Aircraft nose landing gear steering test mechanism

Abstract

The utility model relates to the technical field of aviation, in particular to an aircraft nose landing gear steering testing mechanism which comprises a box body, a top seat is arranged on the top end wall of the box body, a supporting column is rotatably connected to the middle portion of the inner bottom wall of the box body through a bearing, and the top end wall of the supporting column extends into the top seat and is provided with a top plate. A connecting plate is connected to the outer wall of the supporting column in an interference fit mode, a hydraulic oil cylinder is arranged on the inner bottom wall of the box body, an electromagnet is arranged on the driving top end wall of the hydraulic oil cylinder, a sensor is arranged on the outer wall of the hydraulic oil cylinder, a rail is arranged on the inner bottom wall of the box body, and a plurality of connecting rods are arranged on the bottom end wall of the top plate. And rollers are arranged on the bottom end walls of the connecting rods, and the rollers are connected to the rails in a sliding mode. According to the utility model, the rotation angle of the supporting column is recorded through the sensor, so that the data of the rotation angle of the nose landing gear of the airplane can be accurately obtained, an accurate quantitative index is provided for the evaluation of the steering performance of the nose landing gear of the airplane, and the requirement of the modern aviation industry on high-precision performance detection of airplane parts is met; the control precision of the aircraft sliding on the ground can be improved, and the flight safety is guaranteed.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aviation technology, concretely relates to a plane nose landing gear steering test mechanism. BACKGROUND

[0002] In the field of aviation, the safety of the aircraft is of vital importance, and the steering performance reliability of the nose landing gear as a key component in the process of take-off and landing and taxiing of the aircraft is directly related to the flight safety. The nose landing gear of the aircraft not only bears the weight and impact force of the aircraft during taxiing on the ground, but also needs to have precise steering control capability to ensure that the aircraft can accurately steer and travel on the runway.

[0003] Currently, when detecting the steering of the nose landing gear of the aircraft, the method commonly used in the industry is to press the front wheel on a metal plate for simple steering detection. This detection method is mainly to prevent direct friction between the tire and the ground, to protect the tire and to simulate the running state of the aircraft on the ground to some extent. However, this traditional detection method has many obvious limitations.

[0004] This simple detection method can only determine whether the nose landing gear steering is normal by visual observation. The detection personnel can only observe the approximate action of the nose landing gear during steering by naked eye, lack precise quantitative indicators, and cannot accurately determine the steering angle of the nose landing gear. In the modern aviation industry, the performance requirements for aircraft parts are getting higher and higher, and the precise steering angle plays a key role in the controllability and safety of the aircraft on the ground. Inaccurate steering angle may cause the aircraft to deviate from the predetermined route during taxiing, increasing the risk of collision with other aircraft or ground facilities.

[0005] Due to the lack of accurate measurement and recording of the steering angle, maintenance personnel cannot make targeted adjustments and maintenance of the steering system of the nose landing gear according to the detection results. This may cause some potential problems to be discovered and solved in time, and these problems may accumulate over time, eventually affecting the overall safety and reliability of the aircraft. UTILITY MODEL CONTENT

[0006] The utility model discloses a nose landing gear steering test mechanism for solving the above-mentioned problems.

[0007] In order to achieve the above technical purpose and achieve the above technical effect, the utility model is realized by the following technical scheme:

[0008] The utility model provides a kind of aircraft nose landing gear steering test mechanism, including box, top end wall of the box is equipped with top seat, the inner bottom wall of the box is rotationally connected with support column in middle part by bearing, the top end wall of the support column extends into top seat and is equipped with top plate, the outer wall of the support column is connected with connecting plate by interference fit, the inner bottom wall of the box is equipped with hydraulic cylinder, the driving top end wall of the hydraulic cylinder is equipped with electromagnet, the outer wall of the hydraulic cylinder is equipped with sensor, the inner bottom wall of the box is equipped with track, the bottom end wall of the top plate is equipped with multiple connecting rods, the bottom end wall of the connecting rod is equipped with roller, and roller is slidably connected on track.

