Multifunctional undercarriage system comprehensive test bench

Abstract

A multifunctional undercarriage system comprehensive test bench is used for testing on a hydraulic machine controlled by a microcomputer and comprises the hydraulic machine, a simulation part and an undercarriage system part, the hydraulic machine comprises a cross beam, a sliding block and a base, and the simulation part comprises an undercarriage cabin interface simulation part and a ground simulation part. The undercarriage system part comprises a retractable actuating cylinder, a buffer strut and an airplane wheel assembly, a ground simulation part is mounted on the base, the ground simulation part is in contact with the airplane wheel assembly, an undercarriage cabin interface simulation part is mounted on the sliding block, the airplane wheel assembly is connected with the buffer strut, one end of the retractable actuating cylinder is connected with the undercarriage cabin interface simulation part, and the other end of the retractable actuating cylinder is connected with the airplane wheel assembly. And the other end of the retractable actuating cylinder is connected with the buffer strut. According to the invention, all tests required to be carried out in the final assembly and test flight stages of the undercarriage system can be simulated, the final assembly period can be greatly shortened in batch production models, tests can be carried out in advance in aircraft development tasks, and sufficient data support and improvement period are provided for design.

Description

Technical Field

[0001] The invention relates to the technical field of landing gear testing, and in particular to a multifunctional landing gear system integrated test bench. Background Art

[0002] The landing gear is an important accessory device used for take-off, landing and taxiing on the ground. A complete landing gear system needs to have basic functions such as support, buffering, taxiing, retraction and braking. Generally, the buffer strut with wheels provides support, buffering, taxiing and braking functions, and the retraction and extension actuator provides retraction and auxiliary support functions.

[0003] Since the landing gear system consists of many components and each component has independent functions, most aircraft manufacturing companies currently adopt a flat manufacturing model, with different hydraulic parts manufacturers manufacturing each component of the landing gear system separately. Finally, the components are directly assembled with the fuselage during the aircraft assembly stage, and various verification tests are carried out and debugged accordingly. As a result, the coordinated working performance of a large number of components in the landing gear system must be verified during the assembly stage, such as the retraction and extension performance verification of the retractable actuator after connecting to the landing gear, the static pressure load performance verification of the buffer strut at the working angle, etc. In addition, the verification of ground braking and taxiing performance can only be carried out during the aircraft test flight.

[0004] In summary, according to the current landing gear system assembly and test process, a large number of coordination tests must be carried out during the final assembly and flight test stages, which can easily lead to a lengthy and cumbersome landing gear system assembly process and require repeated disassembly, assembly and debugging, ultimately affecting the assembly efficiency of the entire aircraft. Summary of the invention

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

[0006] The technical problem solved by the present invention is achieved by adopting the following technical solutions: A multifunctional landing gear system comprehensive test bench is used for testing on a hydraulic press controlled by a microcomputer, and includes a hydraulic press, a simulation component and a landing gear system component, wherein the hydraulic press includes a crossbeam, a slider and a base, the simulation component includes a landing gear compartment interface simulation component and a ground simulation component, the landing gear system component includes a retractable actuator cylinder, a buffer strut and a wheel assembly, the base is provided with a ground simulation component, the ground simulation component is in contact with the wheel assembly, the slider is provided with a landing gear compartment interface simulation component, the wheel assembly is connected to the buffer strut, one end of the retractable actuator cylinder is connected to the landing gear compartment interface simulation component, and the other end of the retractable actuator cylinder is connected to the buffer strut; The landing gear bay interface simulation component includes a buffer strut joint for connecting a buffer strut, a retracting and extending actuating cylinder joint for connecting an actuating cylinder, an upper lock joint for connecting an upper lock, and a landing gear bay bottom plate. The retracting and extending actuating cylinder joint and the upper lock joint are installed at the front end of the landing gear bay bottom plate. A 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 bottom plate. A buffer strut joint is provided at the rear end of the landing gear bay bottom plate. The ground simulation component includes an inertia wheel, a servo motor, a belt, a connecting shaft, a weight-increasing ring and a ground simulation base plate, wherein a pair of mounting seats for installing the connecting shaft are arranged on one side of the rear end of the ground simulation base plate, and a rotating through hole for accommodating the rotation of the inertia wheel is arranged between the pair of mounting seats, one end of the inertia wheel and the belt are respectively installed on the connecting shaft, and a weight-increasing ring for replacing the inertia of the inertia wheel is arranged on the connecting shaft; the other end of the belt is nested on the output shaft of the servo motor, and a ground simulation through hole for installing the ground simulation component is arranged at the front end of the ground simulation base plate; the inertia wheel is in contact with the wheel assembly, and the inertia wheel simulates the movement state of the wheel relative to the ground when the aircraft is taxiing and landing.

