4-1, analyzing the maximum transient wave amplitude which can be applied under the mass of the initial wedge-shaped test piece 4 and the maximum acceleration which can be achieved by the wedge-shaped test piece 4 under the maximum transient wave amplitude;
s4-2, analyzing the mass of the maximum wedge-shaped test piece 4 which can be achieved under the initial transient wave amplitude and the maximum acceleration which can be achieved under the mass of the maximum wedge-shaped test piece 4;
s4-3, comprehensively analyzing and synchronously increasing the mass of the wedge-shaped test piece 4 and the maximum acceleration which can be achieved by the wedge-shaped test piece 4 after transient wave amplitude;
the method of the step S4-1 is as follows:
s4-1-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-1-2, if any acceleration error exists at any timeE 1 More than 3%, the corresponding mass ism 1 The transient wave amplitude of wedge-shaped test piece 4 of (2) isA m1 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece 4 during the real test;
s4-1-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the amplitude of transient wave is increased toA m2 The operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, the corresponding mass ism 1 The transient wave amplitude of wedge-shaped test piece 4 of (2) isA m2 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece 4 during the real test;
s4-1-4, acceleration error at 4 timesE 2 All are less than or equal to 3 percent, the transient wave amplitude is improved againA m And repeating the process of S4-1-3 until the transient wave amplitudeA mn Acceleration errors of corresponding 4 momentsE n At least one measured acceleration of > 3% at 4 momentsaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece 4 during the actual test,A mn =1.5*A mn-1 ；
the method of the step S4-2 is as follows:
s4-2-1, calculating in the analysis step S3Acceleration error of 4 times obtainedE 1 ；
S4-2-2, if any acceleration error exists at any timeE 1 More than 3%, corresponding to transient wave amplitudeA m1 The maximum mass of the lower alternative wedge-shaped test piece 4 ism 1 At this time, the measured acceleration at 4 moments is screened outaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm 1 ；
S4-2-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece 4 is improved to bem 2 The operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, corresponding to transient wave amplitudeA m1 The maximum mass of the lower alternative wedge-shaped test piece 4 ism 2 At this time, the measured acceleration at 4 moments is screened outaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm 2 ；
S4-2-4, acceleration error at 4 timesE 2 And is less than or equal to 3 percent, the quality of the wedge-shaped test piece 4 is improved again and the process of S4-2-3 is repeated until the quality of the wedge-shaped test piece 4 is reachedm n Acceleration errors of corresponding 4 momentsE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA m1 The maximum mass of the lower alternative wedge-shaped test piece 4 ism n At this time, the measured acceleration at 4 moments is screened outaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm n ，m n =2*m n-1 。
The method of the step S4-3 is as follows:
s4-3-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-3-2, if any acceleration error exists at any timeE 1 More than 3%, the measured acceleration at 4 times is selectedaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm 1 ；
S4-3-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece 4 is improved to bem 2 ' simultaneously increasing transient wave amplitude toA m2 ' the operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, corresponding to transient wave amplitudeA m2 The maximum mass of the' lower alternative wedge test piece 4 ism 2 ' at this time, the measured accelerations at 4 moments are screened outaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm 2 ′；
S4-3-4, acceleration error at 4 timesE 2 And the quality of the wedge-shaped test piece 4 is improved again and the transient wave amplitude is improved, and the process of S4-3-3 is repeated until the quality of the wedge-shaped test piece 4 is reachedm n ' at transient wave amplitudeA mn Acceleration error at corresponding 4 moments under' conditionE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA mn The maximum mass of the' lower alternative wedge test piece 4 ism n ' at this time, the measured accelerations at 4 moments are screened outaUnder which the maximum mass of the wedge-shaped test piece 4 is the maximum value ofm n ′，A mn ′=1.2*A mn-1 ′，m n ′=1.6*m n-1 ′。
Test example: the field test was performed in the same manner as in example 2, and the test was divided into 3 groups, wherein the first group was performed in accordance with step S4-1, the second group was performed in accordance with step S4-2, and the third group was performed in accordance with step S4-3.
