An emergency separation dynamic test device for an aircraft landing gear

Abstract

The application belongs to the field of airplane ground test, and is an emergency separation dynamic test device for airplane landing gear, which comprises a test bench, a lifting release mechanism, a hanging basket, a follow-up belt rotating device, a test piece and a ground load measuring device; when the emergency separation dynamic test is carried out, the lifting release mechanism is first controlled to lift the test piece to a set height, and then the lifting release mechanism is controlled to lower the hanging basket, the hanging basket falls together with the test piece, the follow-up belt rotating device controls the rotation of the wheel in the falling process to simulate the real falling condition of the landing gear, and finally the test piece falls on the ground load measuring device, at this time, the separation load of the test piece is measured by the sensor of the separation load measuring device, the load of the test piece is measured by the inductive element on the ground load measuring device, and through the simulation of the overload condition of the airplane emergency landing, the separation load, separation sequence and the motion trajectory of the landing gear system after separation of the emergency separation shaft pin of the landing gear can be studied.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of airplane ground test, and particularly relates to an airplane landing gear emergency separation dynamic test device. BACKGROUND

[0002] The landing gear, as an important load-bearing component of an airplane, plays an extremely important role in the process of take-off and landing of the airplane. In the design process of a civil airplane, in order to reduce the severity of an accident and avoid serious injury to the crew and passengers, foreign related models such as Airbus A320 and Boeing B737 often adopt an emergency separation design at the connection between the main landing gear structure and the wing, so as to realize the safe separation of the landing gear and the wing structure under the condition that the landing gear structure bears a large overload, avoid the danger of tearing the wing tank by the landing gear, and reduce the injury to the crew in an accident. For a transport airplane, the emergency separation design of the landing gear should be verified by test and meet the airworthiness requirements.

[0003] The internationally common airworthiness compliance verification work of the emergency separation design of the landing gear is mainly performed by a method of calculation analysis (MOC2), and a static strength test of an emergency separation safety pin is additionally performed. The method of calculation analysis mainly utilizes analysis and calculation to show that under the condition of overload, the wing tank is not broken due to the failure of the landing gear, so as to cause a fire caused by a sufficient amount of fuel leakage. The analysis needs to show that under different overload conditions (the ratio of drag to vertical force, the ratio of lateral force to vertical force), the breaking strength of the main structure of the landing gear and the wing box structure (including the fuel tank) is higher than that of the safety pin of the landing gear structure.

[0004] With the improvement of the safety performance requirement of a civil airplane, the verification method of calculation of the landing gear system alone cannot meet the research and verification requirements, and a dynamic test method at the level of the landing gear system is required to verify the emergency separation capability of the landing gear under the condition of emergency landing overload.

[0005] Therefore, how to verify the emergency separation capability of the landing gear under the condition of emergency landing overload is a problem to be solved. SUMMARY

[0006] The present application aims to provide an airplane landing gear emergency separation dynamic test device to solve the problem that the calculation verification of the landing gear system alone in the prior art cannot meet the current safety performance requirement.

[0007] The technical scheme of the present application is: a kind of airplane landing gear emergency separation dynamic test device, including test bench, lifting release mechanism, basket, follow-up belt rotating device, test piece and ground load measuring device;The lifting release mechanism is located on test bench, the basket is connected with lifting release mechanism and lifting release mechanism can drive basket to move up and down, counterweight is arranged in the basket;Test piece is connected to the lower portion of basket, follow-up belt rotating device is connected between basket and test piece, follow-up belt rotating device can drive the rotation of test piece on the wheel, ground load measuring device is arranged directly below test piece, inductive element is arranged in ground load measuring device, separation load measuring sensor that can measure the load of emergency separation shaft pin in real time is connected between test piece and basket.

[0008] Preferably, it further includes an emergency separation protection system, the emergency separation protection system includes soft sling, the soft sling has four groups and is evenly arranged along the circumference of the test piece, the basket is provided with a lifting ring, the test piece is provided with a shaft pin hole on the support, and each group of soft slings is connected between the lifting ring on the basket and the shaft pin hole on the test piece.

