CN114754999A - Airplane wheel brake response test device and test method for airplane landing gear - Google Patents

Abstract

The invention relates to an aircraft landing gear wheel brake response test device and a test method, which can adjust the installation position of a load simulation oil cylinder through a set position adjustment component, and then adjust the installation position of the landing gear component, so that the test device can be used for different models and sizes. At the same time, the position adjustment assembly adopts the screw assembly, the roller assembly and the slide rail mechanism to realize the adjustment in the vertical direction, which improves the stability of the action in the vertical direction; for the hub wheel drive assembly, a set of A remote-controllable emergency brake assembly is used to deal with emergencies during the test; at the same time, a response measurement system is set on the landing gear assembly to measure the dynamic response of the landing gear during rollout braking; in addition, the hub wheel assembly By setting the replaceable auxiliary hub wheel and inertia wheel, while accurately simulating the speed of the body, configure the auxiliary hub wheel and inertia wheel of different masses to realize the simulation of body energy regulation.

Description

A test device and test method for wheel braking response of aircraft landing gear

technical field

The invention relates to the technical field of aircraft landing gear design and manufacture, and more particularly, to an aircraft landing gear wheel brake response test device and a test method.

Background technique

The dynamic response of the aircraft landing gear during the rollout braking process is one of the important topics in the research of aircraft landing gear dynamics. When the design parameters of the braking system do not match, it may cause the landing gear to produce "walking", "chattering", "howling" and other failure phenomena during the braking process. more serious accidents. Therefore, in the process of designing and manufacturing the aircraft in our country, it is necessary to carry out the simulation test of the dynamic response of the aircraft landing gear in the rolling braking process.

However, in the prior art, the landing gear system is passively detected only after a problem with the landing gear system is found when the newly developed aircraft rolls. It not only increases the difficulty of solving the problem, but also increases the research cost, and affects the development cycle of the aircraft. Therefore, it is necessary to conduct a test simulation of the aircraft landing gear in advance to check whether the function and main performance indicators of the landing gear meet the design requirements. In the process, it is necessary to realize the matching design of the airframe speed and airframe energy, so as to provide a test basis for the airworthiness of the landing gear.

The existing simulation test of the braking system of the aircraft landing gear adopts the method of adjusting the rotational speed of the inertia wheel to realize the simulation of the body energy, and tests the braking distance, time, torque, etc., to test the performance of the braking system. The mechanical characteristics of the corresponding landing gear are not tested, because the existing testing technology only focuses on the simulation of the airframe energy and does not simulate the corresponding airframe speed, so it is impossible to simulate the dynamic characteristics of the landing gear under the configuration of a specific type of braking system, resulting in the dynamic characteristics of the landing gear. The characteristics have not been fully tested and cannot provide a basis for the optimal design of the combined mechanism of the landing gear and braking system.

SUMMARY OF THE INVENTION

In order to overcome the problem that the simulation test of the aircraft landing gear and the braking system in the prior art only tests the performance of the braking system and cannot effectively simulate and test the mechanical properties of the landing gear, the present invention proposes an aircraft landing gear braking response test device and a test method.

An aircraft landing gear wheel brake response test device, comprising a test frame, a load simulating oil cylinder, a landing gear assembly, a hub wheel assembly and a driving assembly, wherein the load simulating oil cylinder is installed on the upper end of the test frame through a position adjusting assembly, The load simulating oil cylinder moves in the vertical direction along the test frame through the position adjusting assembly, the landing gear assembly is fixedly installed on the lower end of the load simulating oil cylinder, and the hub wheel assembly is installed on the test frame the lower end of the frame, the drive assembly is connected with the hub wheel assembly to drive the hub wheel assembly to rotate, the hub wheel assembly includes a hub wheel contacting with the wheel of the landing gear assembly, and is arranged on the Auxiliary hub wheels and hub wheel support assemblies on both sides of the hub wheel, the hub wheels and auxiliary hub wheels are mounted on the hub wheel support assemblies, and the drive assembly is connected with the hub wheel support assemblies to drive the hub wheels and the auxiliary hub wheel rotates.