[0009] Further, the outer ring of the bearing is fixedly connected with the inner bottom wall of the box through the bearing seat, and the inner ring of the bearing is connected with the outer wall of the support column by interference fit.

[0010] Further, the connecting plate is located inside the multiple connecting rods.

[0011] Further, the multiple rollers are arranged on the bottom end wall of the top plate in circumferential gaps.

[0012] Further, the sensor uses an optical angle sensor, and the outer wall of the support column is connected with a code disc by interference fit.

[0013] The utility model has the advantages that:

[0014] The sensor records the angle of rotation of the support column, accurately obtaining the data of the rotation angle of the aircraft nose landing gear, which provides accurate quantitative indicators for the evaluation of the steering performance of the aircraft nose landing gear, meets the requirements of modern aviation industry for high-precision performance detection of aircraft parts, helps to improve the control accuracy of the aircraft during ground sliding, and ensures flight safety.

[0015] Accurate angle measurement and recording provide detailed and accurate detection basis for maintenance personnel, who can adjust and maintain the steering system of the nose landing gear according to these data, timely find and solve potential problems, avoid maintenance blindness caused by lack of accurate data, effectively prevent problem accumulation, prolong the service life of the nose landing gear, and improve the safety and reliability of the aircraft as a whole.

[0016] Similar to the traditional detection method, the aircraft nose landing gear is placed on the top plate for testing, avoiding direct friction between the tire and the ground, protecting the tire, reducing the wear and tear of the tire caused by detection, and reducing the operating cost of the aircraft. This method can simulate the running state of the aircraft on the ground to some extent, making the detection result more in line with the actual flight situation, and improving the effectiveness and practicality of the detection. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some of the embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort.

[0018] Fig. 1 The structural schematic diagram of the present application is shown in the figure.

[0019] Fig. 2 The structural schematic diagram of the present application is shown in the figure.

[0020] In the drawings, the components represented by each number are listed as follows:

[0021] 1, box, 2, top seat, 3, bearing, 4, support column, 5, top plate, 6, connecting plate, 7, hydraulic cylinder, 8, electromagnet, 9, sensor, 10, track, 11, connecting rod, 12, roller. DETAILED DESCRIPTION

[0022] The technical scheme in the embodiments of the present application will be described clearly and completely in the following with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without any creative effort are within the scope of protection of the present application.

[0023] Referring to Figs. 1-2 As shown in the figure, a kind of aircraft nose landing gear steering test mechanism, including box 1, top end wall of box 1 is equipped with top seat 2, the inner bottom wall of box 1 is equipped with support column 4 by bearing 3 rotation connection in middle part, the top end wall of support column 4 extends into top seat 2 and is equipped with top plate 5, support column 4 is equipped with connecting plate 6 on outer wall with interference fit, the inner bottom wall of box 1 is equipped with hydraulic cylinder 7, the driving top end wall of hydraulic cylinder 7 is equipped with electromagnet 8, the outer wall of hydraulic cylinder 7 is equipped with sensor 9, the inner bottom wall of box 1 is equipped with track 10, the bottom end wall of top plate 5 is equipped with multiple connecting rods 11, connecting rod 11 is equipped with roller 12 on bottom end wall, and roller 12 is slidably connected on track 10.

[0024] Further, the outer ring of bearing 3 is fixedly connected with the inner bottom wall of box 1 through bearing seat, the inner ring of bearing 3 is connected with the outer wall of support column 4 with interference fit, bearing 3 plays a fixing role on support column 4, so that support column 4 can rotate through bearing 3.

[0025] Further, the connecting plate 6 is located inside the plurality of connecting rods 11, and by controlling the on-off of the hydraulic oil cylinder 7 and the electromagnetic iron 8, the rotating test and fixing operation can be easily realized.

[0026] Further, the plurality of rollers 12 are arranged in a circumferential gap on the bottom end wall of the top plate 5, which effectively enhances the stability of the top plate 5 during rotation, reduces the interference of unstable factors such as shaking and deviation on the measurement results, ensures the accuracy and reliability of the angle measurement, and makes the test data more reliable.

