A test device for a landing gear steering mechanism

Abstract

The application belongs to the technical field of helicopter test, and discloses a test device of landing gear steering mechanism, which comprises a load device, a pressure bearing platform and a rotating platform, the pressure bearing platform is fixed to the ground, the landing gear is installed below the load device, the load device applies a preset landing gear load to the landing gear, and the rotating platform is below the steering wheel of the landing gear; wherein the upper surface of the rotating platform is a plane simulating a helicopter runway, the pressure bearing platform is a bearing structure of the rotating platform, and the rotating platform can rotate relative to the pressure bearing platform under the landing gear load. The steering test device is convenient to use, simple to operate, stable and reliable in performance, can realize the steering test of the front / tail landing gear of the helicopter, can meet the steering test of the front / tail landing gear of various types of helicopters, guarantees the node of the development task of the new type, shortens the test period, and improves the test efficiency.

Description

Technical Field

[0001] This invention belongs to the field of helicopter testing technology and relates to a steering test device, specifically a test device for a landing gear steering mechanism. Background Technology

[0002] The steering mechanism is a key component of helicopter landing gear, responsible for important functions such as taxiing, turning, and stopping. Currently, there are generally two types of helicopter steering mechanisms both domestically and internationally. One type uses a fixed point (the brake) for steering, with the remaining points moving to achieve the steering function. The other type incorporates steering functionality in the front and rear landing gear, automatically locking and centering during flight and unlocking before landing. For example, the Russian-developed Ka-27 helicopter and the Boeing CH-47 Chinook heavy transport helicopter both use the first type. Western developed countries, such as the US AH-64 Apache and UH-60 Black Hawk helicopters, and the European Tiger helicopter, typically employ a three-point landing gear configuration with steering capabilities in the front and rear landing gear.

[0003] The aforementioned types of helicopters place extremely high demands on the flexibility, reliability, and stability of their ground taxiing and steering. Insufficient steering of the nose / tail landing gear during ground taxiing can impair pilot control. The reliability and stability of landing gear steering directly affect helicopter landing safety. Therefore, conducting durability tests on helicopter landing gear steering to determine its reliability and stability is the only method and means. This also provides crucial scientific evidence for determining the first overhaul period of nose / tail landing gear with steering capabilities, significantly improving helicopter safety.

[0004] To conduct steering tests on the landing gear, it is necessary to simulate the actual working conditions of helicopter landing gear. However, there is currently a lack of corresponding equipment to achieve this. The helicopter landing gear needs to bear the weight of the helicopter, and under this pressure, it needs to complete relatively high-frequency steering tests. Conventional testing equipment cannot meet such requirements. Summary of the Invention

[0005] The purpose of this invention is to address the aforementioned problems by providing a test device for a landing gear steering mechanism. Addressing the challenge of accurately measuring the reliability and stability of newly developed helicopter landing gear steering, this invention utilizes experimental verification techniques to overcome key technologies such as operating condition simulation, test measurement and control, and system integration. A set of steering devices capable of simulating the working environment of the front and rear landing gear steering has been independently developed for durability testing, effectively shortening the test cycle and improving test efficiency.

[0006] The technical solution of this invention:

[0007] A test apparatus for a landing gear steering mechanism includes a load device, a pressure-bearing platform, and a rotating platform. The pressure-bearing platform is fixed to the ground, and the landing gear is installed below the load device. The load device applies a preset landing gear load to the landing gear, and the rotating platform is located below the landing gear steering wheels. The upper surface of the rotating platform is a plane simulating a helicopter runway, and the pressure-bearing platform is the load-bearing structure of the rotating platform. The rotating platform can rotate relative to the pressure-bearing platform under the landing gear load.

[0008] Furthermore, the rotating platform specifically includes an upper platform, a main shaft, a connecting seat, and a swing cylinder. The main body of the pressure-bearing platform is a frame structure. The main shaft is vertically located at the center of the pressure-bearing platform. The top of the main shaft is fixedly connected to the upper platform, and the lower part of the main shaft is located in the connecting seat and rotates through the drive of the swing cylinder.