Further, as a preferred technical solution, the position adjustment assembly includes a lift adjustment mechanism and a beam mechanism, the lift adjustment mechanism is respectively connected to the test frame and the beam mechanism, and the upper end of the load simulation cylinder is connected to the beam mechanism, so The beam mechanism drives the load simulation oil cylinder to move in the vertical direction through the lift adjustment mechanism.

Further, as a preferred technical solution, the lifting adjustment mechanism includes a lead screw assembly, and the position adjustment assembly further includes a test frame beam, the test frame beam is arranged below the beam mechanism, and the lead screw assembly is sequentially connected to the test frame. Describe the top of the test frame, the beam mechanism and the test frame beam.

Further, as a preferred technical solution, it also includes a hanging basket assembly, the two side walls of the hanging basket assembly are slidably connected to the slide rails provided on the two side walls of the test frame through the roller assembly; the load simulation oil cylinder is installed in the test frame. In the gondola assembly, the landing gear assembly is fixedly connected with the bottom end of the gondola assembly.

Further, as a preferred technical solution, the hub wheel support assembly includes a hub wheel support shaft and a hub wheel support frame, the hub wheel and the auxiliary hub wheel are fixedly installed on the hub wheel support shaft, and the hub wheel support shaft is It is erected on the hub wheel support frame and can rotate along the hub wheel support frame, and the drive assembly is connected with the hub wheel support shaft to drive the hub wheel support shaft to drive the hub wheel and the auxiliary hub wheel along the edge. The hub wheel support frame rotates.

Further, as a preferred technical solution, the hub wheel assembly further includes an inertia wheel, and the inertia wheel is detachably mounted on the hub wheel support assembly.

Further, as a preferred technical solution, the hub wheel assembly further includes an emergency braking assembly and a torque sensor, and the emergency braking assembly includes an emergency braking mechanism arranged on the hub wheel support assembly and a connection with the emergency braking mechanism. A pressure supply and air storage mechanism; the torque sensor is mounted on the hub wheel support assembly.

Further, as a preferred technical solution, a response measurement system is also included, and the response measurement system is connected with the landing gear assembly to measure the dynamic response data of the landing gear assembly during the rollout braking process.

An aircraft landing gear wheel braking response test method, comprising the following steps:

S10. Complete the assembly of the test device described in any one of claims 1-8 and the setting of initial test data;

S20. According to the pressing load required for the test, the wheel is pressed on the wheel hub surface by the load simulation oil cylinder;

S30. Calculate the target rotational speed of the drive assembly according to the simulated body speed to ensure that the linear speed of the hub wheel track surface is equal to the body speed, and then start the drive assembly;

S40. The hub wheel rotates with the machine wheel in the opposite direction. After the speed of the standby wheel is stable, set and apply the corresponding electric inertia according to the test requirements. The drive component inputs additional energy or reverse braking energy according to the set electric inertia, and starts the machine at the same time. wheel brake assembly until the wheels are fully braked;

S50. During the braking process, the response measurement system synchronously collects the dynamic response data of the landing gear assembly;

S60. According to the dynamic response data of the landing gear assembly, carry out the dynamic response analysis of the landing gear assembly, and evaluate the dynamic performance of the landing gear assembly.

Further, as a preferred technical solution, step S10 specifically includes:

Adjust the load simulation cylinder to match the position of the landing gear assembly to be tested through the position adjustment assembly;

installation of landing gear assemblies and response measurement systems;

Install the corresponding wheel and wheel brake assembly on the landing gear assembly;

According to the energy of the simulated body required for the test, calculate the mass of the auxiliary hub wheel and inertia wheel to be assembled and the required electric inertia, so as to realize the infinite simulation of the body energy;

Install the corresponding auxiliary hub wheel and inertia wheel, and set the electric inertia of the drive assembly.

