CN114754999A - Airplane wheel brake response test device and test method for airplane landing gear - Google Patents
Airplane wheel brake response test device and test method for airplane landing gear Download PDFInfo
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- CN114754999A CN114754999A CN202210529308.XA CN202210529308A CN114754999A CN 114754999 A CN114754999 A CN 114754999A CN 202210529308 A CN202210529308 A CN 202210529308A CN 114754999 A CN114754999 A CN 114754999A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention relates to a test device and a test method for the brake response of wheels of an aircraft landing gear, wherein the installation position of a load simulation oil cylinder is adjusted through an arranged position adjusting assembly, so that the installation position of a landing gear assembly is adjusted, and the test device can perform simulation tests on landing gear assemblies with different types and sizes; meanwhile, the position adjusting assembly realizes adjustment in the vertical direction by adopting a screw rod assembly and a roller assembly to be matched with a slide rail mechanism, so that the stability of action in the vertical direction is improved; aiming at the hub wheel driving assembly, an emergency brake assembly capable of being remotely controlled is arranged so as to deal with sudden accidents in the test process; meanwhile, a response measuring system is arranged on the landing gear component and used for measuring the dynamic response of the landing gear in the sliding brake process; in addition, the hub wheel assembly is provided with the replaceable auxiliary hub wheel and the inertia wheel, so that the auxiliary hub wheel and the inertia wheel with different masses are configured while the speed of the machine body is accurately simulated, and the energy regulation simulation of the machine body is realized.
Description
Technical Field
The invention relates to the technical field of design and manufacture of an aircraft landing gear, in particular to a test device and a test method for the brake response of wheels of the aircraft landing gear.
Background
The dynamic response of an aircraft landing gear in the sliding braking process is one of important subjects of the dynamics research of the aircraft landing gear, and the dynamics characteristics and the failure occurrence mechanism of the landing gear structure and a braking system in the sliding braking process are mainly researched. When the design parameters of the braking system are not matched, the landing gear can generate the fault phenomena of walking, buffeting, squeaking and the like in the braking process, and when the fault phenomena are serious, the more serious accidents of tire burst, buffeting and even breakage of the landing gear can be caused. Therefore, in the design and manufacturing process of the airplane in China, a dynamic response simulation test of the landing gear in the sliding braking process needs to be carried out.
However, in the prior art, only after the problem of the undercarriage system is found when the newly developed airplane runs off, the undercarriage system is passively detected, and the design is modified when the problem is found when the newly developed airplane runs off, so that the difficulty of solving the problem is increased, the research cost is increased, and the development period of the airplane is influenced.
The existing simulation test of the aircraft landing gear brake system realizes the simulation of the energy of the aircraft body by adjusting the rotation speed of the inertia wheel, and tests the brake distance, time, moment and the like to detect the performance of the brake system. The mechanical characteristics of the corresponding undercarriage are not tested, because the prior testing technology only concerns the simulation of the energy of the undercarriage, the speed of the corresponding undercarriage is not simulated, and the dynamic characteristics of the undercarriage under the configuration of a specific type brake system cannot be simulated, so that the dynamic characteristics of the undercarriage cannot be fully tested, and the basis cannot be provided for the optimal design of the undercarriage and a brake system combination mechanism.
Disclosure of Invention
The invention provides a test device and a test method for the brake response of an aircraft landing gear, aiming at solving the problem that the mechanical properties of the landing gear cannot be effectively simulated and tested only by testing the performance of a brake system in the simulation test of the landing gear and the brake system of the aircraft in the prior art.
A testing device for the braking response of an airplane wheel of an airplane landing gear comprises a testing frame, a load simulation oil cylinder, a landing gear component, a hub wheel component and a driving component, the load simulation oil cylinder is arranged at the upper end part of the test frame through a position adjusting component, the load simulation oil cylinder moves in the vertical direction along the test frame through the position adjusting component, the landing gear component is fixedly arranged at the lower end part of the load simulation oil cylinder, the hub wheel component is arranged at the lower end part of the test frame, the driving assembly is connected with the wheel hub assembly to drive the wheel hub assembly to rotate, the wheel hub assembly comprises a wheel hub which is in contact with the wheel of the landing gear assembly, auxiliary wheel hubs which are arranged on two sides of the wheel hub and a wheel hub supporting assembly, the hub wheel and the auxiliary hub wheel are mounted on the hub wheel support assembly, and the driving assembly is connected with the hub wheel support assembly to drive the hub wheel and the auxiliary hub wheel to rotate.