[0009] Furthermore, the portion of the spindle located within the connecting seat is provided with an external spline, the swing cylinder is arranged laterally and is hydraulically driven, and the contact point between the swing cylinder and the external spline of the spindle is provided with a matching spline; the swing cylinder moves forward or backward under the push of hydraulic force, and the mutual cooperation of the splines causes the spindle to rotate in a preset direction.

[0010] Furthermore, there are two swing cylinders, which are symmetrically arranged on the left and right sides of the connecting seat.

[0011] Furthermore, the rotating platform also includes an upper flange bushing, the lower end of which is fixedly connected to the main shaft, and the upper side of the upper flange bushing is a flange portion, with the upper platform fixedly connected to the flange portion of the upper flange bushing.

[0012] Furthermore, a displacement sensor and a torque sensor are also installed on the spindle.

[0013] Furthermore, the pressure-bearing platform includes a lower support plate, a frame, and a mounting plate. The frame serves as the support for the entire device, and the lower support plate is located on top of the frame. The lower support plate is rotatably connected to the bottom of the upper platform of the rotating platform via a pressure-bearing bearing. The mounting plate is located on the frame and serves as a mounting platform for the connecting seat.

[0014] Furthermore, both the upper platform and the lower support plate are disc structures, and the sides of the upper platform and the lower support plate have corner marks and corner dials.

[0015] Furthermore, both the lower surface of the upper platform and the upper surface of the lower support plate are provided with a groove for placing the pressure bearing.

[0016] The beneficial effects of this invention are:

[0017] 1. The steering test device of the present invention is convenient to use, simple to operate, and has stable and reliable performance. It can realize the steering test of the front / tail landing gear of helicopters and can meet the steering test of the front / tail landing gear of various models of helicopters, thus ensuring the milestone of the development task of new models.

[0018] 2. To address the challenge of accurately measuring the reliability and stability of the newly developed helicopter landing gear steering, key technologies such as operating condition simulation, test measurement and control, and system integration were overcome by utilizing experimental verification techniques.

[0019] 3. This invention can perform durability tests on steering devices that simulate the steering working environment of the front and rear landing gears, shortening the test cycle and improving test efficiency.

[0020] 4. This invention uses a hydraulic drive to control the platform rotation. The design of the double swing cylinders allows the hydraulic pressure to be quickly converted into the rotational force of the main shaft, thereby driving the rotating platform to rotate at a predetermined frequency, which greatly improves the test efficiency and can effectively ensure the rotation of the platform without insufficient driving force. Attached Figure Description

[0021] Figure 1 This is a front sectional view of the pressure-bearing platform and the rotating platform of the present invention;

[0022] Figure 2 This is a top view of the rotating platform of the present invention;

[0023] Figure 3 This is a front view of the pressure-bearing platform and the rotating platform of the present invention;

[0024] Figure 4 This is a side view of the pressure-bearing platform and the rotating platform of the present invention;

[0025] Figure 5 This is a perspective view of the pressure-bearing platform and the rotating platform of the present invention;

[0026] Among them, 1—upper platform, 2—upper bearing, 3—steel ball, 4—lower bearing, 5—steel ball sleeve, 6—lower support plate, 7—frame, 8—swing cylinder, 9—mounting plate, 10—spindle, 11—connecting seat, 12—displacement sensor, 13—torque sensor, 14—upper flange bushing, 15—connecting bolt, 16—through hole, 17—threaded hole, 18—upper groove, 19—lower groove, 20—large through hole, 21—support surface, 22—support foot. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0028] A test apparatus for a landing gear steering mechanism includes a load device, a pressure-bearing platform, and a rotating platform. The pressure-bearing platform is fixed to the ground, and the landing gear is installed below the load device. The load device applies a preset landing gear load to the landing gear, and the rotating platform is located below the landing gear steering wheels. The upper surface of the rotating platform is a plane simulating a helicopter runway, and the pressure-bearing platform is the load-bearing structure of the rotating platform. The rotating platform can rotate relative to the pressure-bearing platform under the landing gear load.

