CN116986012B - Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft - Google Patents
Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft Download PDFInfo
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- CN116986012B CN116986012B CN202311236520.8A CN202311236520A CN116986012B CN 116986012 B CN116986012 B CN 116986012B CN 202311236520 A CN202311236520 A CN 202311236520A CN 116986012 B CN116986012 B CN 116986012B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a landing gear running obstacle-crossing impact test device and method for a carrier-based aircraft, and belongs to the technical field of landing gear running obstacle-crossing impact tests. The device comprises an equivalent mass system, a test bench, a lifting/locking system, a hinge point force sensor, a motor belt rotating system and an obstacle; the method is characterized in that the weight of an equivalent weight system is the same as the equivalent weight of an actual landing gear by increasing or decreasing the balancing weight in the hanging basket; after the equivalent mass system is lifted to a preset throwing height by a lifting/locking system and then thrown, the landing gear slides on the steel belt conveying device; and finally triggering the data acquisition equipment and measuring test data. The invention fills the blank of research on the landing gear running obstacle crossing impact test method based on the high-acceleration steel belt in laboratory environment at present, and has the advantage of being capable of verifying the running obstacle crossing capability of the landing gear.
Description
Technical Field
The invention relates to the technical field of landing gear running obstacle-crossing impact tests of aircrafts, in particular to a landing gear running obstacle-crossing impact test device and method of a carrier-based aircraft.
Background
The environment of the aircraft carrier is extremely complex, when the carrier-based aircraft slides on the aircraft carrier deck at high speed, the carrier-based aircraft can continuously pass through obstacles such as a lamp cover, a camera cover and the like, a transient large impact load can be generated to act on the aircraft body and the landing gear, and the impact load is likely to be superimposed on the already severe carrier-based load. The carrier-based aircraft can firstly generate larger impact on the landing gear in the running obstacle crossing process, so that the landing gear bears larger impact load. Second, if the obstruction creates a lateral excitation of the landing gear wheels, it may also cause the aircraft to yaw or for landing gear shimmy to occur. Therefore, impact load, overload, strut compression and the like generated on the landing gear structure when the carrier-based aircraft slides on the deck to surmount the obstacle are very important parameters for the design of the landing gear structure of the aircraft and the design of the dynamic stability of the system.
Therefore, in order to ensure the service safety and the operational performance of the carrier-based aircraft, the running obstacle crossing capability of the landing gear of the carrier-based aircraft on the ship needs to be checked in a laboratory environment, the influence of obstacle crossing load on the running obstacle crossing capability and the machine body structure of the landing gear of the carrier-based aircraft needs to be studied under different sinking speeds, obstacle crossing speeds and obstacle crossing positions of the wheels, and the running obstacle crossing capability of the landing gear needs to be checked and verified, so that test basis is provided for the life estimation and the performance design of the landing gear in the development stage of the carrier-based aircraft.
At present, the research aspect of the landing gear running obstacle crossing impact test method based on the high-acceleration steel belt in the laboratory environment is still blank, so that the research on the landing gear running obstacle crossing test method based on the high-acceleration steel belt in the laboratory environment is very important and urgent.
Disclosure of Invention
The invention solves the technical problems that: at present, research on a landing gear running obstacle surmounting impact test method based on a high-acceleration steel belt in a laboratory environment is still blank.
In order to solve the problems, the technical scheme of the invention is as follows:
the invention provides a landing gear running obstacle crossing impact test device of a carrier-based aircraft, which comprises the following components:
an equivalent mass system for simulating an equivalent mass of the landing gear, the equivalent mass system comprising the landing gear;
the test bed is used for providing an installation environment and vertical movement guidance for the equivalent mass system;
the lifting/locking system is used for lifting and releasing the equivalent mass system in the running obstacle crossing impact test process, and is arranged in the test bed;
the hinge point force sensor is used for measuring the dynamic load of the landing gear in the running obstacle crossing impact test process, and is arranged on the landing gear;
the motor belt rotating system is used for providing a running obstacle crossing environment of the equivalent mass system along the course, and is arranged at the bottom of the undercarriage;
and the barriers are used for simulating a lamp cover and/or a camera cover on the aircraft carrier deck and are arranged on the motor belt-turning system.
Further, the equivalent mass system comprises a hanging basket, a balancing weight is arranged in the hanging basket, the top of the hanging basket is fixedly connected with the lifting/locking system, a mounting hinge point is arranged at the bottom of the hanging basket, and the mounting hinge point is rotatably connected with the landing gear through a supporting clamp.