Compared with the prior art, the beneficial effects of the technical solution of the present invention are:

The installed position adjustment component adjusts the load to simulate the installation position of the oil cylinder, and then adjusts the installation position of the landing gear assembly, so that the test device can perform simulated tests on landing gear assemblies of different sizes. The roller assembly is installed in the vertical direction to cooperate with the slide rail mechanism to improve the stability of the vertical direction. At the same time, for the hub wheel drive assembly, a remote-controllable emergency brake assembly is installed to deal with unexpected accidents during the test process. , A response measurement system is set on the landing gear assembly to measure the dynamic response of the landing gear during the rollout braking process; in addition, the hub wheel assembly can accurately simulate the speed of the body through the replaceable auxiliary hub wheels and inertia wheels. At the same time, it is equipped with auxiliary hub wheels and inertia wheels of different masses to realize the simulation of airframe energy regulation, improve the authenticity of the dynamic response test simulation of the aircraft landing gear during the rollout braking process, and better adapt the performance of the landing gear structure and braking system. The matching optimization design provides the basis.

Description of drawings

Figure 1 is a schematic structural diagram of the present invention.

FIG. 2 is an enlarged schematic view of the position adjustment assembly of the present invention.

FIG. 3 is a structural block diagram of the present invention.

Figure 4 is a flow chart of the present invention.

Detailed ways

The present invention will be further described below in conjunction with specific embodiments.

The same or similar numbers in the drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if there are terms “upper”, “lower”, “left” and “right” , "top", "bottom", "inside", "outside" and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or It is implied that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation, so the terms describing the positional relationship in the drawings are for illustrative purposes only and should not be construed as limitations on this patent.

In addition, if there are terms such as "first" and "second", they are only used for descriptive purposes, and are mainly used to distinguish different devices, elements or components. The specific types and structures may be the same or different, and are not used to indicate or The relative importance and quantity of the indicated means, elements or components are implied and should not be construed as indicating or implying relative importance.

Example 1

In order to overcome the problem that the simulation test of the aircraft landing gear and braking system in the prior art only tests the performance of the braking system and cannot effectively simulate and test the mechanical properties of the landing gear, this embodiment provides a real simulation test in the early stage of the design of the landing gear system. Airframe motion energy and speed, landing gear roll braking process, testing landing gear braking response, and research on the impact of wheel braking on the structural characteristics of the landing gear. The analysis method of the impact of various harmful vibrations on the fatigue life of the landing gear; it is also used to study the failure phenomena such as "walking", "buffering" and "howling" of the landing gear caused by wheel braking, explore the mechanism, analyze the causes, It provides a basis for the optimal design of the performance adaptation of the landing gear structure and the braking system, so as to find problems in advance, avoid technical risks, shorten the development cycle, and save development costs.

An aircraft landing gear wheel brake response test device disclosed in this embodiment, as shown in Figures 1-2, includes a test frame 1, a load simulation cylinder 2, a gondola assembly 7, a landing gear assembly 3, a hub wheel assembly 4 and The drive assembly 5, the load simulation cylinder 2 are installed on the upper end of the test frame 1 through the position adjustment assembly 6, the load simulation cylinder 2 is installed in the gondola assembly 7, and the load simulation cylinder 2 is installed along the test frame 1 through the position adjustment assembly 6. Moving in the vertical direction, the two side walls of the gondola assembly 7 are slidably connected with the slide rail mechanism provided on the two side walls of the test frame 1 through the roller assembly 8 to improve the stability of the vertical movement; the landing gear assembly 3 passes through The landing gear mounting fixture 32 is fixedly connected to the bottom end of the gondola assembly 7 , the lower end of the landing gear assembly 3 is mounted with an organic wheel 31 and a wheel brake assembly 311 matching the wheel 31 , and the hub wheel assembly 4 is installed on the test stand 1 The lower end of the drive assembly 5 is connected with the wheel hub assembly 4 to drive the wheel hub assembly 4 to rotate.

