Tool for measuring rotation torque of nose landing gear of civil aircraft

Abstract

The utility model discloses a tool for measuring the rotation torque of a nose landing gear of a civil aviation passenger plane, which comprises a main body, the main body comprises a fixed block and an extension bar, the rear end of the fixed block is fixedly connected with the front end of the extension bar, the front end of the fixed block is provided with two symmetrical connecting holes, and the symmetrical line of the two connecting holes coincides with the center line of the extension bar. During testing, the fixing block is connected with a towing head mounting position on an inner cylinder of the nose landing gear through the two connecting holes, and during testing, the rear end of the lengthening rod is connected with the dynamometer. According to the utility model, a worker can be assisted to test the rotating torque of the nose landing gear more conveniently, so that whether the performance of a new cam assembly after replacement meets the requirements of a manual or not can be verified more conveniently.

Description

Technical Field

[0001] The utility model relates to a test tool for a civil aviation airliner, specifically to a tool for measuring the rotation torque of the nose landing gear of a civil aviation airliner Background Technique

[0002] The cam assembly is an important component on the nose landing gear of a civil aviation airliner, including an upper part and a lower part, namely an upper cam and a lower cam respectively. When the nose landing gear is in the extended state, the upper cam and the lower cam will be combined together to play a centering role. When the aircraft lands, the upper cam and the lower cam play a role in centering the axle, and the direction of the wheel will point directly in front of the aircraft, enabling the aircraft to land along a straight line and decelerate

[0003] When overhauling the nose landing gear, if the cam assembly of the nose landing gear is not replaced, then there is no need to test the rotation torque of the nose landing gear after overhaul. However, if the cam assembly is replaced, then it is necessary to test the rotation torque of the nose landing gear after replacement

[0004] The following takes the nose landing gear of an A330 civil aviation airliner as an example to illustrate the test requirements for the rotation torque: During the test, the shock strut inside the nose landing gear of the A330 civil aviation airliner is inflated to make it extend. After extension, a tire or an equivalent heavy object is installed on the axle of the nose landing gear. Then, according to the requirements of the manual, first rotate the nose landing gear 8° left and right. At this time, the rotation torque should not be greater than 2700 N·m. Then, when rotating back from the 8° position to the 0° position, the rotation torque should not be less than 600 N·m

[0005] However, due to the low frequency of replacement of the cam assembly during the overhaul process and the small number of nose landing gears that need to be tested for the rotation torque, the original factory tools for supporting and fixing the nose landing gear do not include the function of measuring the rotation torque. Therefore, it is necessary to adopt additional auxiliary tools to achieve the test of the rotation torque

[0006] If a lengthening rod is directly used to rotate the nose landing gear at the axle position, due to the narrow space, the column of the support of the original factory tool for supporting and fixing the nose landing gear will be touched during the rotation process, and it is not suitable for multiple people to rotate and operate, making the test very difficult. Therefore, a tool for measuring the rotation torque of the nose landing gear of a civil aviation airliner of the present utility model is designed Content of the Utility Model

[0007] The purpose of the present utility model is to provide a tool for measuring the rotation torque of the nose landing gear of a civil aviation airliner, which can assist the staff to more conveniently test the rotation torque of the nose landing gear, so as to more conveniently verify whether the performance of the newly replaced cam assembly meets the requirements of the manual

[0008] The purpose of the present utility model is achieved through the following technical solutions:

[0009] A tool for measuring the rotational torque of the nose landing gear of a civil airliner, characterized in that: it includes a main body, the main body includes a fixed block and an extension rod, the rear end of the fixed block is fixedly connected to the front end of the extension rod, and the front end of the fixed block is provided with two symmetrical connection holes, and the symmetry line of the two connection holes coincides with the center line of the extension rod. During the test, the fixed block is connected to the towing head installation part on the inner cylinder of the nose landing gear through the two connection holes, and the rear end of the extension rod is connected to a dynamometer during the test.

[0010] A further technical solution of the present utility model is that: the fixed block as a whole is a symmetrical structure.

[0011] A further technical solution of the present utility model is that: the two side edges of the fixed block are bevel edges, so that the width of the fixed block gradually becomes smaller from the front end to the rear end, and the front edge of the fixed block is an inwardly concave arc edge.

[0012] A further technical solution of the present utility model is that: the rear end of the fixed block is in the shape of a triangular tip.

[0013] A further technical solution of the present utility model is that: protective layers are respectively provided on the two side edges, the front edge of the fixed block, and the side wall of the connection hole.

[0014] A further technical solution of the present utility model is that: the protective layer is a copper bushing.

[0015] A further technical solution of the present utility model is that: the length of the extension rod is 2 meters.

[0016] Compared with the prior art, the present utility model has the following beneficial effects:

[0017] The fixed block of the tool of the present utility model can be directly connected to the towing head installation part on the inner cylinder of the nose landing gear. Specifically, it is directly connected by a fixing pin passing through the connection hole of the fixed block and the installation hole of the head installation part, thus solving the connection problem. The connection is convenient, fast, and stable and reliable. After the tool is connected to the towing head installation part on the inner cylinder of the nose landing gear, the rotational torque test can be carried out by the staff pulling the dynamometer connected to the rear end of the extension rod, and the rotational torque value of the nose landing gear can be quickly measured, with strong practicability. And through the extension rod, the staff can more easily rotate the nose landing gear for the rotational torque test. In actual use, when the extension rod is designed to be 2 meters, it takes about 135KG of force to rotate the nose landing gear, and 3 staff members can easily complete the measurement of the rotational torque. Description of the Drawings

[0018] Figure 1 is a three-dimensional schematic diagram of the tool of the embodiment of the present utility model;

[0019] Figure 2 is a top view schematic diagram of the tool of the embodiment of the present utility model;

[0020] Figure 3 It is a schematic structural view when the tooling in the embodiment of the present utility model is connected to the towing head installation position on the inner cylinder of the nose landing gear.