Description: the hanging basket and the balancing weight can be debugged according to the weight of different aircraft landing gears; the installation hinge point has the advantages of convenient repair and debugging and detachable assembly.
Further, a hinge point force sensor is provided between the mounting hinge point and the support jig.
Description: the dynamic load of the landing gear in the running obstacle crossing impact test process can be better detected through the hinge point force sensor arranged at the mounting hinge point.
Further, the dynamic load measured by the hinge point force sensor is divided into heading dynamic load, vertical dynamic load and lateral dynamic load.
Description: the course dynamic load measured by the hinge point force sensor can be used for analyzing the stress of the landing gear in the course; the vertical dynamic load can be used for analyzing the state of the landing gear in the test; the lateral dynamic load can be used for the stress analysis of the landing gear in heading.
Further, the lifting/locking system comprises an actuator cylinder, a release lock is fixedly connected to the bottom of the actuator cylinder, and the bottom of the release lock is magnetically connected with the equivalent mass system through an electromagnetic sheet; and a lifting motor is fixed on the test bench, and the output end of the lifting motor is connected with the actuating cylinder.
Description: the lifting/locking system is connected with the top of the hanging basket through the electromagnet sheet in a magnetic attraction manner, and can instantly release the equivalent mass system when the motor belt rotating system reaches the course speed, so that the experimental simulation effect is better.
Still further, the motor belt transfer system is placed on the supporting table, and the motor belt transfer system includes: the driving belt pulley motor, the driven belt pulley motor and the steel belt conveying device are arranged on the steel belt conveying device, the steel belt conveying device is arranged on the driving belt pulley motor and the driven belt pulley motor, and the driving belt pulley motor and the driven belt pulley motor drive the steel belt conveying device to rotate together.
Description: the motor belt rotating system can simulate the running obstacle crossing environment of an actual aircraft carrier through the driving belt pulley motor, the driven belt pulley motor and the steel belt conveying device, so that the test simulation effect is better.
Preferably, the landing gear comprises a buffer support, the bottom of the buffer support is rotationally connected with the organic wheel through a wheel shaft, a buffer air cavity is arranged in the buffer support, and one side of the top of the buffer air cavity is provided with an inflating nozzle; a first displacement sensor is arranged on the lower bottom surface of the hanging basket, and a second displacement sensor is arranged on the buffer support column; the center of the wheel shaft is provided with a first acceleration sensor, and the center of the hanging basket is provided with a second acceleration sensor; the inflation nozzle is internally provided with a pressure sensor.
Description: the key physical quantities of the landing gear running obstacle-surmounting impact test of the carrier-based aircraft comprise the vertical load, displacement, acceleration and air cavity pressure of the landing gear, and the sensor can be arranged to acquire test data more accurately.
Preferably, the landing gear running obstacle crossing impact test device of the carrier-based aircraft further comprises: and the data acquisition equipment is arranged on one side of the motor belt rotating system and is electrically connected with the hinge point force sensor, the first displacement sensor, the second displacement sensor, the first acceleration sensor, the second acceleration sensor and the pressure sensor.
Description: the key physical quantity of the landing gear running obstacle-surmounting impact test of the carrier-based aircraft comprises the vertical load, displacement, acceleration and air cavity pressure of the landing gear, so that based on the setting positions of the sensors, the first displacement sensor is used for measuring the mass center displacement of the equivalent mass system, the second displacement sensor is used for measuring the displacement of the buffer support column on the landing gear, the first acceleration sensor is used for measuring the wheel axle center three-way acceleration in the landing gear running obstacle-surmounting process, the second acceleration sensor is used for measuring the gravity center acceleration of the equivalent mass system, and the pressure sensor is used for measuring the air cavity pressure of the landing gear.
The invention also provides a landing gear running obstacle-surmounting impact test method of the carrier-based aircraft, which is based on the landing gear running obstacle-surmounting impact test device of the carrier-based aircraft, and comprises the following steps:
s1, connecting a landing gear to the bottom of a hanging basket through a supporting clamp;
s2, increasing and reducing a balancing weight in the hanging basket to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear;
s3, adjusting the distance between each obstacle on the motor belt rotating system to enable the obstacles to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system;
s5, starting a motor belt rotation system and achieving the running speed required by the landing gear running obstacle crossing impact test;
s6, throwing an undercarriage, and enabling the undercarriage to slide on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system to put in the equivalent mass system, and enabling the landing gear to contact with the steel belt conveying device after touching the ground so as to be forced to run on the steel belt conveying device;
s7, measuring test data:
when the wheel passes over an obstacle on the motor belt turning system, the dynamic load response acquired by the landing gear hinge point force sensor is tested.