In this embodiment, the wheel hub assembly 4 includes a wheel hub 41 in contact with the wheel 31 , an auxiliary wheel hub 42 disposed on both sides of the wheel hub 41 , a wheel hub support assembly 43 , an inertia wheel 44 , an emergency brake assembly 45 , and The torque sensor 46 , the wheel hub 41 , the auxiliary wheel hub 42 , the inertia wheel 44 , the emergency brake assembly 45 and the torque sensor 46 are all mounted on the wheel hub support assembly 43 , and the drive assembly 5 is connected with the wheel hub support assembly 43 to drive the wheel hub 41 And the auxiliary hub wheel 42 rotates.

In this embodiment, as shown in FIG. 3 : the auxiliary hub wheel 42 and the inertia wheel 44 cooperate with the drive assembly 5 to realize the speed control of the hub wheel 41 , so as to pass the mechanical inertia of the hub wheel 41 , the auxiliary hub wheel 42 and the inertia wheel 44 And the drive component 5 simulates the inertia combination and speed control, realizes the simulation of the motion energy and speed of the aircraft body, simulates the ground load of the wheel 31 of the landing gear component 3 through the load simulation cylinder 2, and simulates the actual rolling process of the landing gear component 3. Conditions The brake is carried out through the wheel brake assembly 311, so as to measure the dynamic response of the landing gear assembly 3 in real time, and through the analysis of the response data, find out the design parameters of the wheel brake assembly 311 and its "buffering" to the landing gear assembly 3, The root cause of problems such as "walking" and "howling". It provides research basis for the performance improvement, improvement and optimization of the structure of the landing gear assembly 3 and the wheel brake assembly 311.

In this embodiment, since the rotational speed of the wheel hub 41 needs to meet the rolling requirement of the wheel 31 of the landing gear assembly 3 , the rotational speed of the wheel hub 41 needs to be consistent with the rotational speed of the wheel 31 , then a replaceable auxiliary wheel 42 is provided. With the inertia wheel 44, the auxiliary hub wheel 42 or the inertia wheel 44 of different masses can be configured to realize the energy regulation simulation while the rotation speed of the hub wheel 41 and the wheel 31 are consistent.

In addition, the provided emergency brake assembly 45 can deal with unexpected accidents in the test process, for example, to prevent the wheel 31 from running on the hub wheel 41 through the wheel brake assembly 311, which is prone to accidents such as tire blowout, resulting in equipment damage. The replacement of the auxiliary hub wheel and the inertia wheel is provided, and the auxiliary hub wheel and inertia wheel of different masses are configured while the speed of the body is constant, so as to realize the simulation of the energy regulation of the body, ensure the integrity of the test data, and better serve the landing gear. Provide the basis for the optimal design of the structure and the performance of the braking system.

In this embodiment, the wheel hub support assembly 43 includes a wheel hub support shaft 431 and a wheel hub support frame 432. The wheel hub 41, the auxiliary wheel hub 42, the inertia wheel 44, the emergency brake assembly 45 and the torque sensor 46 are all fixedly mounted on the hub. On the wheel support shaft 431, the hub wheel support shaft 431 is erected on the hub wheel support frame 432 and can rotate along the hub wheel support frame 432. The drive assembly 5 is connected with the hub wheel support shaft 431 to drive the hub wheel support shaft 431 to drive the hub wheel 41 and the hub wheel support shaft 431. The auxiliary wheel hub 42 rotates along the wheel hub support frame 432 .

As a preferred embodiment, the emergency braking assembly 45 includes an emergency braking mechanism 451 disposed on the hub wheel supporting shaft 431 of the hub wheel supporting assembly 43 and a pressure supply and air storage mechanism 452 connected to the emergency braking mechanism 451; the driving assembly 5 includes a driving motor .

In addition, in this embodiment, the bottom end of the test stand 1 is fixedly installed on the ground, and a foundation pit 10 is provided downward on the ground. The hub wheel 41 and the auxiliary hub wheel 42 are located in the foundation pit 10, and the hub wheel support assembly 43 It is erected on the ground on both sides of the foundation pit 10 .

