A multifunction landing gear system comprehensive test bed

Abstract

A multifunctional landing gear system integrated test bench, used for testing on a microcomputer-controlled hydraulic press, includes a hydraulic press, simulation components, and landing gear system components. The hydraulic press includes a crossbeam, a slider, and a base. The simulation components include a landing gear bay interface simulation component and a ground simulation component. The landing gear system components include a retraction / expansion actuator, a shock absorber strut, and a wheel assembly. The ground simulation component is mounted on the base and contacts the wheel assembly. The landing gear bay interface simulation component is mounted on the slider. The wheel assembly is connected to the shock absorber strut. One end of the retraction / expansion actuator is connected to the landing gear bay interface simulation component, and the other end is connected to the shock absorber strut. This invention can simulate all tests required for the landing gear system during final assembly and flight testing. It can significantly reduce the final assembly cycle in mass production models and allow for earlier testing in aircraft development, providing sufficient data support and improvement time for the design.

Description

Technical Field

[0001] This invention relates to the field of landing gear testing technology, and in particular to a multifunctional integrated test bench for landing gear systems. Background Technology

[0002] Landing gear is an important accessory device on an aircraft used for takeoff, landing, and ground taxiing. A complete landing gear system needs to have basic functions such as support, cushioning, taxiing, retraction, and braking. Generally, the shock absorber strut with wheels provides support, cushioning, taxiing, and braking functions, while the retraction actuator provides retraction and auxiliary support functions.

[0003] Because the landing gear system has many components, each with its own independent function, most aircraft manufacturers currently adopt a flat manufacturing model. Different hydraulic component manufacturers produce the various components of the landing gear system separately, which are then directly assembled with the fuselage during the final assembly stage of the aircraft. Various verification tests and corresponding adjustments are then carried out. As a result, the collaborative performance of many components in the landing gear system can only be verified during the final assembly stage. For example, the retraction and extension performance of the retraction actuator after connecting to the landing gear, and the performance of the shock absorber strut under static pressure load at the working angle, can only be verified during the aircraft's test flight.

[0004] In summary, according to the current landing gear system assembly and testing process, a large number of coordination tests can only be carried out during the final assembly and flight test phases. This can easily lead to a lengthy and cumbersome landing gear system assembly process, requiring repeated disassembly and reassembly for debugging, which ultimately affects the overall assembly efficiency of the aircraft. Summary of the Invention

[0005] The technical problem solved by this invention is to provide a multifunctional landing gear system integrated test bench to solve the problems in the background art mentioned above.

[0006] The technical problem solved by this invention is achieved by the following technical solution:

[0007] A multifunctional landing gear system integrated test bench is provided for testing on a microcomputer-controlled hydraulic press. The test bench includes a hydraulic press, simulation components, and landing gear system components. The hydraulic press includes a crossbeam, a slider, and a base. The simulation components include a landing gear bay interface simulation component and a ground simulation component. The landing gear system components include a retraction and extension actuator, a shock absorber, and a wheel assembly. The ground simulation component is mounted on the base and contacts the wheel assembly. The landing gear bay interface simulation component is mounted on the slider. The wheel assembly is connected to the shock absorber. One end of the retraction and extension actuator is connected to the landing gear bay interface simulation component, and the other end is connected to the shock absorber.

[0008] The landing gear bay interface simulation component includes a buffer strut connector for connecting the buffer strut, a retraction and extension actuator connector for connecting the actuator, an upper lock connector for connecting the upper lock, and a landing gear bay floor plate. The retraction and extension actuator connector and the upper lock connector are installed at the front end of the landing gear bay floor plate, the landing gear bay interface through hole for installing the landing gear bay interface simulation component is provided in the middle of the landing gear bay floor plate, and the buffer strut connector is provided at the rear end of the landing gear bay floor plate.