Further, as a preferred technical scheme, the position adjusting assembly comprises a lifting adjusting mechanism and a beam mechanism, the lifting adjusting mechanism is respectively connected with the testing frame and the beam mechanism, the upper end of the load simulation oil cylinder is connected with the beam mechanism, and the beam mechanism drives the load simulation oil cylinder to move in the vertical direction through the lifting adjusting mechanism.
Further, as preferred technical scheme, lift adjustment mechanism includes the lead screw subassembly, position control subassembly still includes the test jig crossbeam, the test jig crossbeam sets up crossbeam mechanism below, the lead screw subassembly connects gradually the top, the crossbeam mechanism and the test jig crossbeam of test jig.
Further, as a preferred technical scheme, the test jig further comprises a hanging basket assembly, wherein two side walls of the hanging basket assembly are in sliding connection with sliding rails arranged on two side walls of the test frame through roller assemblies; the load simulation oil cylinder is installed in the hanging basket component, and the landing gear component is fixedly connected with the bottom end of the hanging basket component.
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 mounted on the hub wheel support shaft, the hub wheel support shaft is erected on the hub wheel support frame and can rotate along the hub wheel support frame, and the driving assembly is connected with the hub wheel support shaft to drive the hub wheel and the auxiliary hub wheel to rotate along the hub wheel support frame.
Further, as a preferred technical solution, the wheel hub assembly further includes an inertia wheel, and the inertia wheel is detachably mounted on the wheel hub support assembly.
Further, as a preferred technical scheme, the hub wheel assembly further comprises an emergency brake assembly and a torque sensor, wherein the emergency brake assembly comprises an emergency brake mechanism arranged on the hub wheel support assembly and a pressure supply and air storage mechanism connected with the emergency brake mechanism; the torque sensor is mounted on the wheel hub support assembly.
Further, as a preferred technical scheme, the system also comprises a response measurement system, wherein the response measurement system is connected with the landing gear assembly so as to measure dynamic response data of the landing gear assembly in the process of the skid braking.
A method for testing the brake response of an airplane wheel of an airplane landing gear comprises the following steps:
s10, completing the assembly of the test device of any one of claims 1-8 and setting of initial test data;
s20, according to the compaction load required by the test, the airplane wheel is compacted on the hub wheel road surface through a load simulation oil cylinder;
s30, calculating a target rotating speed of the driving assembly according to the speed of the simulated machine body to ensure that the linear speed of the hub wheel road surface is equal to the speed of the machine body, and then starting the driving assembly;
s40, the hub wheel drives the wheel to rotate along the opposite direction, after the rotation speed of the standby wheel is stable, corresponding electric inertia is applied according to test requirement setting, the driving assembly inputs additional energy or reverse braking energy according to the set electric inertia, and meanwhile, the wheel brake assembly is started until the wheel is completely braked;
s50, in the braking process, a response measurement system synchronously acquires dynamic response data of the undercarriage component;
s60, according to the dynamic response data of the landing gear assembly, carrying out dynamic response analysis on the landing gear assembly, and evaluating the dynamic performance of the landing gear assembly.
Further, as a preferred technical solution, step S10 specifically includes:
adjusting the load simulation oil cylinder to a position matched with the undercarriage component to be tested through the position adjusting component;
installing a landing gear assembly and a response measurement system;
mounting corresponding wheels and wheel brake assemblies on the landing gear assembly;
calculating the mass of the auxiliary hub wheel and the inertia wheel to be assembled and the required electric inertia according to the simulated engine body energy required by the test so as to realize stepless simulation of the engine body energy;
and installing the corresponding auxiliary hub wheel and the inertia wheel and setting the electric inertia of the driving assembly.