In this embodiment, the position adjustment assembly 6 includes a lift adjustment mechanism 61 and a beam mechanism 62. The lift adjustment mechanism 61 is respectively connected to the test frame 1 and the beam mechanism 62. The upper end of the load simulation cylinder 2 is connected to the beam mechanism 62. The beam mechanism 62 The load simulating oil cylinder 2 is driven to move in the vertical direction along the test stand 1 by the lift adjusting mechanism 61 .

As a preferred embodiment, the lift adjustment mechanism 61 includes a screw assembly, and the position adjustment assembly 6 further includes a test frame beam 63. The test frame beam 63 is arranged below the beam mechanism 62, and the screw assembly is sequentially connected to the top of the test frame 1 and the beam mechanism 62. and test frame beams 63 .

That is, the two ends of the screw assembly are respectively connected to the top of the test rack 1 and the test rack beam 63, and pass through the beam mechanism 62. Therefore, the screw assembly can drive the beam mechanism 62 to move in the vertical direction during the rotation process, and then The installation position of the landing gear assembly 3 can be adjusted to install the landing gear assembly 3 of different specifications.

Therefore, in this embodiment, the installation position of the load simulation cylinder 2 is adjusted through the provided position adjustment assembly 6, and then the installation position of the landing gear assembly 3 is adjusted, so that the test device of this embodiment can be used for different types of landing gear assemblies 3. Carry out a simulation test; at the same time, the lifting adjustment mechanism 61 of the position adjustment assembly 6 is realized by a screw assembly, which can shorten the adjustment stroke. Improve the stability of vertical movement.

Example 2

The present embodiment discloses an aircraft landing gear wheel brake response test device. On the basis of the first embodiment, the present embodiment discloses another implementation manner of the position adjustment assembly 6 .

In this embodiment, the position adjustment assembly 6 also includes a level adjustment mechanism, the level adjustment mechanism includes a horizontal slide rail arranged above the test frame beam 63, the beam mechanism 62 is movably connected with the horizontal slide rail, and can drive the load simulation cylinder 2 to move Movement in the horizontal direction.

At this time, the two ends of the screw assembly are respectively connected to the top of the test frame 1 and the test frame beam 63, and pass through the horizontal slide rail. Therefore, the screw assembly can drive the horizontal slide rail to drive the beam mechanism 62 in the vertical direction during the rotation process. It moves in the vertical direction, thereby driving the load simulation cylinder 2 to move in the vertical direction, thereby realizing the adjustment of the installation position of the landing gear assembly 3 to install the landing gear assembly 3 of different specifications.

Example 3

This embodiment discloses an aircraft landing gear wheel brake response test device. On the basis of Embodiment 1, this embodiment also discloses a response measurement system. The response measurement system is connected to the landing gear assembly 3 to measure the landing gear assembly. 3. Dynamic response data during the rollout braking process. Through the analysis of the dynamic response data of the landing gear assembly 3, find out the design parameters of the wheel brake assembly 311 and the occurrence of "chattering", "walking" and "whistling" of the landing gear assembly 3. It provides a research basis for the performance improvement, improvement and optimization design of the landing gear assembly 3 and the wheel brake assembly 311.

Example 4

This embodiment discloses a method for testing the braking response of an aircraft landing gear wheel, as shown in FIG. 4 , including the following steps:

S10. Complete the assembly of the test device described in any one of Embodiments 1-3 and the setting of initial test data.

Specifically include:

Adjust the load simulation cylinder 2 to the position matching the landing gear assembly 3 to be tested by the position adjusting assembly 6, and then install the landing gear assembly 3 and the response measurement system.

Install the corresponding wheel 31 and wheel brake assembly 311 on the landing gear assembly 3 , and then install the corresponding part of the wheel hub assembly 4 .

According to the simulated body energy required for the test, calculate the mass of the auxiliary hub wheel 42 and the inertia wheel 44 to be assembled and the required electric inertia, so as to realize the infinite simulation of the body energy, and install the corresponding auxiliary hub wheel 42 and inertia wheel at the same time. 44. Set the electric inertia of the drive assembly 5 to complete the assembly of the test device and the setting of the initial test data.