A first group: the 10kg wedge test piece 4 was tested at a transient wave amplitude of 5g as follows:
ttheoretical acceleration =0.5 sy=43.83m/s 2 Measured accelerationa=43.06m/s 2 Strain 0.009, errorE 1 =1.78%；
t=1s, theoretical accelerationy=46.19m/s 2 Measured accelerationa=45.41m/s 2 Strain 0.018, errorE 1 =1.71%；
tTheoretical acceleration =1.5sy=6.99m/s 2 Measured accelerationa=6.88m/s 2 Strain 0.002, errorE 1 =1.59%；
t=2s, theoretical accelerationy=-36.57m/s 2 Measured accelerationa=-37.44m/s 2 Strain 0.013, errorE 1 =2.32%；
The acceleration error at 4 moments can be seenE 1 All are less than or equal to 3 percent, and the amplitude of transient waves is improved toA m2 To 7.5g, continue to calculate and monitor the theoretical accelerationyAnd measured accelerationaObtaining acceleration errors at 4 momentsE 2 The amplitude of transient waves is increased again and is equal to or less than 3 percentA m3 To 11.25g, continue to calculate and monitor the theoretical accelerationyAnd measured accelerationaFound at this timetWhen=1s, theoretical accelerationy=95.36m/s 2 Measured accelerationa=91.54m/s 2 Error ofE 3 =3.82% > 3%, while the acceleration maximum is alsotMeasured acceleration at=1saThus, the maximum acceleration that can be achieved during the actual test for a wedge-shaped test piece 4 with a mass of 10kg is 91.54m/s 2 ；
Second group: the 10kg wedge-shaped test piece 4 detects the same result as the acceleration error at 4 moments under the amplitude of 5g transient waveE 1 All are less than or equal to 3 percent, and the quality of the wedge-shaped test piece 4 is improvedm 2 To 20kg, continue to calculate and monitor the theoretical accelerationyAnd measured accelerationaObtaining acceleration errors at 4 momentsE 2 The quality of the wedge-shaped test piece 4 is increased again until the wedge-shaped test piece 4 is reached, wherein the quality is equal to or less than 3 percentQuality of (2)m 4 To 80kg at this timetWhen=2s, theoretical accelerationy=-36.57m/s 2 Measured accelerationa=-38.21m/s 2 Error ofE 4 =4.29% > 3% with maximum acceleration oftMeasured acceleration at=1sa=45.58m/s 2 Thus, the maximum acceleration that can be reached by a wedge-shaped test piece 4 with a mass of 80kg during the actual test is 45.58m/s 2 An alternative maximum mass under this acceleration condition is 80kg;
third group: the 10kg wedge-shaped test piece 4 detects the same result as the acceleration error at 4 moments under the amplitude of 5g transient waveE 1 All are less than or equal to 3 percent, and the quality of the wedge-shaped test piece 4 is improvedm 2 ' to 16kg, increase transient wave amplitudeA m2 ' to 6g, continuing to calculate and monitor theoretical accelerationyAnd measured accelerationaObtaining acceleration errors at 4 momentsE 2 The quality of the wedge-shaped test piece 4 is improved again, wherein the quality is equal to or less than 3 percentm 3 ' to 25.6kg, increase transient wave amplitudeA m3 ' to 7.2g, continuing to calculate and monitor theoretical accelerationyAnd measured accelerationaFound at this timetWhen=1.5 s, theoretical accelerationy=9.23m/s 2 Measured accelerationa=8.69m/s 2 Error ofE 3 =6.21% > 3% with maximum acceleration oftMeasured acceleration at=1sa=61.94m/s 2 Thus, the maximum acceleration that can be reached by a wedge-shaped test piece 4 with a mass of 25.6kg during the actual test is 61.94m/s 2 An alternative maximum mass under this acceleration condition is 25.6kg;
as can be seen from the above data, the maximum acceleration that can be achieved in a real test run of wedge-shaped test piece 4 with a mass of 10kg is 91.54m/s 2 The method comprises the steps of carrying out a first treatment on the surface of the At 45.58m/s 2 An alternative maximum mass under acceleration conditions is 80kg; at 61.94m/s 2 An alternative maximum mass under acceleration conditions is 25.6kg; therefore, the combination of three groups of data conclusions can know that the carrier-based aircraft landing gear impact power performanceThe acceleration precision of the test system can ensure whether the wedge-shaped test piece 4 with specified mass and the sliding table trolley 3 accelerate to the speed required by specified requirements in the electromagnetic acceleration area 12, when the formal impact power performance test is carried out, the wedge-shaped test piece 4 with proper mass is selected according to the requirements, and the proper acceleration is controlled so that the sliding table trolley 3 drives the wedge-shaped test piece 4 to reach the set speed within a small error range when reaching the impact position.