[0009] The ground simulation component includes an inertia wheel, a servo motor, a belt, a connecting shaft, a weight-adding ring, and a ground simulation base plate. The rear end of the ground simulation base plate has a pair of mounting seats for the connecting shaft, and a rotation through-hole between the mounting seats to accommodate the rotation of the inertia wheel. One end of the inertia wheel and one end of the belt are respectively mounted on the connecting shaft, and a weight-adding ring for changing the inertia wheel's inertia is provided on the connecting shaft. The other end of the belt is nested on the output shaft of the servo motor. The front end of the ground simulation base plate has a ground simulation through-hole for mounting the ground simulation component. The inertia wheel contacts the aircraft wheel assembly, simulating the motion of the aircraft wheels relative to the ground during takeoff and landing.

[0010] In this invention, the buffer strut joint and the upper lock joint are welded to the landing gear bay floor plate by weld seam.

[0011] In this invention, the buffer support joint is provided with a pin hole for connecting the buffer support.

[0012] In this invention, the output shaft of the servo motor is parallel to the connecting shaft.

[0013] In this invention, a frustum for mounting an inertia wheel is provided on the connecting shaft.

[0014] In this invention, a threaded ring for mounting a belt is provided on the connecting shaft.

[0015] In this invention, the weight-adding ring is locked to the connecting shaft by a locking nut.

[0016] In this invention, the test bench is used in conjunction with a servo hydraulic test bench. The positions of the joints in the landing gear bay interface simulation component are consistent with the positions of the interfaces used to install the landing gear system in the aircraft landing gear bay, so as to simulate the actual connection state between the components of the landing gear system and the fuselage. The ground simulation component simulates the motion state of the landing gear wheels relative to the ground when the aircraft lands through the rotation of the inertia wheel. The hydraulic press applies pressure to the entire landing gear system to simulate the actual load conditions of the landing gear in a static state or during takeoff and landing. The servo hydraulic test bench simulates the aircraft hydraulic system and provides driving pressure to the components of the test bench according to the actual test requirements, simulating the actual installation, retraction, and taxiing state of the landing gear system. Through this test bench, the tests required for the landing gear system in the final assembly and flight test stages can be completed.

[0017] Beneficial effects: This invention simulates the actual installation, retraction, and taxiing of the landing gear system to simulate all the tests required for the landing gear system during the final assembly and flight test phases. This not only significantly reduces the final assembly cycle in mass production models, but also allows for the early implementation of landing gear system tests that were originally required to be conducted randomly in aircraft development tasks, providing sufficient data support and improvement time for the design. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of a preferred embodiment of the present invention.

[0019] Figure 2 This is a schematic diagram of the landing gear bay interface simulation component structure in a preferred embodiment of the present invention.

[0020] Figure 3 This is a schematic diagram of the ground simulation component structure in a preferred embodiment of the present invention.

[0021] Figure 4 This is an exploded view of the ground simulation component in a preferred embodiment of the present invention.

[0022] Figure 5 This is a schematic diagram of the test bench for the loading and unloading test of the actuator cylinder in a preferred embodiment of the present invention.

[0023] Figure 6 This is a schematic diagram of a test bench performing an upper-level lock unlocking test in a preferred embodiment of the present invention.

[0024] Figure 7 for Figure 6 A schematic diagram of the unlocking sequence under a magnified view of part W in the middle.

[0025] Figure 8 This is a schematic diagram of a static pressure test of a buffer support on a test bench in a preferred embodiment of the present invention.

[0026] Figure 9 This is a schematic diagram of a braking test performed on a test bench in a preferred embodiment of the present invention. Detailed Implementation

[0027] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below with reference to specific illustrations.