The invention also provides another carrier-based aircraft landing gear running obstacle-crossing impact test method, which is based on the carrier-based aircraft landing gear running obstacle-crossing impact test device and comprises the following steps:
s1, connecting a landing gear to the bottom of a hanging basket through a supporting clamp;
s2, increasing and reducing a balancing weight in the hanging basket to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear;
s3, adjusting the distance between each obstacle on the motor belt rotating system to enable the obstacles to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system;
s5, starting a motor belt rotation system and achieving the running speed required by the landing gear running obstacle crossing impact test;
s6, throwing an undercarriage, and enabling the undercarriage to slide on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system to put in the equivalent mass system, and enabling the landing gear to contact with the steel belt conveying device after touching the ground so as to be forced to run on the steel belt conveying device;
s7, triggering data acquisition equipment, and measuring test data:
when the wheel passes over an obstacle on the steel belt, triggering a data acquisition device, synchronously testing dynamic load response acquired by a hinge point force sensor on the landing gear, measuring the mass center displacement of an equivalent mass system by a first displacement sensor, measuring the displacement of a buffer support on the landing gear by a second displacement sensor, measuring the three-way acceleration of the center of a wheel shaft in the landing gear running over-obstacle process by a first acceleration sensor, measuring the gravity center acceleration of the equivalent mass system by a second acceleration sensor, and measuring the pressure of an air cavity of the landing gear by a pressure sensor; the axle center three-way acceleration is divided into course acceleration, vertical acceleration and lateral acceleration.
Description: the landing gear running obstacle crossing impact test of the carrier-based aircraft better realizes the simulation of the landing gear running obstacle crossing process in practice by acquiring the vertical load, displacement, acceleration and air cavity pressure of the landing gear; the triggering conditions of the data acquisition equipment are as follows: the vertical dynamic load value obtained by the hinge point force sensor is larger than 5kN.
The beneficial effects of the invention are as follows:
(1) The landing gear running obstacle crossing impact test device and method for the carrier-based aircraft can simulate the running obstacle crossing process of the carrier-based aircraft on the surface of the carrier, measure the impact load response of a landing gear system, check the rigidity and strength of the landing gear structure and verify the running obstacle crossing capability of the landing gear;
(2) The landing gear running obstacle crossing impact test device and method for the carrier-based aircraft can measure the load of the carrier-based aircraft at the landing gear mounting hinge point in the running obstacle crossing process, and design test basis for the mounting connection structure between the landing gear and the aircraft body;
(3) The landing gear running obstacle crossing impact test device and method for the carrier-based aircraft can study the influence of different landing gear running speeds, different obstacle distances and different carrier contact speeds on landing gear running obstacle crossing performance.
Drawings
FIG. 1 is a diagram of a carrier aircraft landing gear running obstacle surmounting impact test device according to embodiment 1 of the present invention;
FIG. 2 is a gear heading structural diagram of embodiment 1 of the invention;
FIG. 3 is a block diagram of the lifting/locking system of embodiment 1 of the present invention;
FIG. 4 is a top view of the structure of the obstacle of example 1 of the present invention;
FIG. 5 is a diagram of a carrier aircraft landing gear running obstacle surmounting impact test device according to embodiment 2 of the present invention;
FIG. 6 is a flow chart of a method for performing a landing gear running obstacle surmounting impact test of the carrier-based aircraft in the embodiment 3 and the embodiment 4 of the present invention;
FIG. 7 is a diagram showing the state change of the running obstacle surmounting impact test apparatus according to the embodiment 3 and the embodiment 4 of the present invention during running obstacle surmounting;
the device comprises a 1-test bench, a 2-hanging basket, a 3-lifting/locking system, a 31-actuating cylinder, a 32-releasing lock, a 33-electromagnetic iron sheet, a 4-lifting motor, a 5-balancing weight, a 6-landing gear, a 61-buffering strut, a 62-wheel shaft, a 63-wheel, a 64-buffering air cavity, a 65-second displacement sensor, a 66-pressure sensor, a 67-first acceleration sensor, a 7-obstacle, an 8-steel belt conveying device, a 9-driving belt pulley motor, a 10-driven belt pulley motor, a 11-supporting bench, a 12-hinge point sensor, a 13-first displacement sensor, a 14-second acceleration sensor and 15-data acquisition equipment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, the "plurality" generally includes at least two.