[0007] In the present invention, the buffer strut joint and the upper lock joint are welded to the bottom plate of the landing gear compartment through a weld.

[0008] In the present invention, a pin hole for connecting the buffer pillar is provided on the buffer pillar joint.

[0009] In the present invention, the output shaft of the servo motor is parallel to the connecting shaft.

[0010] In the present invention, a truncated table for mounting the inertia wheel is arranged on the connecting shaft.

[0011] In the present invention, a threaded ring for mounting a belt is provided on the connecting shaft.

[0012] In the present invention, the weight-increasing ring is locked on the connecting shaft by a locking nut.

[0013] In the present invention, the test bench is used in conjunction with the servo-hydraulic test bench, wherein the relevant positions of the joints in the landing gear bay interface simulation component are consistent with the relevant positions of the interfaces in the aircraft landing gear bay for installing the landing gear system, so as to simulate the actual state of connection between the components in the landing gear system and the fuselage; the ground simulation component simulates the movement state of the landing gear wheel 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 condition of the landing gear in a static state or during take-off and landing; the servo-hydraulic test bench simulates the aircraft hydraulic system, provides driving pressure for the components of the test bench according to the actual needs of the test, and simulates 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.

[0014] Beneficial effects: The present invention achieves the purpose of simulating all the tests required for the landing gear system in the final assembly and test flight stages by simulating the actual installation, retraction, extension and taxiing states of the landing gear system. This can not only significantly shorten the final assembly cycle in mass production models, but also significantly advance the landing gear system tests that were originally required to be performed randomly in aircraft development tasks, thereby providing sufficient data support and improvement cycle for the design. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a structural schematic diagram of a preferred embodiment of the present invention.

[0016] Figure 2 It is a schematic diagram of the structure of the landing gear bay interface simulation component in a preferred embodiment of the present invention.

[0017] Figure 3 It is a schematic diagram of the structure of the ground simulation component in the preferred embodiment of the present invention.

[0018] Figure 4 It is an exploded view of the ground simulation component in the preferred embodiment of the present invention.

[0019] Figure 5 It is a schematic diagram of a test bench in a preferred embodiment of the present invention conducting a load-retracting and retracting test of an actuator.

[0020] Figure 6 This is a schematic diagram of an upper lock unlocking test performed on a test bench in a preferred embodiment of the present invention.

[0021] Figure 7 for Figure 6 Schematic diagram of the unlocking sequence under the partial enlarged view at W in the middle.

[0022] 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.

[0023] Fig. 9 This is a schematic diagram of a brake test performed on a test bench in a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0024] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below with reference to specific diagrams.

[0025] See also Figures 1 to 4A multifunctional landing gear system comprehensive test bench is used for testing on a microcomputer-controlled hydraulic press, comprising a hydraulic press 1, a simulation component 2 and a landing gear system component 3, wherein the hydraulic press 1 comprises a crossbeam 11, a slider 12 and a base 13, the simulation component 2 comprises a landing gear compartment interface simulation component 21 and a ground simulation component 22, the landing gear system component 3 comprises a retractable actuator 31, a buffer strut 32 and a wheel assembly 33, the base 13 is provided with a ground simulation component 22, the ground simulation component 22 is in contact with the wheel assembly 33, the landing gear compartment interface simulation component 21 is mounted on the slider 12, the wheel assembly 33 is connected to the buffer strut 32, one end of the retractable actuator 31 is connected to the landing gear compartment interface simulation component 21, and the other end of the retractable actuator 31 is connected to the buffer strut 32; The landing gear compartment interface simulation component 21 includes a buffer strut joint 211 for connecting a buffer strut, a retracting and extending actuating cylinder joint 212 for connecting an actuating cylinder, an upper lock joint 213 for connecting an upper lock, a landing gear compartment bottom plate 214 and a weld 215. The retracting and extending actuating cylinder joint 212 and the upper lock joint 213 are installed at the front end of the landing gear compartment bottom plate 214. A landing gear compartment interface through hole is provided in the middle of the landing gear compartment bottom plate 214 for installing the landing gear compartment interface simulation component 21. The rear end of the landing gear compartment bottom plate 214 is provided with a buffer strut joint 211, and the buffer strut joint 211 and the upper lock joint 213 are welded to the landing gear compartment bottom plate 214 through a weld 215. 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-increasing ring 226, a rear weight-increasing ring 227, a rear locking nut 228 and a ground simulation base plate 229, wherein a pair of mounting seats for mounting the connecting shaft 224 are provided on one side of the rear end of the ground simulation base plate 229, and a rotating 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 installed on the connecting shaft 224, and a The front weight-increasing ring 226 and the rear weight-increasing ring 227 are used to replace the inertia of the inertia wheel 221. The front weight-increasing ring 226 is locked on the connecting shaft 224 by the front locking nut 225, and the rear weight-increasing ring 227 is locked on the connecting shaft 224 by the rear locking nut 228. A belt 223 is embedded on the output shaft of the servo motor 222, and a ground simulation through hole is provided at the front end of the ground simulation base plate 229 for installing the ground simulation component 22. The inertia wheel 221 contacts the wheel assembly 33, and the inertia wheel 221 simulates the movement state of the wheel relative to the ground when the aircraft is taxiing and landing.