[0028] See Figures 1-4A multifunctional landing gear system integrated test bench is provided, which conducts tests on a microcomputer-controlled hydraulic press. It includes a hydraulic press 1, a simulation component 2, and a landing gear system component 3. The hydraulic press 1 includes a crossbeam 11, a slider 12, and a base 13. The simulation component 2 includes a landing gear bay interface simulation component 21 and a ground simulation component 22. The landing gear system component 3 includes a retraction and extension actuator 31, a buffer strut 32, and a wheel assembly 33. The ground simulation component 22 is installed on the base 13 and contacts the wheel assembly 33. The landing gear bay interface simulation component 21 is installed on the slider 12. The wheel assembly 33 is connected to the buffer strut 32. One end of the retraction and extension actuator 31 is connected to the landing gear bay interface simulation component 21, and the other end of the retraction and extension actuator 31 is connected to the buffer strut 32.

[0029] The landing gear bay interface simulation component 21 includes a buffer strut connector 211 for connecting the buffer strut, a retraction and extension actuator connector 212 for connecting the actuator, an upper lock connector 213 for connecting the upper lock, a landing gear bay floor plate 214, and a weld 215. The retraction and extension actuator connector 212 and the upper lock connector 213 are installed at the front end of the landing gear bay floor plate 214. The landing gear bay interface through hole is provided in the middle of the landing gear bay floor plate 214 for installing the landing gear bay interface simulation component 21. The buffer strut connector 211 is provided at the rear end of the landing gear bay floor plate 214, and the buffer strut connector 211 and the upper lock connector 213 are welded to the landing gear bay floor plate 214 through the weld 215.

[0030] The ground simulation component 22 includes an inertia wheel 221, a servo motor 222, a belt 223, a connecting shaft 224, a front locking nut 225, a front weight-adding ring 226, a rear weight-adding ring 227, a rear locking nut 228, and a ground simulation base plate 229. The ground simulation base plate 229 has a pair of mounting seats for mounting the connecting shaft 224 on one side of its rear end, and a rotation through hole for accommodating the rotation of the inertia wheel 221 is provided between the pair of mounting seats. The inertia wheel 221 and the belt 223 are mounted on the connecting shaft 224, and a [missing information - likely a continuation of the previous sentence] is provided on the connecting shaft 224. The front weight ring 226 and rear weight ring 227 are used to replace the inertia of the inertia wheel 221. The front weight ring 226 is locked to the connecting shaft 224 by the front locking nut 225, and the rear weight ring 227 is locked to the connecting shaft 224 by the rear locking nut 228. A belt 223 is nested on the output shaft of the servo motor 222. The front end of the ground simulation base plate 229 is provided with a ground simulation through hole for installing the ground simulation component 22. The inertia wheel 221 contacts the wheel assembly 33, and the inertia wheel 221 simulates the motion state of the wheels relative to the ground when the aircraft is taxiing and landing.

[0031] In this embodiment, the buffer support joint 211 is provided with a pin hole for connecting the buffer support.

[0032] In this embodiment, the output shaft of the servo motor 222 is parallel to the connecting shaft 224.

[0033] In this embodiment, a frustum for mounting the inertia wheel 221 is provided on the connecting shaft 224.

[0034] In this embodiment, a threaded ring for mounting the belt 223 is provided on the connecting shaft 224.

[0035] In this embodiment, the test bench needs to be used in conjunction with a servo hydraulic test bench. The relevant positions of each joint in the landing gear bay interface simulation component 21 are consistent with the relevant positions of the interfaces used to install the landing gear system in the aircraft landing gear bay, which is used to simulate the real state of the connection between each component in the landing gear system and the fuselage. The ground simulation component 22 simulates the motion state of the landing gear wheels relative to the ground when the aircraft lands through the rotation of the inertia wheel 221. The hydraulic press applies pressure to the entire landing gear system to simulate the actual load conditions of the landing gear in a static state or during takeoff and landing (including the weight of the aircraft and various loads generated during the movement). The servo hydraulic test bench simulates the aircraft hydraulic system and provides corresponding driving pressure to components such as actuators, upper locks, and wheels according to the actual test requirements. Through the above functional accessories, this test bench can simulate the real installation, retraction, and taxiing state of the landing gear system. Therefore, it can complete the tests required for the landing gear system in the final assembly and flight test stages.