Compared with the prior art, the technical scheme of the invention has the beneficial effects that:
the mounting position of the load simulation oil cylinder is adjusted through the arranged position adjusting assembly, and then the mounting position of the landing gear assembly is adjusted, so that the test device can perform simulation tests on landing gear assemblies of different types and sizes; meanwhile, the position adjusting assembly is realized by adopting a screw rod assembly, and a roller assembly is arranged in the vertical direction to be matched with a sliding rail mechanism, so that the stability of action in the vertical direction is improved; meanwhile, aiming at the hub wheel driving assembly, an emergency brake assembly capable of being remotely controlled is arranged so as to deal with sudden accidents in the test process; meanwhile, a response measuring system is arranged on the landing gear component and used for measuring the dynamic response of the landing gear in the sliding brake process; in addition, the hub wheel assembly is provided with the replaceable auxiliary hub wheel and the inertia wheel, so that the auxiliary hub wheel and the inertia wheel with different masses are configured while the speed of the airplane body is accurately simulated, the energy regulation simulation of the airplane body is realized, the authenticity of the dynamic response test simulation of the airplane landing gear in the sliding braking process is improved, and a basis is better provided for the optimization design of the performance adaptability of the landing gear structure and the braking system.
Drawings
FIG. 1 is a schematic view of the structure of the present invention.
Fig. 2 is an enlarged schematic view of the position adjustment assembly of the present invention.
FIG. 3 is a block diagram of the present invention.
FIG. 4 is a flow chart of the present invention.
Detailed Description
The present invention will be further described with reference to the following embodiments.
The same or similar reference numerals 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 is an orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of description and simplicity of description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore the terms describing positional relationship in the drawings are for illustrative purposes only and should not be construed as limiting the patent.
Furthermore, if the terms "first," "second," and the like are used for descriptive purposes only, they are used primarily for distinguishing between different devices, elements, or components that may or may not be the same in particular nature and configuration, and not for indicating or implying relative importance between the indicated devices, elements, or components, but rather for indicating or implying relative importance.
Example 1
In order to overcome the problem that the mechanical characteristics of the landing gear cannot be effectively simulated and tested by only testing the performance of the brake system in the simulation test of the landing gear and the brake system of the airplane in the prior art, the embodiment provides a test technology for truly simulating the movement energy and speed of an airplane body, the sliding brake process of the landing gear, the brake dynamic response of the landing gear and the influence of the brake of the airplane wheel on the structural characteristics of the landing gear in the early stage of the design of the landing gear system; the test technology provides an analysis method for researching the vibration characteristics of the landing gear structure caused by braking and researching the influence of various harmful vibrations on the fatigue life of the landing gear; the method also provides a basis for researching the fault phenomena of landing gear walking, buffeting and screaming caused by the braking of the airplane wheel, exploring the generation mechanism, analyzing the generation reason, thoroughly solving the optimization design of the adaptability of the landing gear structure and the braking system performance, so as to find the problems in advance, avoid the technical risk, shorten the development period and save the development expenditure.
The aircraft landing gear wheel brake response test device disclosed in the embodiment comprises a test frame 1, a load simulation oil cylinder 2, a hanging basket assembly 7, a landing gear assembly 3, a hub wheel assembly 4 and a driving assembly 5, wherein the load simulation oil cylinder 2 is mounted at the upper end part of the test frame 1 through a position adjusting assembly 6, the load simulation oil cylinder 2 is mounted in the hanging basket assembly 7, the load simulation oil cylinder 2 moves in the horizontal and vertical directions along the test frame 1 through the position adjusting assembly 6, and two side walls of the hanging basket assembly 7 are in sliding connection with sliding rail mechanisms arranged on two side walls of the test frame 1 through roller assemblies 8 so as to improve the stability of vertical direction movement; the landing gear assembly 3 is fixedly connected with the bottom end of the hanging basket assembly 7 through a landing gear mounting clamp 32, a wheel 31 and a wheel brake assembly 311 matched with the wheel 31 are mounted at the lower end of the landing gear assembly 3, the wheel hub assembly 4 is mounted at the lower end of the test frame 1, and the driving assembly 5 is connected with the wheel hub assembly 4 to drive the wheel hub assembly 4 to rotate.
In the present embodiment, the wheel hub assembly 4 includes a wheel hub 41 contacting 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 a 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 driving assembly 5 is connected to the wheel hub support assembly 43 to drive the wheel hub 41 and the auxiliary wheel hub 42 to rotate.