Claims (7)
1. The impact power performance test method of the carrier-based aircraft landing gear is based on an impact power performance test system of the carrier-based aircraft landing gear and is characterized in that the test system comprises an electromagnetic acceleration rail (1), a GTO control cabinet (2) and a slipway trolley (3);
the electromagnetic acceleration track (1) sequentially comprises the following steps from left to right according to the functional segmentation: the device comprises a rotor parking area (11), an electromagnetic acceleration area (12), an electromagnetic deceleration area (13) and a hydraulic braking area (14), wherein a linear motor rotor (15) capable of sliding along an electromagnetic acceleration track (1) is arranged inside the rotor parking area (11), a sliding table trolley (3) is borne above the linear motor rotor (15), a wedge-shaped test piece (4) is arranged on the upper surface of the sliding table trolley (3), a strain gauge (41) is adhered to the contact surface between the bottom of the wedge-shaped test piece (4) and the sliding table trolley (3), and an acceleration sensor (42) is arranged at the rear end of the wedge-shaped test piece (4);
an energy storage cabinet (5) is arranged on one side of the GTO control cabinet (2), the energy storage cabinet (5) is electrically connected with the GTO control cabinet (2) through a cable, and the energy storage cabinet (5) is electrically connected with a linear motor rotor (15) through a cable;
the test method comprises the following steps:
s1, equipment homing: fixedly mounting a sliding table trolley (3) and a linear motor rotor (15) at the leftmost side of a rotor parking area (11) of an electromagnetic acceleration track (1), wherein the mass ism 1 The wedge-shaped test piece (4) is fixedly arranged on the sliding table trolley (3), and the strain gauge (41) and the acceleration sensor (42) are arranged on the wedge-shaped test piece (4);
s2, vibration test: sinusoidal damping shock waves are applied to the linear motor rotor (15) through the GTO control cabinet (2), meanwhile, the energy storage cabinet (5) releases electric energy to drive the linear motor rotor (15) to complete electromagnetic ejection, so that the linear motor rotor drives the sliding table trolley (3) and the wedge-shaped test piece (4) to move along the electromagnetic acceleration area (12), and theoretical acceleration of the sliding table trolley (3) and the wedge-shaped test piece (4) is calculated according to the following formula:
in the method, in the process of the invention,yis thattTheoretical acceleration of the sliding table trolley (3) and the wedge-shaped test piece (4) at the moment;A m the amplitude of transient wave is given in g, and the initial value is given asA m1 ；εTaking 0.025 as damping ratio;ωfor the modal circle frequency, take 2rad/s；T e For a limited duration of the shock waveform, take 2s,tthe movement time of the sliding table trolley (3) and the wedge-shaped test piece (4) is set;
when the movement time of the sliding table trolley (3) exceeds 2s, the sliding table trolley enters an electromagnetic deceleration area (13) and a hydraulic braking area (14) to perform deceleration braking;
s3, data monitoring: obtained by data statisticstTheoretical acceleration within 0-2 syChange curve and taket=0.5s、t=1s、t=1.5 s sumtTheoretical acceleration of 4 times total of 2syThe actual measurement acceleration of the sliding table trolley (3) and the wedge-shaped test piece (4) at the 4 moments, which are measured by the acceleration sensor (42), is collected by the GTO control cabinet (2)aAnd the measured acceleration at 4 timesaWith theoretical acceleration at 4 momentsyComparing the two images in a one-to-one correspondence manner, and calculating to obtain acceleration errors at 4 momentsE 1 =︱ y-a︱/a；
S4, data analysis:
s4-1, analyzing the maximum transient wave amplitude which can be applied under the mass of the initial wedge-shaped test piece (4) and the maximum acceleration which can be achieved by the wedge-shaped test piece (4) under the maximum transient wave amplitude;
s4-2, analyzing the mass of the maximum wedge-shaped test piece (4) which can be reached under the initial transient wave amplitude and the maximum acceleration which can be reached under the mass of the maximum wedge-shaped test piece (4);
s4-3, comprehensively analyzing and synchronously increasing the mass of the wedge-shaped test piece (4) and the maximum acceleration which can be achieved by the wedge-shaped test piece (4) after the transient wave amplitude.
2. The method for testing the impact power performance of the landing gear of the carrier-based aircraft according to claim 1 is characterized in that a hydraulic brake (16) is arranged outside the electromagnetic acceleration rail (1) located in the hydraulic braking area (14), and an emergency deceleration wall (17) is arranged at the tail end of the electromagnetic acceleration rail (1).