[0036] In this embodiment, according to Figure 1 After the installation of the multi-functional landing gear system integrated test bench is completed, various corresponding tests can be carried out, as follows:

[0037] 1) Loaded deployment and retraction test of the actuator cylinder

[0038] like Figure 5 As shown, the interface on the retraction actuator is connected to the servo hydraulic test bench. Pressure is applied to the actuator to push out the piston rod on the actuator. As the actuator extends, the landing gear completes the lowering action in the order of A→B→C in the attached diagram. Then, the pressure is adjusted according to the specifications to control the piston rod on the actuator to retract. The landing gear will then complete the retraction action in the order of C→B→A. This completes one load-bearing retraction test of the actuator. The test is judged to be qualified by comparing whether the actuator unlocks under the specified pressure, the retraction time, and the stability of the retraction process. Figure 5 In the diagram, H represents the direction of piston rod extension, I represents the pipeline connection to the servo hydraulic test bench, and J represents the direction of movement of the buffer support and wheel. Irrelevant structures have been omitted.

[0039] 2) Upper lock unlocking test

[0040] like Figures 6-7As shown, the interface of the upper lock actuator cylinder is connected to the servo hydraulic test bench. Pressure is applied to the actuator cylinder, pushing out the piston rod on the actuator cylinder. As the actuator cylinder extends, it pushes the rocker arm to rotate, thereby unlocking. The lock hook rotates under the drive of the landing gear locking ring, thereby unlocking. The locking process does not require pressure. The upper lock relies on the landing gear locking ring to push the lock hook to rotate in the opposite direction to the corresponding position. Then, the spring pulls the rocker arm to achieve mechanical locking. The test is judged by comparing whether the lock is unlocked under the specified pressure and the degree of flexibility in unlocking and locking. Figures 6-7 In the diagram, H represents the piston rod extension direction, I represents the pipeline connection to the servo hydraulic test bench, K represents the rocker arm rotation direction, L represents the lock hook rotation direction, M represents the landing gear locking ring movement direction, and R, S, T, and U represent the upper lock unlocking sequence. Irrelevant structures have been hidden.

[0041] 3) Static pressure test of buffer support

[0042] like Figure 8 As shown, with the landing gear in the lowered state, the servo hydraulic test bench drives the press to apply corresponding pressure to the landing gear, driving the buffer strut to compress. After a certain period of time, the pressure is slowly released, and the buffer strut naturally rebounds under the action of internal pressure. The test is judged by plotting the pressure-displacement curve. At the same time, the sealing performance can be judged by measuring the change of internal pressure of the buffer device before and after the test. Figure 8 In the diagram, N represents the buffer support in its natural state, O represents the buffer support in its compressed state, and X and Y represent the static pressure test sequence of the buffer support. Irrelevant structures have been omitted.

[0043] 4) Braking test

[0044] like Figure 9 As shown, the landing gear is subjected to corresponding pressure by a press to control the buffer strut to be in a compressed state. Then, the inertia wheel is rotated to drive the wheel to rotate until it reaches the theoretical speed of the wheel when the aircraft lands. Then, the inertia wheel servo motor is disconnected and the wheel brake is controlled by a hydraulic press until the wheel stops the inertia wheel. By comparing the time required for braking and the stability during the braking process, it can be judged whether it is qualified. Figure 9 In the diagram, I represents the servo hydraulic test bench with pipeline connection, P represents the rotation direction of the machine wheel, and Q represents the rotation direction of the inertia wheel. Irrelevant structures have been omitted.

[0045] In this embodiment, in order to more realistically simulate the ground environment, the surface friction coefficient of the inertial wheel 221 should be close to that of the actual ground.

[0046] The inertia wheel 221 can adjust its rotational inertia by replacing the weight-adding ring, thereby matching the aircraft's inertia when landing at different equivalents or speeds.