In this embodiment, as shown in fig. 3: the auxiliary hub wheel 42 and the inertia wheel 44 are matched with the driving assembly 5 to realize the rotation speed control of the hub wheel 41, so that the mechanical inertia of the hub wheel 41, the auxiliary hub wheel 42 and the inertia wheel 44 and the control of the simulated inertia combination and speed of the driving assembly 5 are used for realizing the motion energy and speed simulation of an airplane body, the ground load of the airplane wheel 31 of the landing gear assembly 3 is simulated through the load simulation oil cylinder 2, the brake is carried out through the airplane wheel brake assembly 311 under the condition of simulating the real sliding process of the landing gear assembly 3, the dynamic response of the landing gear assembly 3 is measured in real time, and the design parameters of the airplane wheel brake assembly 311 and the root sources of the problems of buffeting, walking, howling and the like of the landing gear assembly 3 are found through the analysis of response data. And research basis is provided for the perfection, improvement and optimization design of the structure of the landing gear component 3 and the performance of the wheel brake component 311.
In the present embodiment, since the rotation speed of the hub wheel 41 needs to meet the wheel 31 running requirement of the landing gear assembly 3, and therefore the rotation speed of the hub wheel 41 needs to be consistent with the rotation speed of the wheel 31, the replaceable auxiliary hub wheel 42 and the replaceable inertia wheel 44 are provided, and the energy regulation simulation can be realized by configuring the auxiliary hub wheel 42 or the inertia wheel 44 with different masses while achieving the rotation speed consistency of the hub wheel 41 and the wheel 31.
In addition, the emergency brake assembly 45 can be used for dealing with sudden accidents in the test process, for example, when the wheel 31 is braked and slipped off on the wheel hub 41 through the wheel brake assembly 311, accidents such as tire burst and the like are easy to occur, and the equipment is damaged. The replaceable auxiliary hub wheel and the replaceable inertia wheel are arranged, so that the auxiliary hub wheel and the inertia wheel with different masses are configured while the speed of the machine body is constant, the energy regulation simulation of the machine body is realized, the integrity of test data is ensured, and a basis is better provided for the optimization design of the performance adaptability of the undercarriage structure and the brake system.
In the present embodiment, the hub wheel support assembly 43 includes a hub wheel support shaft 431 and a hub wheel support frame 432, the hub wheel 41, the auxiliary hub wheel 42, the inertia wheel 44, the emergency brake assembly 45 and the torque sensor 46 are all fixedly mounted on the hub wheel support shaft 431, the hub wheel support shaft 431 is mounted on the hub wheel support frame 432 and can rotate along the hub wheel support frame 432, and the driving assembly 5 is connected with the hub wheel support shaft 431 and drives the hub wheel support shaft 431 to drive the hub wheel 41 and the auxiliary hub wheel 42 to rotate along the hub wheel support frame 432.
As a preferred embodiment, the emergency brake assembly 45 includes an emergency brake mechanism 451 provided on the hub wheel support shaft 431 of the hub wheel support assembly 43 and a pressure supply and storage mechanism 452 connected to the emergency brake mechanism 451; the drive assembly 5 comprises a drive motor.
In addition, in the present embodiment, the bottom end of the test frame 1 is fixedly installed on the ground, the foundation pit 10 is provided on the ground downward, the hub wheels 41 and the auxiliary hub wheels 42 are located in the foundation pit 10, and the hub wheel support assemblies 43 are erected on the ground on both sides of the foundation pit 10.
In this embodiment, the position adjusting assembly 6 includes a lifting adjusting mechanism 61 and a beam mechanism 62, the lifting adjusting mechanism 61 is respectively connected to the testing jig 1 and the beam mechanism 62, the upper end of the load simulation cylinder 2 is connected to the beam mechanism 62, and the beam mechanism 62 drives the load simulation cylinder 2 to move in the vertical direction along the testing jig 1 through the lifting adjusting mechanism 61.
As a preferred embodiment, the lifting adjusting mechanism 61 comprises a screw rod assembly, the position adjusting assembly 6 further comprises a testing jig cross beam 63, the testing jig cross beam 63 is arranged below the cross beam mechanism 62, and the screw rod assembly is sequentially connected with the top of the testing jig 1, the cross beam mechanism 62 and the testing jig cross beam 63.