[0029] The rotating platform specifically includes an upper platform 1, a main shaft 10, a connecting seat 11, and a swing cylinder 8. The main body of the pressure-bearing platform is a frame structure. The main shaft 10 is vertically located at the center of the pressure-bearing platform. The top of the main shaft 10 is fixedly connected to the upper platform 1. The lower part of the main shaft 10 is located in the connecting seat 11 and rotates through the drive of the swing cylinder 8.

[0030] The portion of the spindle 10 located within the connecting seat 11 is provided with an external spline. The swing cylinder 8 is arranged laterally and is hydraulically driven. The contact point between the swing cylinder 8 and the external spline of the spindle 10 is provided with a matching spline. The swing cylinder 8 moves forward or backward under the push of hydraulic force, and the interlocking splines cause the spindle 10 to rotate in a preset direction.

[0031] There are two swing cylinders 8, which are symmetrically arranged on the left and right sides of the connecting seat 11.

[0032] The rotating platform also includes an upper flange bushing 14, the lower end of which is fixedly connected to the main shaft 10. The upper side of the upper flange bushing 14 is a flange part, and the upper platform 1 is fixedly connected to the flange part of the upper flange bushing 14.

[0033] The spindle 10 is also equipped with a displacement sensor 12 and a torque sensor 13.

[0034] The pressure-bearing platform includes a lower support plate 6, a frame 7, and a mounting plate 9. The frame 7 serves as the support body for the entire device. The lower support plate 6 is located on the top of the frame 7. The lower support plate 6 is rotatably connected to the bottom of the upper platform 1 of the rotating platform through a pressure-bearing bearing. The mounting plate 9 is located on the frame 7 and serves as the mounting platform for the connecting seat 11.

[0035] Both the upper platform 1 and the lower support plate 6 are disc structures, and the sides of the upper platform 1 and the lower support plate 6 have corner marks and corner scales.

[0036] The lower surface of the upper platform 1 and the upper surface of the lower support plate 6 are both provided with a groove for placing the pressure bearing.

[0037] Another embodiment of the present invention will now be described with reference to the accompanying drawings.

[0038] A steering test device includes an upper platform 1, an upper bearing 2, a steel ball 3, a lower bearing 4, a steel ball sleeve 5, a lower support plate 6, a frame 7, a swing cylinder 8, a mounting plate 9, a main shaft 10, a connecting seat 11, a displacement sensor 12, a torque sensor 13, an upper flange bushing 14, and connecting bolts 15, etc., for realizing the steering function of the front / tail landing gear of a helicopter.

[0039] There is a Φ300 through hole on the upper platform 1.

[0040] The upper platform 1 has eight evenly distributed Φ18 through holes 16, with a large through hole 20 in the center. After the top of the upper flange bushing is aligned with the large through hole 20, the upper platform 1 is connected to the upper flange bushing 14 by connecting bolts 15. The upper platform 1 has four M16 threaded holes 17 for conducting steering tests, and the upper platform 1 has an upper groove 18 on the reverse side.

[0041] The upper bearing 2 is embedded in the upper groove 18 on the bottom surface of the upper platform 1.

[0042] The lower support plate 6 has a lower groove 19, and the lower bearing 4 is embedded in the lower groove 19 of the lower support plate 6.

[0043] The lower support plate 6 has a 360° scale.

[0044] The steel ball sleeve 5 is installed between the upper bearing 2 and the lower bearing 4, and 36 steel balls 3 are installed on the steel ball sleeve 5. The number of steel balls can be increased or decreased according to the size of the bearing and the pressure it bears, to ensure that it can withstand sufficient pressure.

[0045] The bottom surface of the lower support plate 6 is connected to the four support surfaces 21 on the frame 7 by welding.