[0026] In this embodiment, the buffer pillar joint 211 is provided with a pin hole for connecting the buffer pillar.

[0027] In this embodiment, the output shaft of the servo motor 222 is parallel to the connecting shaft 224 .

[0028] In this embodiment, a truncated cone for mounting the inertia wheel 221 is disposed on the connecting shaft 224 .

[0029] In this embodiment, a threaded ring for mounting the belt 223 is provided on the connecting shaft 224 .

[0030] In this embodiment, the test bench needs to be used in conjunction with the servo-hydraulic test bench, wherein the relevant positions of the joints in the landing gear bay interface simulation component 21 are consistent with the relevant positions of the interfaces for installing the landing gear system in the aircraft landing gear bay, and are used to simulate the actual state of connection between the components in the landing gear system and the fuselage; the ground simulation component 22 simulates the movement 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 take-off and landing (including the weight of the aircraft and various loads generated during movement); the servo-hydraulic test bench simulates the hydraulic system of the aircraft, and provides corresponding driving pressure for the actuator, upper lock, wheels and other components according to the actual test needs. Through the above functional accessories, the test bench can simulate the actual installation, retraction and taxiing state of the landing gear system, and therefore can complete the tests required for the landing gear system in the final assembly and flight test stages.

[0031] In this embodiment, according to Figure 1 After completing the installation of the multifunctional landing gear system integrated test bench, the corresponding tests can be carried out, as follows: 1) Actuator retraction and extension test with load like Figure 5 As shown, the interface on the retractable actuator is connected to the servo hydraulic test bench, the actuator is pressurized, and the piston rod on the actuator is pushed out. As the actuator is extended, the landing gear completes the lowering action in the order of A→B→C in the attached figure. Then, the pressure is adjusted according to the specification requirements to control the piston rod on the actuator to contract, and the landing gear will complete the retraction action in the order of C→B→A. In this way, a retractable test of the actuator with load is completed. Whether the test is qualified is determined by comparing whether the actuator is unlocked, the retracting time, and the stability of the retracting process under the specified pressure; Figure 5 In the figure, H is the extension direction of the piston rod, I is the pipeline connection servo hydraulic test bench, J is the movement direction of the buffer support and the wheel, and irrelevant structures have been hidden; 2) Upper lock unlocking test like Figures 6 and 7As shown, the interface of the upper lock actuator is connected to the servo hydraulic test bench, and the actuator is pressurized to push out the piston rod on the actuator. As the actuator is extended, the rocker arm is pushed to rotate to unlock, and the lock hook is driven by the landing gear lock ring to rotate to unlock; there is no need to pressurize the locking process. After the upper lock relies on the landing gear lock ring to push the lock hook to rotate in the opposite direction to the corresponding position, the spring pulls the rocker arm to achieve mechanical locking. Whether the test is qualified is determined by comparing whether it is unlocked under the specified pressure, and the degree of unlocking and locking flexibility; Figures 6 and 7 In the figure, H is the extension direction of the piston rod, I is the pipeline connection servo hydraulic test bench, K is the rotation direction of the rocker arm, L is the rotation direction of the lock hook, M is the movement direction of the landing gear lock ring, R, S, T, U are the unlocking order of the upper lock, and irrelevant structures have been hidden; 3) Static pressure test of buffer pillar like Figure 8 As shown, when the landing gear is lowered, the servo hydraulic test bench drives the press to apply corresponding pressure to the landing gear, driving the buffer strut to compress, and slowly unloading after a certain period of time. The buffer strut naturally rebounds under the action of the internal pressure. Whether the test is qualified is judged by drawing the pressure-displacement curve. At the same time, whether the sealing performance is qualified can also be judged by measuring the change in the internal pressure of the buffer device before and after the test; Figure 8 In the figure, N means the buffer pillar is in the natural state, O means the buffer pillar is in the compressed state, X and Y are the static pressure test sequence of the buffer pillar, and irrelevant structures have been hidden; 4) Braking test like Fig. 9 As shown, a corresponding pressure is applied to the landing gear through a press to control the buffer strut to be in a compressed state, and then the inertia wheel is rotated to drive the wheel to rotate until the theoretical speed of the wheel is reached when the aircraft lands, and then the inertia wheel servo motor is disconnected while the wheel brake is controlled by a hydraulic press until the wheel stops the inertia wheel. Whether it is qualified can be judged by comparing the time required for braking and the stability during the braking process; Fig. 9 In the figure, I is the pipeline connection servo hydraulic test bench, P is the rotation direction of the wheel, Q is the rotation direction of the inertia wheel, and irrelevant structures have been hidden.