That is, the top and the test jig crossbeam 63 of test jig 1 are connected respectively to the both ends of lead screw subassembly, and pass crossbeam mechanism 62, so, the lead screw subassembly can drive crossbeam mechanism 62 and move in vertical direction at rotatory in-process, and then realizes adjusting undercarriage subassembly 3's mounted position to the undercarriage subassembly 3 of different specifications of installation.
Therefore, in the embodiment, the installation position of the load simulation oil cylinder 2 is adjusted through the arranged position adjusting assembly 6, and then the installation position of the landing gear assembly 3 is adjusted, so that the test device of the embodiment can perform simulation tests on landing gear assemblies 3 of different types; meanwhile, the lifting adjusting mechanism 61 of the position adjusting assembly 6 is realized by a screw rod assembly, the adjusting stroke can be shortened, and in the process, the roller assemblies 8 are matched with the sliding rail mechanism to realize adjustment in the vertical direction, so that the stability of action in the vertical direction is improved.
Example 2
The embodiment discloses an aircraft landing gear wheel brake response test device, and discloses another implementation mode of a position adjusting assembly 6 on the basis of embodiment 1.
In this embodiment, the position adjusting assembly 6 further includes a horizontal adjusting mechanism, the horizontal adjusting mechanism includes a horizontal slide rail disposed above the testing frame beam 63, and the beam mechanism 62 is movably connected to the horizontal slide rail and can drive the load simulation cylinder 2 to move in the horizontal direction.
At this moment, the top of the test jig 1 and the test jig crossbeam 63 are connected respectively at the both ends of the screw rod assembly, and pass horizontal slide rail, so, the screw rod assembly can drive horizontal slide rail in the rotation process and drive the crossbeam mechanism 62 to move in the vertical direction, and then drive the load simulation oil cylinder 2 to move in the vertical direction, and then realize adjusting the mounted position of undercarriage subassembly 3 to install the undercarriage subassembly 3 of different specifications.
Example 3
The embodiment discloses an aircraft landing gear wheel brake response test device, and the embodiment also discloses a response measurement system on the basis of the embodiment 1, wherein the response measurement system is connected with a landing gear component 3 to measure dynamic response data of the landing gear component 3 in a sliding brake process, and the root causes of the problems of 'buffeting', 'walking', 'howling' and the like of the wheel brake component 311 and the landing gear component 3 are found out through analysis of the dynamic response data of the landing gear component 3, so that research bases are provided for the perfection, improvement and optimization design of the performance of the landing gear component 3 and the wheel brake component 311.
Example 4
The embodiment discloses a method for testing the brake response of an airplane wheel of an airplane landing gear, which comprises the following steps as shown in fig. 4:
s10, completing the assembly of the test device and the setting of initial test data in any one of the embodiments 1-3.
The method specifically comprises the following steps:
the load simulation rams 2 are adjusted by the position adjustment assembly 6 to a position matching the landing gear assembly 3 to be tested and then the landing gear assembly 3 and the response measurement system are installed.
The corresponding wheel 31 and wheel brake assembly 311 are mounted on the landing gear assembly 3 and then the corresponding part of the wheel hub assembly 4.
According to the simulated body energy required by the test, the mass of the auxiliary hub wheel 42 and the inertia wheel 44 required to be assembled and the required electric inertia are calculated so as to realize stepless simulation of the body energy, meanwhile, the corresponding auxiliary hub wheel 42 and the corresponding inertia wheel 44 are installed, and the electric inertia of the driving assembly 5 is set so as to complete the assembly of the test device and the setting of initial test data.
S20, according to the compaction load required by the test, the wheel 31 is compacted on the road surface of the hub wheel 41 through the load simulation oil cylinder 2.
And S30, calculating the target rotating speed of the driving assembly 5 according to the simulated body speed to ensure that the linear speed of the road surface of the hub wheel 41 is equal to the body speed, and then starting the driving assembly 5.
S40, the hub wheel 41 drives the wheel 31 to rotate in the opposite direction, after the rotation speed of the standby wheel 31 is stable, corresponding electric inertia is applied according to test requirement setting, the driving assembly 5 inputs additional energy or reverse braking energy according to the set electric inertia, and meanwhile, the wheel braking assembly 311 is started until the wheel 31 is completely braked.
S50, in the braking process, the response measurement system synchronously acquires dynamic response data of the undercarriage component 3.