[0009] Preferably, it further includes an emergency separation protection system, the emergency separation protection system includes soft sling, the soft sling has four groups and is evenly arranged along the circumference of the test piece, the basket and test piece are provided with lifting rings, and each group of soft slings is connected between the lifting ring on the basket and the lifting ring on the test piece.

[0010] Preferably, the lifting release device includes a lifting motor, a steel wire rope and a release lock, the lifting motor is arranged on the test bench, a chain gear is arranged on the rotating shaft of the lifting motor, the release lock is connected with the basket, the upper end of the steel wire rope is fixed on the test bench, the middle part is connected with the chain gear, and the lower end is connected with the release lock.

[0011] Preferably, the ground load measuring device includes a pavement simulation layer, a three-way force platform and an expansion protection platform, the pavement simulation layer is arranged opposite to the test piece, the pavement simulation layer is of rectangular structure, the three-way force platform is connected below the pavement simulation layer, and the expansion protection platform is of open annular structure and arranged around the pavement simulation layer.

[0012] Preferably, it further includes a lift simulation device, the lift simulation device includes a lift simulation cylinder, the lift simulation cylinder has multiple groups and is arranged below the basket, the top of the lift simulation cylinder is provided with a buffer pad, and the buffer pad abuts against the basket after the test piece abuts against the ground load measuring device.

[0013] Preferably, it further includes a non-contact measurement system, the non-contact measurement system includes a support and a high-speed camera arranged on the top of the support, and the high-speed camera is arranged on one side of the ground load measuring device.

[0014] The application discloses an emergency separation dynamic test device for an aircraft landing gear, which comprises a test bench, a lifting release mechanism, a hanging basket, a follow-up belt rotating device, a test piece and a ground load measuring device. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions provided by the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

[0016] Figure 1 It is a whole structure front view of the application;

[0017] Figure 2 It is a whole structure side view of the application;

[0018] Figure 3 It is a structure schematic diagram of the ground load measuring device of the application.

[0019] 1, test bench; 2, lifting release mechanism; 3, hanging basket; 4, separation load measuring sensor; 5, follow-up belt rotating device; 6, soft sling; 7, lift simulation device; 8, high-speed camera; 9, counterweight; 10, test piece; 11, servo motor; 12, belt; 13, belt rotating disc; 14, ground load measuring device; 15, pavement simulation layer; 16, three-way force platform; 17, expansion protection platform; 18, foundation. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the application clearer, the following will combine the drawings in the embodiments of the application to make the technical solutions in the embodiments of the application more detailed.

[0021] An emergency separation dynamic test device for an aircraft landing gear, as shown in Figures 1-2 Fig. 1, comprises a test bench 1, a lifting release mechanism 2, a hanging basket 3, a follow-up belt rotating device 5, a test piece 10 and a ground load measuring device 14.

[0022] The test bench 1 is a main installation base and a bearing structure. The lifting release mechanism 2 can provide a motion guide for the basket 3, so that the basket 3 can move freely in a vertical direction. The load borne by the landing gear during the test is transmitted to the test bench 1 through the basket 3.

[0023] The lifting release mechanism 2 is arranged on the test bench 1. The basket 3 is connected to the lifting release mechanism 2 and can be driven by the lifting release mechanism 2 to move up and down. The basket 3 is provided with a counterweight 9. The basket 3 is an installation base of the test piece 10. The addition of the counterweight 9 can simulate the equivalent mass of the landing gear. The basket 3 can move freely in a vertical direction along the test bench 1. The basket 3 and the landing gear together form a test falling body system. The basket 3 can be released at a certain height to simulate the vertical touchdown speed of the landing gear.

[0024] The test piece 10 is connected below the basket 3. The test piece 10 is the landing gear, which includes a wheel and a strut. A follow-up belt rotating device 5 is connected between the basket 3 and the test piece 10. The follow-up belt rotating device 5 can drive the wheel on the test piece 10 to rotate. A ground load measuring device 14 is arranged directly below the test piece 10. The ground load measuring device 14 is below a foundation 18. The ground load measuring device 14 is provided with a sensing element. A separation load measuring sensor 4 is connected between the test piece 10 and the basket 3. The separation load measuring sensor 4 can measure the load of the emergency separation shaft pin in real time during the test, so as to determine the separation sequence. When the separation shaft pin at the hinge point breaks, the corresponding load is the separation load.