[0046] The frame 7 is welded from square steel. The frame 7 has 4 support surfaces 21 on it and 4 support legs 22 on it.

[0047] The frame 7 has a mounting plate 9, and the connecting seat 11 is fixed on the mounting base plate 9. The swing cylinder 8 and the main shaft 10 are connected through the connecting seat 11. The main shaft 10 is equipped with a displacement sensor 12 and a torque sensor 13. The upper end of the main shaft 10 is connected to the upper flange bushing 14 through a keyway. The upper flange bushing 14 is fixed to the upper platform 1 by connecting bolts 15.

[0048] When the steering test device needs to work, the swing cylinder 8 is connected through the connecting seat 10. The swing cylinder 8 drives the main shaft 10 to rotate. The main shaft 10 drives the upper platform 1 to rotate through the upper flange bushing 14. The test piece is mounted on the upper platform 1, and the test piece can be used for steering test.

[0049] Meanwhile, the lower support plate 6 is marked with a 360° scale, which can clearly show the rotation angle. The main shaft 10 is equipped with a displacement sensor 12 and a torque sensor 13, which can be used to control and monitor the steering angle and torque of the steering test device.

[0050] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A test apparatus for a landing gear steering mechanism, characterized in that, It includes a load-bearing device, a pressure-bearing platform, and a rotating platform. The pressure-bearing platform is fixed to the ground, and the landing gear is installed below the load-bearing device. The load-bearing device applies a preset landing gear load to the landing gear, and the rotating platform is located below the landing gear's steering wheels. The upper surface of the rotating platform is a plane that simulates a helicopter runway, and the pressure-bearing platform is the load-bearing structure of the rotating platform. The rotating platform can rotate relative to the pressure-bearing platform when subjected to the landing gear load. The rotating platform specifically includes an upper platform (1), a main shaft (10), a connecting seat (11), and a swing cylinder (8). The main body of the pressure-bearing platform is a frame structure. The main shaft (10) is vertically located at the center of the pressure-bearing platform. The top of the main shaft (10) is fixedly connected to the upper platform (1). The lower part of the main shaft (10) is located in the connecting seat (11) and rotates through the drive of the swing cylinder (8). The portion of the main shaft (10) located inside the connecting seat (11) is provided with an external spline. The swing cylinder (8) is arranged laterally and is driven by hydraulic pressure. The contact point between the swing cylinder (8) and the external spline of the main shaft (10) is provided with a matching spline. The swing cylinder (8) moves forward or backward under the push of hydraulic force. Due to the mutual cooperation of the splines, the main shaft (10) rotates in a preset direction. There are two swing cylinders (8), which are symmetrically arranged on the left and right sides of the connecting seat (11). The pressure-bearing platform includes a lower support plate (6), a frame (7), and a mounting plate (9). The frame (7) serves as the support body of the entire device. The lower support plate (6) is located above the frame (7). The lower support plate (6) is rotatably connected to the bottom of the upper platform (1) of the rotating platform through a pressure-bearing bearing. The mounting plate (9) is located on the frame (7) as the mounting platform of the connecting seat (11).

2. The test apparatus for a landing gear steering mechanism according to claim 1, characterized in that, The rotating platform also includes an upper flange bushing (14), the lower end of which is fixedly connected to the main shaft (10). The upper side of the upper flange bushing (14) is a flange part, and the upper platform (1) is fixedly connected to the flange part of the upper flange bushing (14).

3. The test apparatus for a landing gear steering mechanism according to claim 1, characterized in that, A displacement sensor (12) and a torque sensor (13) are also installed on the spindle (10).

4. The test apparatus for a landing gear steering mechanism according to claim 1, characterized in that, Both the upper platform (1) and the lower support plate (6) are disc structures. The sides of the upper platform (1) and the lower support plate (6) have corner marks and corner scales.

5. The test apparatus for a landing gear steering mechanism according to claim 1, characterized in that, The lower surface of the upper platform (1) and the upper surface of the lower support plate (6) are both provided with a groove for placing the pressure bearing.

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