And S60, according to the dynamic response data of the undercarriage component 3, carrying out dynamic response analysis on the undercarriage component 3, and evaluating the dynamic performance of the undercarriage component 3, so that the design parameters of the wheel brake component 311 and the root causes of the problems of buffeting, walking, screaming and the like of the undercarriage component 3 are analyzed and found out, and a research basis is provided for the perfect performance, improvement and optimized design of the undercarriage component 3 and the wheel brake component 311.
In the embodiment, the installation position of the load simulation oil cylinder 2 is matched with the landing gear assembly 3 to be tested, and the specific adjustment of the installation position of the load simulation oil cylinder 2 is referred to embodiment 1, which is not explained in more detail; the auxiliary hub wheel 42 and the inertia wheel 44 are replaced according to the simulated body energy required by the test, and the driving assembly 5 adopts a driving motor, and the electric inertia of the driving motor is set according to the test requirement.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. The aircraft landing gear wheel brake response test device is characterized by comprising a test frame (1), a load simulation oil cylinder (2), a landing gear assembly (3), a hub wheel assembly (4) and a driving assembly (5), wherein the load simulation oil cylinder (2) is installed at the upper end part of the test frame (1) through a position adjusting assembly (6), the load simulation oil cylinder (2) is installed at the lower end part of the load simulation oil cylinder (2) through the position adjusting assembly (6) along the test frame (1) in the vertical direction, the landing gear assembly (3) is fixedly installed at the lower end part of the load simulation oil cylinder (2), a wheel (31) and a wheel brake assembly (311) matched with the wheel (31) are installed at the lower end part of the test frame (1), the hub wheel assembly (4) is installed at the lower end part of the test frame (1), and the driving assembly (5) is connected with the hub wheel assembly (4) to drive the hub wheel assembly (4) to rotate, the wheel hub assembly (4) comprises a wheel hub (41) in contact with the wheel (31), an auxiliary wheel hub (42) and a wheel hub support assembly (43), the auxiliary wheel hub (42) and the wheel hub (41) are arranged on two sides of the wheel hub (41), the wheel hub (41) and the auxiliary wheel hub (42) are mounted on the wheel hub support assembly (43), and the driving assembly (5) is connected with the wheel hub support assembly (43) to drive the wheel hub (41) and the auxiliary wheel hub (42) to rotate.
2. An aircraft landing gear wheel brake response test device according to claim 1, wherein the position adjusting assembly (6) comprises a lifting adjusting mechanism (61) and a beam mechanism (62), the lifting adjusting 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) drives the load simulation oil cylinder (2) to move in the vertical direction through the lifting adjusting mechanism (61).
3. An aircraft landing gear wheel brake response test device according to claim 2, wherein the lifting adjusting mechanism (61) comprises a screw rod assembly, the position adjusting assembly (6) further comprises a test frame cross beam (63), the test frame cross beam (63) is arranged below the cross beam mechanism (62), and the screw rod assembly sequentially connects the top of the test frame (1), the cross beam mechanism (62) and the test frame cross beam (63).
4. The aircraft landing gear wheel brake response test device of claim 1, further comprising a hanging basket assembly (7), wherein two side walls of the hanging basket assembly (7) are slidably connected with sliding rail mechanisms arranged on two side walls of the test frame (1) through roller assemblies (8); the load simulation oil cylinder (2) is installed in the hanging basket component (7), and the landing gear component (3) is fixedly connected with the bottom end of the hanging basket component (7).
5. An aircraft landing gear wheel brake 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), 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 driving assembly (5) is connected with the hub wheel support shaft (431) and drives the hub wheel support shaft (431) to drive the hub wheel (41) and the auxiliary hub wheel (42) to rotate along the hub wheel support frame (432).
6. An aircraft landing gear wheel brake response test device according to claim 1, wherein the wheel hub assembly (4) further comprises an inertia wheel (44), and the inertia wheel (44) is detachably mounted on the wheel hub support assembly (43).
7. An aircraft landing gear wheel brake response test device according to claim 1, wherein the wheel hub assembly (4) further comprises an emergency brake assembly (45) and a torque sensor (46), the emergency brake assembly (45) comprises an emergency brake mechanism (451) arranged on the wheel hub supporting assembly (43) and a pressure supply and air storage mechanism (452) connected with the emergency brake mechanism (451); the torque sensor (46) is mounted on the wheel hub support assembly (43).