3. The impact power performance test method for the carrier-based aircraft landing gear according to claim 1, wherein a PLC (programmable logic controller), a data collector and an industrial personal computer are arranged inside the GTO control cabinet (2), and an operating console is arranged outside the front surface of the GTO control cabinet (2).
4. The method for testing the impact power performance of the landing gear of the carrier-based aircraft according to claim 1, wherein the method of the step S4-1 is as follows:
s4-1-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-1-2, if any acceleration error exists at any timeE 1 More than 3%, the corresponding mass ism 1 Transient wave amplitude of wedge-shaped test piece (4) of (2)A m1 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece (4) in the real test process;
s4-1-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the amplitude of transient wave is increased toA m2 The operations of steps S2 and S3 are performed again, and 4 moments are calculatedAcceleration errorE 2 If there is any acceleration error at any one timeE 2 More than 3%, the corresponding mass ism 1 Transient wave amplitude of wedge-shaped test piece (4) of (2)A m2 Measured acceleration at 4 timesaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece (4) in the real test process;
s4-1-4, acceleration error at 4 timesE 2 All are less than or equal to 3 percent, the transient wave amplitude is improved againA m And repeating the process of S4-1-3 until the transient wave amplitudeA mn Acceleration errors of corresponding 4 momentsE n At least one measured acceleration of > 3% at 4 momentsaThe maximum value of (i) is massm 1 The maximum acceleration that can be reached by the wedge-shaped test piece (4) during the actual test,A mn =1.5*A mn-1 。
5. the method for testing the impact power performance of the landing gear of the carrier-based aircraft according to claim 1, wherein the method of the step S4-2 is as follows:
s4-2-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-2-2, if any acceleration error exists at any timeE 1 More than 3%, corresponding to transient wave amplitudeA m1 The maximum mass of the lower alternative wedge-shaped test piece (4) ism 1 At this time, the measured acceleration at 4 moments is screened outaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm 1 ；
S4-2-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece (4) is improved to bem 2 The operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, then correspond toAmplitude of transient waveA m1 The maximum mass of the lower alternative wedge-shaped test piece (4) ism 2 At this time, the measured acceleration at 4 moments is screened outaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm 2 ；
S4-2-4, acceleration error at 4 timesE 2 Are all less than or equal to 3 percent, the quality of the wedge-shaped test piece (4) is improved again and the process of S4-2-3 is repeated until the quality of the wedge-shaped test piece (4)m n Acceleration errors of corresponding 4 momentsE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA m1 The maximum mass of the lower alternative wedge-shaped test piece (4) ism n At this time, the measured acceleration at 4 moments is screened outaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm n ，m n =2*m n-1 。
6. The method for testing the impact power performance of the landing gear of the carrier-based aircraft according to claim 1, wherein the method of the step S4-3 is as follows:
s4-3-1, analyzing the acceleration errors of 4 moments calculated in the step S3E 1 ；
S4-3-2, if any acceleration error exists at any timeE 1 More than 3%, the measured acceleration at 4 times is selectedaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm 1 ；
S4-3-3, acceleration error at 4 timesE 1 All are less than or equal to 3 percent, the quality of the wedge-shaped test piece (4) is improved to bem 2 ' simultaneously increasing transient wave amplitude toA m2 ' the operations of steps S2 and S3 are performed again, and the acceleration errors at 4 moments are calculatedE 2 If there is any acceleration error at any one timeE 2 More than 3%, corresponding to transient wave amplitudeA m2 ' lower alternative wedge test piece (4)Maximum mass of (2) ism 2 ' at this time, the measured accelerations at 4 moments are screened outaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm 2 ′；
S4-3-4, acceleration error at 4 timesE 2 The quality of the wedge-shaped test piece (4) is improved again and the transient wave amplitude is improved, and the process of S4-3-3 is repeated until the quality of the wedge-shaped test piece (4)m n ' at transient wave amplitudeA mn Acceleration error at corresponding 4 moments under' conditionE n At least one of which is more than 3%, corresponds to the amplitude of the transient waveA mn The maximum mass of the' lower alternative wedge-shaped test piece (4) ism n ' at this time, the measured accelerations at 4 moments are screened outaIs the maximum value of the wedge-shaped test piece (4) under the condition of the maximum accelerationm n ′，A mn ′=1.2*A mn-1 ′，m n ′=1.6*m n-1 ′。
7. The method for testing the impact power performance of the landing gear of the carrier-based aircraft according to claim 1, wherein in the step S1m 1 10kg, in the step S2A m1 5g, 9.8 gm/s 2 。
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