[0032] In this embodiment, in order to simulate the ground environment more realistically, the surface friction coefficient of the inertia wheel 221 should be close to that of the actual ground; The inertia of the inertia wheel 221 can be adjusted by replacing the weight-increasing ring, and thereby match the inertia of the aircraft when landing at different equivalents or different speeds; By replacing the landing gear bay interface simulation components of corresponding specifications and adjusting the inertia wheel, this test bench can be used for a variety of landing gears. In theory, as long as the movement range of the landing gear does not exceed the accommodation space of the test bench, the test bench can be compatible; This test bench can not only carry out various tests one by one so as to gradually debug the landing gear system according to the test results, but also carry out all the tests in a continuous manner. For example, the unlocking, landing gear lowering and braking tests can be carried out in sequence to truly simulate the entire working process of the landing gear system when the aircraft lands.

[0033] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the attached claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved.

Claims

1. A multifunctional landing gear system comprehensive test bench, which is tested on a hydraulic press controlled by a microcomputer, including 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 compartment interface simulation component and a ground simulation component. The landing gear system components include a retractable actuator cylinder, a buffer strut and a wheel assembly. The base is equipped with a ground simulation component, the ground simulation component is in contact with the wheel assembly, the slider is equipped with a landing gear compartment interface simulation component, the wheel assembly is connected to the buffer strut, one end of the retractable actuator cylinder is connected to the landing gear compartment interface simulation component, and the other end of the retractable actuator cylinder is connected to the buffer strut.

2. A multifunctional landing gear system integrated test bench according to claim 1, characterized in that: The landing gear bay interface simulation component includes a buffer strut joint for connecting a buffer strut, a retracting and extending actuating cylinder joint for connecting an actuating cylinder, an upper lock joint for connecting an upper lock, and a landing gear bay bottom plate. The retracting and extending actuating cylinder joint and the upper lock joint are installed at the front end of the landing gear bay bottom plate. A 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 bottom plate. A buffer strut joint is provided at the rear end of the landing gear bay bottom plate. The ground simulation component includes an inertia wheel, a servo motor, a belt, a connecting shaft, a weight-increasing ring and a ground simulation base plate, wherein a pair of mounting seats for installing the connecting shaft are arranged on one side of the rear end of the ground simulation base plate, and a rotating through hole for accommodating the rotation of the inertia wheel is arranged between the pair of mounting seats, one end of the inertia wheel and the belt are respectively installed on the connecting shaft, and a weight-increasing ring for replacing the inertia of the inertia wheel is arranged on the connecting shaft; the other end of the belt is nested on the output shaft of the servo motor, and a ground simulation through hole for installing the ground simulation component is arranged at the front end of the ground simulation base plate; the inertia wheel is in contact with the wheel assembly, and the inertia wheel simulates the movement state of the wheel relative to the ground when the aircraft is taxiing and landing.

3. A multifunctional landing gear system integrated test bench according to claim 2, characterized in that: The buffer strut joint and the upper lock joint are welded to the landing gear compartment bottom plate by welds.

4. A multifunctional landing gear system integrated test bench according to claim 2, characterized in that: The buffer pillar joint is provided with a pin shaft hole for connecting the buffer pillar.

5. The multifunctional landing gear system integrated test bench according to claim 2, characterized in that: The output shaft of the servo motor is parallel to the connecting shaft.

6. The multifunctional landing gear system integrated test bench according to claim 2, characterized in that: A round table for mounting the inertia wheel is arranged on the connecting shaft.

7. The multifunctional landing gear system integrated test bench according to claim 2, characterized in that: A threaded ring for mounting a belt is provided on the connecting shaft.

8. The multifunctional landing gear system integrated test bench according to claim 2, characterized in that: The weight-increasing ring is locked on the connecting shaft by a locking nut.

9. A multifunctional landing gear system comprehensive test bench according to any one of claims 1 to 8, characterized in that: This test bench is used in conjunction with the servo-hydraulic test bench, and the relevant positions of the joints in the landing gear bay interface simulation components are consistent with the relevant positions of the interfaces in the aircraft landing gear bay for installing the landing gear system, so as to simulate the actual state of connection between the components in the landing gear system and the fuselage; the ground simulation component simulates the movement 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 take-off and landing; the servo-hydraulic test bench simulates the aircraft hydraulic system, provides driving pressure for the components of the test bench according to the actual needs of the test, and simulates the actual installation, retraction and taxiing state of the landing gear system. This test bench can complete the tests required for the landing gear system in the final assembly and flight test stages.

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