8. An aircraft landing gear wheel brake response test device according to claim 1, further comprising a response measurement system connected to the landing gear assembly (3) to measure dynamic response data of the landing gear assembly (3) during rollout braking.
9. A method for testing the braking response of an airplane wheel of an airplane landing gear is characterized by comprising the following steps:
s10, completing the assembly of the test device of any one of claims 1-8 and setting of initial test data;
s20, according to the compaction load required by the test, the wheel (31) is compacted on the road surface of the hub wheel (41) through the load simulation oil cylinder (2);
s30, calculating a target rotating speed of the driving assembly (5) according to the speed of the simulated machine body to ensure that the linear speed of the road surface of the hub wheel (41) is equal to the speed of the machine body, and then starting the driving assembly (5);
s40, the hub wheel (41) drives the wheel (31) to rotate in the opposite direction, after the rotation speed of the standby wheel (31) is stable, corresponding electric inertia is applied according to test requirement setting, the driving assembly (5) inputs additional energy or reverse braking energy according to the set electric inertia, and meanwhile, the wheel brake assembly (311) is started until the wheel (31) is completely braked;
s50, in the braking process, a response measurement system synchronously collects dynamic response data of the landing gear component (3);
s60, according to the dynamic response data of the landing gear assembly (3), carrying out dynamic response analysis on the landing gear assembly (3), and evaluating the dynamic performance of the landing gear assembly (3).
10. The aircraft landing gear wheel brake response test method of claim 9, wherein the step S10 specifically includes:
the load simulation oil cylinder (2) is adjusted to a position matched with the undercarriage component (3) to be tested through the position adjusting component (6);
mounting the landing gear assembly (3) and a response measurement system;
mounting a corresponding wheel (31) and wheel brake assembly (311) on the landing gear assembly (3);
according to the simulated engine body energy required by the test, calculating the mass of an auxiliary hub wheel (42) and an inertia wheel (44) required to be assembled and the required electric inertia so as to realize stepless simulation of the engine body energy;
corresponding auxiliary hub wheels (42) and inertia wheels (44) are mounted, setting the electrical inertia of the drive assembly (5).
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| CN202210529308.XA CN114754999A (en) | 2022-05-16 | 2022-05-16 | Airplane wheel brake response test device and test method for airplane landing gear |
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| CN116986013A (en) * | 2023-09-27 | 2023-11-03 | 中国飞机强度研究所 | Method and equipment for airplane landing gear sliding cable-passing impact test |
| CN116986014A (en) * | 2023-09-27 | 2023-11-03 | 中国飞机强度研究所 | Device and method for adjusting and maintaining aircraft posture in full-aircraft drop test |
| CN117109965A (en) * | 2023-10-23 | 2023-11-24 | 中国飞机强度研究所 | Combined test device and test method for landing gear vibration and braking process of aircraft |
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2022
- 2022-05-16 CN CN202210529308.XA patent/CN114754999A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986012A (en) * | 2023-09-25 | 2023-11-03 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
| CN116986012B (en) * | 2023-09-25 | 2023-12-15 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
| CN116986013A (en) * | 2023-09-27 | 2023-11-03 | 中国飞机强度研究所 | Method and equipment for airplane landing gear sliding cable-passing impact test |
| CN116986014A (en) * | 2023-09-27 | 2023-11-03 | 中国飞机强度研究所 | Device and method for adjusting and maintaining aircraft posture in full-aircraft drop test |
| CN116986014B (en) * | 2023-09-27 | 2023-12-12 | 中国飞机强度研究所 | Device and method for adjusting and maintaining aircraft posture in full-aircraft drop test |
| CN116986013B (en) * | 2023-09-27 | 2023-12-15 | 中国飞机强度研究所 | Method and equipment for airplane landing gear sliding cable-passing impact test |
| CN117109965A (en) * | 2023-10-23 | 2023-11-24 | 中国飞机强度研究所 | Combined test device and test method for landing gear vibration and braking process of aircraft |
| CN117109965B (en) * | 2023-10-23 | 2024-01-26 | 中国飞机强度研究所 | Combined test device and test method for landing gear vibration and braking process of aircraft |
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