S20. According to the pressing load required for the test, the wheel 31 is pressed on the surface of the hub wheel 41 by the load simulation oil cylinder 2.

S30. Calculate the target rotational speed of the drive assembly 5 according to the simulated body speed to ensure that the surface linear speed of the hub wheel 41 is equal to the body speed, and then start the drive assembly 5.

S40. The hub wheel 41 rotates with the wheel 31 in the opposite direction. After the rotation speed of the standby wheel 31 is stable, set and apply the corresponding electric inertia according to the test requirements, and the drive component 5 inputs additional energy or reverse braking energy according to the set electric inertia. , and simultaneously activate the wheel brake assembly 311 until the wheel 31 is completely braked.

S50. During the braking process, the response measurement system synchronously collects the dynamic response data of the landing gear assembly 3.

S60. According to the dynamic response data of the landing gear assembly 3, carry out the dynamic response analysis of the landing gear assembly 3, and evaluate the dynamic performance of the landing gear assembly 3, so as to analyze and find out the design parameters of the wheel brake assembly 311 and the occurrence of the landing gear assembly 3. The root causes of problems such as "chattering", "walking" and "howling" provide a research basis for the performance improvement, improvement and optimization of the landing gear assembly 3 and the wheel brake assembly 311.

In this embodiment, the installation position of the load simulation cylinder 2 is matched with the landing gear assembly 3 to be tested. For the specific adjustment of the installation position of the load simulation cylinder 2, please refer to Embodiment 1, and this embodiment will not be described too much; the auxiliary hub The wheel 42 and the inertia wheel 44 are replaced according to the energy size of the simulated body required for the test. The driving component 5 adopts a driving motor, and its electric inertia is set according to the test requirements.

Obviously, the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those of ordinary skill in the art, changes or modifications in other different forms can also be made on the basis of the above description. There is no need and cannot be exhaustive of all implementations here. Any modifications, equivalent replacements and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the claims of the present invention.

Claims (10)