[0047] By replacing the landing gear bay interface simulation components of the corresponding specifications and adjusting the inertia wheel, this test bench can be used for various landing gears. Theoretically, as long as the range of motion of the landing gear does not exceed the capacity of the test bench, the test bench can be compatible.

[0048] This test bench can not only conduct various tests one by one to gradually adjust the landing gear system based on the test results, but also conduct all tests in sequence. For example, by performing unlocking, landing gear lowering, and braking tests in sequence, the entire working process of the landing gear system during aircraft landing can be realistically simulated.

[0049] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the scope of the invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A multifunctional landing gear system integrated test bench, used for testing on a microcomputer-controlled hydraulic press, comprising a hydraulic press, simulation components, and landing gear system components, characterized in that, The hydraulic press includes a crossbeam, a slider, and a base. The simulation components include a landing gear bay interface simulation component and a ground simulation component. The landing gear system components include a retraction and extension actuator, a shock strut, and a wheel assembly. The ground simulation component is mounted on the base and contacts the wheel assembly. The landing gear bay interface simulation component is mounted on the slider. The wheel assembly is connected to the shock strut. One end of the retraction and extension actuator is connected to the landing gear bay interface simulation component, and the other end of the retraction and extension actuator is connected to the shock strut. The landing gear bay interface simulation component includes a buffer strut connector for connecting the buffer strut, a retraction and extension actuator connector for connecting the actuator, an upper lock connector for connecting the upper lock, and a landing gear bay floor plate. The retraction and extension actuator connector and the upper lock connector are installed at the front end of the landing gear bay floor plate, the landing gear bay interface through hole for installing the landing gear bay interface simulation component is provided in the middle of the landing gear bay floor plate, and the buffer strut connector is provided at the rear end of the landing gear bay floor plate. The ground simulation component includes an inertia wheel, a servo motor, a belt, a connecting shaft, a weight-adding ring, and a ground simulation base plate. The rear end of the ground simulation base plate has a pair of mounting seats for the connecting shaft, and a rotation through-hole for accommodating the rotation of the inertia wheel is located between the mounting seats. One end of the inertia wheel and one end of the belt are respectively mounted on the connecting shaft, and a weight-adding ring for changing the inertia wheel's inertia is located on the connecting shaft. The other end of the belt is nested on the output shaft of the servo motor. The front end of the ground simulation base plate has a ground simulation through-hole for mounting the ground simulation component. The inertia wheel contacts the aircraft wheel assembly, simulating the motion of the aircraft wheels relative to the ground during takeoff and landing. This test bench is used in conjunction with a servo hydraulic test bench, and the relevant positions of each joint in the landing gear bay interface simulation component are consistent with the relevant positions of the interface used to install the landing gear system in the aircraft landing gear bay, so as to simulate the real state of the connection between each component in the landing gear system and the fuselage; the ground simulation component simulates the motion state of the landing gear wheels relative to the ground when the aircraft lands through the rotation of the inertia wheel; the hydraulic press applies pressure to the entire landing gear system to simulate the actual load conditions of the landing gear in a static state or during takeoff and landing.

2. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, The buffer strut joint and the upper lock joint are welded to the landing gear bay floor plate via weld seams.

3. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, The buffer support joint is provided with a pin hole for connecting the buffer support.

4. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, The output shaft of the servo motor is parallel to the connecting shaft.

5. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, A frustum for mounting the inertia wheel is provided on the connecting shaft.

6. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, The connecting shaft is equipped with a threaded ring for mounting the belt.

7. The multifunctional landing gear system integrated test bench according to claim 1, characterized in that, The weight-adding ring is locked onto the connecting shaft by a lock nut.

8. A multi-functional landing gear system integrated test bench according to any one of claims 1 to 7, characterized in that, The servo hydraulic test bench simulates the aircraft hydraulic system, providing driving pressure to the test bench components according to actual test requirements. It simulates the actual installation, retraction, and taxiing of the landing gear system. Through this test bench, the tests required for the landing gear system during the final assembly and flight test phases can be completed.

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