[0025] During the emergency separation dynamic test, the test piece 10 is first lifted to a set height by the lifting release mechanism 2. Then, the basket 3 is lowered by the lifting release mechanism 2. The basket 3 falls together with the test piece 10. During the falling process, the follow-up belt rotating device 5 controls the wheel to rotate, so as to simulate the actual falling condition of the landing gear. Finally, the test piece 10 falls onto the ground load measuring device 14. At this time, the separation load of the test piece 10 is measured by the separation load measuring sensor. The load of the test piece 10 is measured by the sensing element on the ground load measuring device 14. The sensing element can have multiple types, including a load sensor.

[0026] After one measurement is completed, the test piece 10 and the basket 3 can be lifted again by the lifting release mechanism 2, so as to perform repeated tests. Through simulation of the overload condition of the airplane during emergency landing, the separation load, the separation sequence of the emergency separation shaft pin of the landing gear, and the motion trajectory of the landing gear system after separation can be researched. The compliance and safety performance of the emergency separation design of the landing gear can be verified, until the actual requirements are met.

[0027] Preferably, an emergency disconnect protection system is further included, which comprises four groups of soft hangers 6 evenly arranged along the circumference of the test piece 10, the basket 3 is provided with a lifting ring, the support of the test piece 10 is provided with an axle pin hole, and each group of soft hangers 6 is connected between the lifting ring on the basket 3 and the axle pin hole on the test piece 10. After the landing gear disconnects the axle pin, the elasticity of the soft hangers 6 can constrain the movement of the landing gear support to some extent, preventing the irregular movement of the disconnected landing gear from damaging the equipment and the test piece 10.

[0028] Preferably, the follow-up belt rotating device 5 comprises a servo motor 11, a belt 12 and a belt rotating disc 13, the servo motor 11 is installed at the bottom of the basket 3, the belt rotating disc 13 is coaxially connected with the corresponding wheel, and the belt 12 is connected between the rotating shaft of the servo motor 11 and the belt rotating disc 13. When the servo motor 11 works, the belt rotating disc 13 is driven to rotate by the belt 12, and the wheel is synchronously driven to rotate by the belt rotating disc 13, so as to simulate the real working condition of the landing gear.

[0029] Preferably, the lifting release device comprises a lifting motor, a steel wire rope and a release lock; the lifting motor is arranged on the test bench 1, a chain gear is arranged on the rotating shaft of the lifting motor, the release lock is connected with the basket 3, and the upper end of the steel wire rope is fixed on the test bench 1, the middle part is connected with the chain gear, and the lower end is connected with the release lock. When the lifting motor rotates forward, the steel wire rope and the release lock are pulled upward, so as to drive the basket 3 to move upward; conversely, the basket 3 moves downward, and the release lock is an existing component, which has two functions of opening and closing. When it is closed, the basket 3 is connected with the steel wire rope, and when it is opened, the basket 3 is released.

[0030] In combination Figure 3 , preferably, the ground load measuring device 14 comprises a pavement simulation layer 15, a three-way force platform 16 and an expansion protection platform 17; the pavement simulation layer 15 is arranged opposite to the test piece 10, the pavement simulation layer 15 has a rectangular structure, the three-way force platform 16 is connected below the pavement simulation layer 15, and the expansion protection platform 17 has an open annular structure and is arranged around the pavement simulation layer 15.

[0031] The pavement simulation layer 15 is used for simulating the real airport ground, the three-way force platform 16 has a plurality of sensing elements, which can measure the vertical, lateral and longitudinal forces respectively, the expansion protection platform 17 is composed of a plurality of transverse plates, longitudinal plates and rib plates, which can support the pavement simulation layer 15 and prevent the wheels from sliding out of the platform area after the landing gear disconnects, thereby preventing secondary damage to the landing gear structure.