It should be understood that although the terms first, second, third, etc. may be used to describe … … in embodiments of the present invention, these … … should not be limited to these terms. These terms are only used to distinguish … …. For example, the first … … may also be referred to as the second … …, and similarly the second … … may also be referred to as the first … …, without departing from the scope of embodiments of the present invention.
Example 1: the embodiment describes a landing gear running obstacle crossing impact test device of a carrier-based aircraft, as shown in fig. 1, including:
an equivalent mass system for simulating the equivalent mass of landing gear 6, the equivalent mass system comprising landing gear 6;
a test stand 1 for providing an installation environment and vertical motion guidance for the equivalent mass system;
a lifting/locking system 3 for lifting and releasing the equivalent mass system during a running obstacle surmounting impact test, the lifting/locking system 3 being mounted in the test bed 1;
the hinge point force sensor 12 is used for measuring the dynamic load of the landing gear 6 in the running obstacle crossing impact test process, and the hinge point force sensor 12 is arranged on the landing gear 6;
the motor belt rotating system is used for providing a running obstacle crossing environment of the equivalent mass system along the course, and is arranged at the bottom of the landing gear 6;
and the plurality of barriers 7 are used for simulating the lamp covers and/or the camera covers on the aircraft carrier deck, the barriers 7 are arranged on the motor belt rotating system, and the structures of the barriers 7 simulating the lamp covers and/or the camera covers on the aircraft carrier deck are shown in fig. 4.
It may be appreciated that in this embodiment, as shown in fig. 1, the equivalent weight system includes a basket 2, a counterweight 5 is disposed in the basket 2, the top of the basket 2 is fixedly connected with the lifting/locking system 3, a mounting hinge point is disposed at the bottom of the basket 2, and the mounting hinge point is rotatably connected with the landing gear 6 through a supporting fixture.
It will be appreciated that in this embodiment, as shown in fig. 1, the hinge point sensor 12 is provided between the mounting hinge point and the support jig; the dynamic load measured by the hinge point force sensor 12 is classified into a heading dynamic load, a vertical dynamic load and a lateral dynamic load.
It can be appreciated that in this embodiment, as shown in fig. 3, the lifting/locking system 3 includes an actuator cylinder 31, a release lock 32 is fixedly connected to the bottom of the actuator cylinder 31, and the bottom of the release lock 32 is magnetically connected to the equivalent mass system through an electromagnet plate 33; a lifting motor 4 is fixed on the test bed 1, and the output end of the lifting motor 4 is connected with an actuator cylinder 31; from the above, the specific connection relationship is as follows: the electromagnet piece 33 is magnetically connected with the top of the hanging basket 2 of the equivalent mass system.
It will be appreciated that in this embodiment, as shown in fig. 1, the motor belt and rotating system is disposed on the support table 11, and the motor belt and rotating system includes: the obstacle 7 is arranged on the steel belt conveying device 8, the steel belt conveying device 8 is arranged on the driving pulley motor 9 and the driven pulley motor 10, and the driving pulley motor 9 and the driven pulley motor 10 jointly drive the steel belt conveying device 8 to rotate.
It can be understood that in this embodiment, as shown in fig. 1 and 2, the landing gear 6 includes a buffer support 61, the bottom of the buffer support 61 is rotatably connected with an organic wheel 63 through a wheel axle 62, a buffer air cavity 64 is arranged in the buffer support 61, and an air charging nozzle is arranged on one side of the top of the buffer air cavity 64; the lower bottom surface of the hanging basket 2 is provided with a first displacement sensor 13, and the buffer support 61 is provided with a second displacement sensor 65; the center of the wheel axle 62 is provided with a first acceleration sensor 67, and the center of the hanging basket 2 is provided with a second acceleration sensor 14; the pressure sensor 66 is arranged in the charging nozzle; as can be seen from the above description in conjunction with fig. 1 and 2, the landing gear 6 further includes a supporting rod with one end fixed to the bottom of the basket 2 and the other end fixed to the buffer support 61, and the supporting rod has no functional effect in the use process of the landing gear running obstacle-surmounting impact test device of the carrier-based aircraft, so the description is omitted.