1. an aircraft landing gear wheel brake response test device, is characterized in that, comprises test frame (1), load simulation oil cylinder (2), landing gear assembly (3), hub wheel assembly (4) and drive assembly (5) ), the load simulation oil cylinder (2) is installed on the upper end of the test stand (1) through a position adjustment assembly (6), and the load simulation oil cylinder (2) passes along the position adjustment assembly (6) along the The test frame (1) moves in the vertical direction, the landing gear assembly (3) is fixedly installed on the lower end of the load simulation oil cylinder (2), and an organic wheel ( 31) and a wheel brake assembly (311) matched with the wheel (31), the hub wheel assembly (4) is mounted on the lower end of the test stand (1), the drive assembly (5) is connected with the hub wheel assembly (4) to drive the hub wheel assembly (4) to rotate, the hub wheel assembly (4) comprises a hub wheel (41) in contact with the wheel (31), and is arranged on the Auxiliary hub wheels (42) and hub wheel support assemblies (43) on both sides of the hub wheel (41), the hub wheels (41) and the auxiliary hub wheels (42) are mounted on the hub wheel support assembly (43) Above, the drive assembly (5) is connected with the hub wheel support assembly (43) to drive the hub wheel (41) and the auxiliary hub wheel (42) to rotate. 2. An aircraft landing gear wheel braking response test device according to claim 1, wherein the position adjustment assembly (6) comprises a lift adjustment mechanism (61) and a beam mechanism (62), the lift The adjustment mechanism (61) is respectively connected with the test frame (1) and the beam mechanism (62), the upper end of the load simulation oil cylinder (2) is connected with the beam mechanism (62), and the beam mechanism (62) passes through the beam mechanism (62). The lift adjustment mechanism (61) drives the load simulation oil cylinder (2) to move in the vertical direction. 3. An aircraft landing gear wheel brake response test device according to claim 2, characterized in that, the lift adjustment mechanism (61) comprises a screw assembly, and the position adjustment assembly (6) further comprises a test stand Cross beam (63), the test frame cross beam (63) is arranged below the cross beam mechanism (62), and the screw assembly is sequentially connected to the top of the test frame (1), the cross beam mechanism (62) and the test frame cross beam (63). 4. An aircraft landing gear wheel brake response test device according to claim 1, characterized in that, further comprising a gondola assembly (7), the two side walls of the gondola assembly (7) passing through the roller assembly ( 8) slidingly connected with the slide rail mechanisms provided on the two side walls of the test stand (1); the load simulation oil cylinder (2) is installed in the gondola assembly (7), the landing gear assembly (3) ) is fixedly connected with the bottom end of the hanging basket assembly (7). 5. An aircraft landing gear wheel braking response test device according to claim 1, wherein the hub wheel support assembly (43) comprises a hub wheel support shaft (431) and a hub wheel support frame (432) , the hub wheel (41) and the auxiliary hub wheel (42) are fixedly mounted on the hub wheel support shaft (431), and the hub wheel support shaft (431) is erected on the hub wheel support frame (432) and can rotate along the hub wheel support frame (432), and the drive assembly (5) is connected with the hub wheel support shaft (431) to drive the hub wheel support shaft (431) to drive the hub wheel (41) and the auxiliary hub wheel (42) rotates along the hub wheel support frame (432). 6. An aircraft landing gear wheel braking response test device according to claim 1, wherein the hub wheel assembly (4) further comprises an inertia wheel (44), and the inertia wheel (44) is detachable is installed on the hub wheel support assembly (43). 7. An aircraft landing gear wheel braking response test device according to claim 1, wherein the hub wheel assembly (4) further comprises an emergency braking assembly (45) and a torque sensor (46), the The emergency braking assembly (45) comprises an emergency braking mechanism (451) arranged on the hub wheel supporting assembly (43) and a pressure supply and air storage mechanism (452) connected with the emergency braking mechanism (451); the torque A sensor (46) is mounted on the hub wheel support assembly (43). 8. An aircraft landing gear wheel brake response test device according to claim 1, further comprising a response measurement system, the response measurement system is connected with the landing gear assembly (3) to measure the Dynamic response data of the landing gear assembly (3) during the rollout braking process. 9. A test method for the braking response of an aircraft landing gear wheel, characterized in that, comprising the following steps: S10. Complete the assembly of the test device described in any one of claims 1-8 and the setting of initial test data; S20. According to the pressing load required for the test, press the wheel (31) on the road surface of the hub wheel (41) through the load simulation oil cylinder (2); S30. Calculate the target rotational speed of the drive assembly (5) according to the simulated body speed to ensure that the surface linear speed of the hub wheel (41) is equal to the body speed, and then start the drive assembly (5); S40. The hub wheel (41) rotates with the machine wheel (31) in the opposite direction. After the rotation speed of the standby wheel (31) is stabilized, the corresponding electric inertia is set and applied according to the test requirements, and the drive component (5) is input according to the set electric inertia. Additional energy or reverse braking energy, while starting the wheel brake assembly (311) until the wheel (31) is completely braked; S50. During the braking process, the response measurement system synchronously collects the dynamic response data of the landing gear assembly (3); S60. According to the dynamic response data of the landing gear assembly (3), perform a dynamic response analysis of the landing gear assembly (3), and evaluate the dynamic performance of the landing gear assembly (3). 10. The method for testing the braking response of an aircraft landing gear wheel according to claim 9, wherein step S10 specifically comprises: Adjust the load simulating oil cylinder (2) to a position matching the landing gear assembly (3) to be tested through the position adjusting assembly (6); install the landing gear assembly (3) and the response measurement system; Install the corresponding wheel (31) and wheel brake assembly (311) on the landing gear assembly (3); Calculate the mass of the auxiliary hub wheel (42) and the inertia wheel (44) to be assembled and the required electric inertia according to the energy size of the simulated body required for the test, so as to realize the infinite simulation of the body energy; Install the corresponding auxiliary hub wheel (42) and inertia wheel (44), and set the electric inertia of the drive assembly (5).

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