[0032] Preferably, the device further comprises a lift simulation device 7, which comprises a plurality of lift simulation cylinders, each of which is arranged below the basket 3 and has a buffer pad at the top, which abuts against the basket 3 after the test piece 10 abuts against the ground load measuring device 14. After the test piece 10 falls, the lift simulation cylinders work to lift the basket 3 by means of the piston rods, so as to prevent the test piece 10 from being damaged again after the emergency separation of the landing gear.

[0033] Preferably, the device further comprises a non-contact measuring system, which comprises a support and a high-speed camera 8 arranged at the top of the support, and the high-speed camera 8 is arranged at one side of the ground load measuring device 14 to record the trajectory after the emergency separation of the landing gear, and there should be no obstacles in the field of view.

[0034] The above merely illustrates the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any modification or replacement within the technical scope disclosed by the present application can be easily thought of by those skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An apparatus for dynamic testing of emergency release of an aircraft landing gear, characterized in that: The test bench (1), the lifting release mechanism (2), the basket (3), the follow-up belt rotating device (5), the test piece (10) and the ground load measuring device (14) are included; the lifting release mechanism (2) is arranged on the test bench (1), the basket (3) is connected with the lifting release mechanism (2) and the lifting release mechanism (2) can drive the basket (3) to move up and down, the basket (3) is internally provided with a counterweight (9); the test piece (10) is connected below the basket (3), the follow-up belt rotating device (5) is connected between the basket (3) and the test piece (10), the follow-up belt rotating device (5) can drive the machine wheel on the test piece (10) to rotate, the ground load measuring device (14) is arranged directly below the test piece (10), the ground load measuring device (14) is internally provided with a sensing element, the test piece (10) is connected with the basket (3) and is provided with a separation load measuring sensor (4) capable of measuring the load of the emergency separation shaft pin in real time; It also includes an emergency separation protection system, the emergency separation protection system includes four groups of soft hangers (6) and is uniformly arranged along the circumference of the test piece (10), the basket (3) is provided with a lifting ring, the test piece (10) is provided with a shaft pin hole on the support, each group of soft hangers (6) is connected between the lifting ring on the basket (3) and the shaft pin hole on the test piece (10).

2. The dynamic test apparatus for emergency separation of an aircraft landing gear according to claim 1, characterized in that: The follow-up belt rotating device (5) includes a servo motor (11), a belt (12) and a belt rotating disc (13), the servo motor (11) is installed at the bottom of the basket (3), the belt rotating disc (13) is coaxially connected with the corresponding machine wheel, and the belt (12) is connected between the rotating shaft of the servo motor (11) and the belt rotating disc (13).

3. The dynamic test apparatus for emergency release of an aircraft landing gear according to claim 1, characterized in that: The lifting release mechanism (2) includes a lifting motor, a steel wire rope and a release lock; the lifting motor is arranged on the test bench (1), a chain gear is arranged on the rotating shaft of the lifting motor, the release lock is connected with the basket (3), and the upper end of the steel wire rope is fixed on the test bench (1), the middle part is connected with the chain gear, and the lower end is connected with the release lock.

4. The dynamic test apparatus for emergency release of an aircraft landing gear according to claim 1, characterized in that: The ground load measuring device (14) includes a pavement simulation layer (15), a three-way force platform (16) and an expansion protection platform (17); the pavement simulation layer (15) is arranged opposite to the test piece (10), the pavement simulation layer (15) is of a rectangular structure, the three-way force platform (16) is connected below the pavement simulation layer (15), and the expansion protection platform (17) is of an open ring structure and is arranged around the pavement simulation layer (15).

5. The dynamic test apparatus for emergency release of an aircraft landing gear according to claim 1, characterized in that: It also includes an imitation lifting simulation device (7), the imitation lifting simulation device (7) includes multiple groups of imitation lifting cylinders, the imitation lifting cylinders are arranged below the basket (3), the top of the imitation lifting cylinder is provided with a buffer pad, and when the test piece (10) is connected with the ground load measuring device (14), the buffer pad abuts against the basket (3).

6. The dynamic test apparatus for emergency release of an aircraft landing gear according to claim 1, characterized in that: Also included is a non-contact measurement system including a support and a high-speed video camera (8) disposed at the top of the support, the high-speed video camera (8) being disposed on one side of the ground load measurement device (14).

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