Example 2: this embodiment differs from embodiment 1 in that, as shown in fig. 5, it further includes: the data acquisition equipment 15 is arranged on one side of the motor belt rotation system, and the data acquisition equipment 15 is electrically connected with the hinge point force sensor 12, the first displacement sensor 13, the second displacement sensor 65, the first acceleration sensor 67, the second acceleration sensor 14 and the pressure sensor 66.
It will be appreciated that the data acquisition device 15 is a dewesoft data acquisition device.
It will be appreciated that the key physical quantities of the landing gear running over obstacle impact test of the carrier aircraft include the vertical load, displacement, acceleration and air cavity pressure of the landing gear 6, and therefore, based on the setting positions of the above-mentioned individual sensors, the first displacement sensor 13 is used for measuring the mass center displacement of the equivalent mass system, the second displacement sensor 65 is used for measuring the displacement of the buffer strut 61 on the landing gear 6, the first acceleration sensor 67 is used for measuring the central three-way acceleration of the wheel axle 62 during the landing gear 6 running over obstacle, the second acceleration sensor 14 is used for measuring the gravity center acceleration of the equivalent mass system, and the pressure sensor 66 is used for measuring the air cavity pressure of the landing gear 6.
Example 3: the embodiment describes a carrier-based aircraft landing gear running obstacle-surmounting impact test method, and the carrier-based aircraft landing gear running obstacle-surmounting impact test device based on embodiment 1, as shown in fig. 6, comprises the following steps:
s1, connecting a landing gear 6 to the bottom of a hanging basket 2 through a support clamp;
s2, increasing and decreasing the balancing weight 5 in the hanging basket 2 to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear 6;
s3, adjusting the distance between each obstacle 7 on the motor belt rotating system to enable the obstacles 7 to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system 3;
s5, starting a motor belt rotation system and reaching the running speed required by the landing gear 6 running obstacle crossing impact test;
s6, throwing in the landing gear 6, and enabling the landing gear 6 to slide on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system 3 to throw in the equivalent mass system, and enabling the landing gear 6 to contact with the steel belt conveying device 8 after touching the ground so as to be forced to run on the steel belt conveying device 8;
s7, measuring test data:
when the wheel 63 passes over the obstacle 7 on the motor rotation system, the main control computer is triggered, the main control computer synchronously tests the dynamic load response acquired by the hinge point force sensor 12 on the landing gear 6, the first displacement sensor 13 measures the mass center displacement of the equivalent mass system, the second displacement sensor 65 measures the displacement of the buffer support 61 on the landing gear 6, the first acceleration sensor 67 measures the center three-way acceleration of the wheel shaft 62 during the landing gear 6 sliding over the obstacle, the second acceleration sensor 14 measures the gravity center acceleration of the equivalent mass system, and the pressure sensor 66 measures the air cavity pressure of the landing gear 6.
It can be understood that in step S6, when the landing gear 6 touches the ground, the state of the landing gear running obstacle surmounting impact test of the carrier-based aircraft is shown as an initial state in fig. 7; in step S7, when the wheel 63 passes over the obstacle 7 on the motor belt system, the state of the landing gear running over obstacle impact test of the carrier-based aircraft is shown as an obstacle-crossing state in fig. 7.
It can be appreciated that in this embodiment, the main control computer is electrically connected with the hinge point force sensor 12, the first displacement sensor 13, the second displacement sensor 65, the first acceleration sensor 67, the second acceleration sensor 14 and the pressure sensor 66 through cables; the triggering conditions of the main control computer are as follows: the vertical dynamic load value obtained by the hinge point force sensor 12 is more than 5kN; the axle 62 center three-way acceleration is divided into heading acceleration, vertical acceleration, and lateral acceleration.