[0027] Further, the sensor 9 adopts an optical angle sensor, and the outer wall of the support column 4 is connected with a code disc in an interference fit, and the optical angle sensor realizes angle measurement by using the photoelectric conversion principle. When the support column 4 rotates, the code disc rotates with it, and the optical angle sensor emits light and receives the light passing through the code disc, and generates different electrical signals according to the on-off of the light, and by processing and counting these electrical signals, the rotation angle of the rotating shaft can be determined.

[0028] Through the technical personnel, all electrical components and parts in the case are general standard parts or parts known to those skilled in the art, and their structure and principle are known to those skilled in the art through technical manuals or through conventional experimental methods. The model is adapted to the normal operation of the scheme, and all electrical components and their power supply are connected by wires, and according to the actual situation, the appropriate controller is selected to meet the control requirements. The specific connection and control sequence should refer to the working principle of the following, the working sequence of each electrical component is completed, and the detailed connection means is a known technology in the art, and the electrical control is not described.

[0029] One specific application of the embodiment is:

[0030] In use, a groove for placing the device is dug on the ground, so that the top plate 5 is in the same plane as the ground, the aircraft nose landing gear is moved to the top plate 5, the electromagnetic iron 8 is powered off, the hydraulic oil cylinder 7 is started to drive the electromagnetic iron 8 to move downward, and the fixing of the connecting plate 6 is released. The aircraft nose landing gear is rotated for test, the top plate 5 drives the support column 4, the connecting plate 6, the connecting rod 11 and the roller 12 to rotate, the connecting rod 11 and the roller 12 support the outside of the top plate 5, so that the top plate 5 is more stable during rotation, and the angle of rotation of the support column 4 can be recorded by the sensor 9, so as to obtain the data of the rotation angle of the aircraft nose landing gear. After the test is completed, the electromagnetic iron 8 is moved upward by the hydraulic oil cylinder 7 to contact the connecting plate 6, and the electromagnetic iron 8 is magnetically attracted to the outer wall of the connecting plate 6 to fix the support column 4 and the top plate 5, so as to prevent rotation during angle test.

[0031] Of course, the above description is not a limitation of the utility model, the utility model is not limited to the above examples, the ordinary skilled in the art, within the scope of the utility model, the changes, changes, additions or replacement made, should belong to the protection scope of the utility model.

Claims

1. An aircraft nose landing gear steering test mechanism, characterised in that: Including box (1), The top end wall of the box (1) is provided with a top seat (2), the inner bottom wall of the box (1) is rotatably connected with a support column (4) through a bearing (3) in the middle, the top end wall of the support column (4) extends into the top seat (2) and is provided with a top plate (5), the outer wall of the support column (4) is connected with a connecting plate (6) in interference fit, the inner bottom wall of the box (1) is provided with a hydraulic oil cylinder (7), the driving top end wall of the hydraulic oil cylinder (7) is provided with an electromagnet (8), the outer wall of the hydraulic oil cylinder (7) is provided with a sensor (9), the inner bottom wall of the box (1) is provided with a track (10), the bottom end wall of the top plate (5) is provided with a plurality of connecting rods (11), the bottom end wall of the connecting rod (11) is provided with a roller (12), and the roller (12) is slidably connected to the track (10).

2. A steering test mechanism for a nose landing gear of an aircraft according to claim 1, characterized in that: The outer ring of the bearing (3) is fixedly connected with the inner bottom wall of the box (1) through a bearing seat, and the inner ring of the bearing (3) is connected with the outer wall of the support column (4) in interference fit.

3. A steering test mechanism for a nose landing gear of an aircraft as claimed in claim 1, wherein: The connecting plate (6) is located on the inner side of the plurality of connecting rods (11).

4. A steering test mechanism for a nose landing gear of an aircraft as claimed in claim 1, wherein: A plurality of the rollers (12) are arranged in circumferential gaps on the bottom end wall of the top plate (5).

5. A steering test mechanism for a nose landing gear of an aircraft as claimed in claim 1, wherein: The sensor (9) adopts an optical angle sensor, and the outer wall of the support column (4) is connected with a code disc in interference fit.

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