Example 4: the embodiment describes a carrier-based aircraft landing gear running obstacle-surmounting impact test method, and the carrier-based aircraft landing gear running obstacle-surmounting impact test device based on embodiment 2, as shown in fig. 6 and 7, comprises the following steps:
s1, connecting a landing gear 6 to the bottom of a hanging basket 2 through a support clamp;
s2, increasing and decreasing the balancing weight 5 in the hanging basket 2 to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear 6;
s3, adjusting the distance between each obstacle 7 on the motor belt rotating system to enable the obstacles 7 to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system 3;
s5, starting a motor belt rotation system and reaching the running speed required by the landing gear 6 running obstacle crossing impact test;
s6, throwing in the landing gear 6, and enabling the landing gear 6 to slide on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system 3 to throw in the equivalent mass system, and enabling the landing gear 6 to contact with the steel belt conveying device 8 after touching the ground so as to be forced to run on the steel belt conveying device 8;
s7, measuring test data:
when the wheel 63 passes over the obstacle 7 on the steel belt, the data acquisition equipment 15 is triggered, the dynamic load response acquired by the hinge point force sensor 12 on the landing gear 6 is synchronously tested, the first displacement sensor 13 measures the mass center displacement of the equivalent mass system, the second displacement sensor 65 measures the displacement of the buffer support 61 on the landing gear 6, the first acceleration sensor 67 measures the center three-way acceleration of the wheel shaft 62 during the running of the landing gear 6 over the obstacle, the second acceleration sensor 14 measures the gravity center acceleration of the equivalent mass system, and the pressure sensor 66 measures the air cavity pressure of the landing gear 6.
It can be understood that in step S6, when the landing gear 6 touches the ground, the state of the landing gear running obstacle surmounting impact test of the carrier-based aircraft is shown as an initial state in fig. 7; in step S7, when the wheel 63 passes over the obstacle 7 on the motor belt system, the state of the landing gear running over obstacle impact test of the carrier-based aircraft is shown as an obstacle-crossing state in fig. 7.
It can be appreciated that in this embodiment, the triggering conditions of the data acquisition device 15 are: the vertical dynamic load value obtained by the hinge point force sensor 12 is more than 5kN; the axle 62 center three-way acceleration is divided into heading acceleration, vertical acceleration, and lateral acceleration.
Claims (5)
1. The utility model provides a carrier-borne aircraft undercarriage running obstacle crossing impact test device which characterized in that includes:
an equivalent mass system for simulating the equivalent mass of a landing gear (6), the equivalent mass system comprising a landing gear (6);
a test stand (1) for providing an installation environment and vertical motion guidance for the equivalent mass system;
a lifting/locking system (3) for lifting and releasing the equivalent mass system during a running obstacle surmounting impact test, the lifting/locking system (3) being mounted within the test bench (1);
the hinge point force sensor (12) is used for measuring the dynamic load of the landing gear (6) in the running obstacle crossing impact test process, and the hinge point force sensor (12) is arranged on the landing gear (6);
the motor belt rotating system is used for providing a running obstacle crossing environment of the equivalent mass system along the course, and is arranged at the bottom of the landing gear (6);
the obstacle (7) is used for simulating a lamp cover and/or a camera cover on the aircraft carrier deck, and the obstacle (7) is arranged on the motor belt-rotating system;
the equivalent weight system comprises a hanging basket (2), a balancing weight (5) is arranged in the hanging basket (2), the top of the hanging basket (2) is fixedly connected with the lifting/locking system (3), the bottom of the hanging basket (2) is provided with a mounting hinge point, and the mounting hinge point is rotationally connected with the landing gear (6) through a supporting clamp;
the hinge point force sensor (12) is arranged between the mounting hinge point and the supporting clamp;
the lifting/locking system (3) comprises an actuator cylinder (31), wherein a release lock (32) is fixedly connected to the bottom of the actuator cylinder (31), and the bottom of the release lock (32) is magnetically connected with the equivalent mass system through an electromagnet sheet (33); a lifting motor (4) is fixed on the test bed (1), and the output end of the lifting motor (4) is connected with an actuator cylinder (31);
the motor takes the system of turning over and arranges in supporting bench (11), and the motor takes the system of turning over includes: the device comprises a driving belt wheel motor (9), a driven belt wheel motor (10) and a steel belt conveying device (8), wherein the obstacle (7) is arranged on the steel belt conveying device (8), the steel belt conveying device (8) is arranged on the driving belt wheel motor (9) and the driven belt wheel motor (10), and the driving belt wheel motor (9) and the driven belt wheel motor (10) drive the steel belt conveying device (8) to rotate together;
the landing gear (6) comprises a buffer support (61), the bottom of the buffer support (61) is rotationally connected with an organic wheel (63) through a wheel shaft (62), a buffer air cavity (64) is arranged in the buffer support (61), and an inflating nozzle is arranged on one side of the top of the buffer air cavity (64); a first displacement sensor (13) is arranged on the lower bottom surface of the hanging basket (2), and a second displacement sensor (65) is arranged on the buffer support column (61); the center of the wheel shaft (62) is provided with a first acceleration sensor (67), and the center of the hanging basket (2) is provided with a second acceleration sensor (14); a pressure sensor (66) is arranged in the charging connector.
2. The landing gear running obstacle surmounting impact test device for the carrier-based aircraft according to claim 1, wherein the dynamic load measured by the hinge point force sensor (12) is divided into a heading dynamic load, a vertical dynamic load and a lateral dynamic load.
3. The carrier-based aircraft landing gear running obstacle-surmounting impact test device of claim 1, further comprising: the data acquisition equipment (15) is arranged on one side of the motor belt rotating system, and the data acquisition equipment (15) is electrically connected with the hinge point force sensor (12), the first displacement sensor (13), the second displacement sensor (65), the first acceleration sensor (67), the second acceleration sensor (14) and the pressure sensor (66).
4. The landing gear running obstacle crossing impact test method for the carrier-based aircraft, based on the landing gear running obstacle crossing impact test device for the carrier-based aircraft according to any one of claims 1-3, is characterized by comprising the following steps:
s1, connecting a landing gear (6) to the bottom of a hanging basket (2) through a supporting clamp;
s2, increasing and decreasing the balancing weight (5) in the hanging basket (2) to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear (6);
s3, adjusting the distance between each obstacle (7) on the motor belt rotating system to enable the obstacles (7) to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system (3);
s5, starting a motor belt rotation system and reaching the running speed required by the landing gear (6) running obstacle crossing impact test;
s6, throwing in a landing gear (6), wherein the landing gear (6) slides on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system (3) to throw in the equivalent mass system, and enabling the landing gear (6) to contact with the steel belt conveying device (8) after being contacted with the ground so as to be forced to run on the steel belt conveying device (8);
s7, measuring test data:
when the wheel (63) passes over an obstacle (7) on the motor steering system, the dynamic load response acquired by a hinge point force sensor (12) on the landing gear (6) is tested.
5. The landing gear running obstacle crossing impact test method for the carrier-based aircraft is based on the landing gear running obstacle crossing impact test device for the carrier-based aircraft of claim 4, and is characterized by comprising the following steps:
s1, connecting a landing gear (6) to the bottom of a hanging basket (2) through a supporting clamp;
s2, increasing and decreasing the balancing weight (5) in the hanging basket (2) to enable the weight of the equivalent weight system to be the same as the equivalent weight of the actual landing gear (6);
s3, adjusting the distance between each obstacle (7) on the motor belt rotating system to enable the obstacles (7) to simulate the installation condition of a lamp cover and/or a camera cover on the surface of the aircraft carrier;
s4, lifting the equivalent mass system to a preset throwing height through a lifting/locking system (3);
s5, starting a motor belt rotation system and reaching the running speed required by the landing gear (6) running obstacle crossing impact test;
s6, throwing in a landing gear (6), wherein the landing gear (6) slides on a motor belt-rotating system:
when the running speed of the motor belt rotating system reaches a preset test value, controlling the lifting/locking system (3) to throw in the equivalent mass system, and enabling the landing gear (6) to contact with the steel belt conveying device (8) after being contacted with the ground so as to be forced to run on the steel belt conveying device (8);
s7, triggering a data acquisition device (15), and measuring test data:
when the wheel (63) passes over an obstacle (7) on a steel belt, triggering a data acquisition device (15), synchronously testing dynamic load response acquired by a hinge point force sensor (12) on the landing gear (6), measuring the mass center displacement of an equivalent mass system by a first displacement sensor (13), measuring the displacement of a buffer support (61) on the landing gear (6) by a second displacement sensor (65), measuring the center three-way acceleration of a wheel shaft (62) in the sliding obstacle crossing process of the landing gear (6) by a first acceleration sensor (67), measuring the gravity center acceleration of the equivalent mass system by a second acceleration sensor (14), and measuring the air cavity pressure of the landing gear (6) by a pressure sensor (66); the central three-way acceleration of the wheel axle (62) is divided into course acceleration, vertical acceleration and lateral acceleration.
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| CN117184444B (en) * | 2023-11-07 | 2024-01-09 | 中国飞机强度研究所 | Prediction test method for obstacle surmounting impact load of aviation aircraft tire |
| CN117184443B (en) * | 2023-11-07 | 2024-01-26 | 中国飞机强度研究所 | Device and method for slide obstacle surmounting impact test of landing gear of carrier-based aircraft |
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