[0021] The meanings of the reference numerals in the figure are as follows:

[0022] 1 - extension rod; 2 - fixing block; 3 - connection hole; 4 - protective layer; 5 - bevel edge; 6 - arc edge; 7 - fixing pin; 8 - nose landing gear; 9 - towing head installation position; 10 - axle. Specific embodiments

[0023] The present utility model will be further described below in conjunction with the embodiments.

[0024] In the description of the present utility model, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model.

[0025] In the description of the present utility model, the meaning of several is one or more, the meaning of multiple is two or more, greater than, less than, exceeding, etc. are understood as not including the present number, above, below, within, etc. are understood as including the present number. If the first and second are described, it is only for the purpose of distinguishing technical features and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or the sequence relationship of the indicated technical features.

[0026] In the description of the present utility model, unless otherwise clearly defined, words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in the present utility model in combination with the specific content of the technical solution.

[0027] Embodiment:

[0028] As Figure 1 and Figure 2 shown, the tooling for measuring the rotational torque of the nose landing gear of a civil airliner in this embodiment includes a main body. The main body is made of metal material as a whole, specifically made of 45 steel, and the main body includes a fixing block 2 and an extension rod 1.

[0029] The fixing block 2 is a symmetrical structure as a whole. The two side edges of the fixing block 2 are bevel edges 5, so that the width of the fixing block 2 gradually becomes smaller from the front end to the rear end, and its rear end is in the shape of a triangular tip. The front edge of the fixing block 2 is an inwardly concave arc edge 6.

[0030] On both sides of the front end of the fixed block 2, there are two connecting holes 3 respectively, and the positions of the two connecting holes 3 are symmetrical.

[0031] The rear end of the fixed block 2 is fixedly connected to the front end of the extension rod 1, and the fixed connection method is multi-point welding. The symmetry line of the two connecting holes 3 coincides with the center line of the extension rod 1.

[0032] In this embodiment, the length of the extension rod 1 is 2 meters. This length is the conclusion drawn after weighing various factors. If the extension rod 1 is too short, to achieve a rotational torque of 2700 N·m, the required force is too large and it cannot be rotated by manpower. If the extension rod 1 is too long, although the rotational force can be reduced, the cost of the tooling increases and it is not convenient to operate. Using a 2-meter extension rod, the rotational force is about 135 kg, and the rotational torque test can be easily completed by 3 workers.

[0033] In this embodiment, protective layers 4 are respectively provided on both side edges, the front edge of the fixed block 2, and the side walls of the connecting holes 3. The protective layer 4 is a copper bushing with a relatively soft material, which can protect the nose landing gear from damage. The copper bushing at the connecting hole 3 can protect the two fixing pins for connection, and the copper bushings on the side edges and the front edge can prevent the tooling from hitting the inner cylinder, and there is a paint layer on the inner cylinder, and hitting the inner cylinder with the tooling will cause damage to the paint layer.

[0034] As Figure 3 shown, the process of performing a rotational torque test on the nose landing gear of a civil airliner by the tooling of this embodiment is as follows:

[0035] Step 1: Fix the nose landing gear 8 to be tested on the original factory tool for supporting and fixing the nose landing gear through two pivot pins at the upper end. After the fixed installation, the inner cylinder at the lower end of the nose landing gear 8 can rotate;

[0036] Step 2: Install an angle gauge on the nose landing gear 8 according to the requirements of the manual to check the rotation angle of the nose landing gear 8;

[0037] Step 3: Install wheels or equivalent weights on the axle 10 of the nose landing gear 8 according to the requirements of the manual to simulate the real state when the aircraft lands;

[0038] Step 4: Inflate the shock absorber strut of the nose landing gear 8 to the specified pressure in the manual according to the requirements;

[0039] Step 5: Align the two connecting holes 3 of the fixed block 2 of the tooling of this embodiment with the mounting holes at the towing head mounting part 9 on the inner cylinder of the nose landing gear 8, and achieve fixed connection by passing the fixing pins 7 through the connecting holes and the mounting holes correspondingly. Then, put an external steel pipe on the extension rod 1 to extend it again to form a lever arm;

[0040] Step 6: Measure with a ruler, make a mark at the 2-meter position of the lever arm, and install a dynamometer at the mark; then, have the staff pull the dynamometer for testing. During the test, first rotate the nose landing gear 8 smoothly, read the rotational force during the rotation process, stop rotating when the rotation angle reaches 8°, and then slowly rotate back to 0°, reading the rotational force during the rotation back;

[0041] Step 7: Calculate the torque based on the rotational force and the lever arm value, and then compare it with the torque value required by the original factory in the manual to determine whether the test result is qualified.

[0042] The above embodiments of the present invention do not limit the protection scope of the present invention. The implementation manners of the present invention are not limited thereto. All such modifications, substitutions or changes in various other forms made to the above structure of the present invention according to the above content of the present invention, in accordance with the common general knowledge and customary means in the art, without departing from the above basic technical idea of the present invention, shall fall within the protection scope of the present invention.

Claims

1. A tool for measuring the rotational torque of the nose landing gear of a civil airliner, characterized in that: It includes a main body, and the main body includes a fixed block and an extension rod. The rear end of the fixed block is fixedly connected to the front end of the extension rod. There are two symmetrically arranged connection holes at the front end of the fixed block, and the symmetry line of the two connection holes coincides with the midline of the extension rod. During the test, the fixed block is connected to the towing head installation on the inner cylinder of the front landing gear through the two connection holes, and the rear end of the extension rod is connected to a dynamometer during the test.

2. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 1, characterized in that: The fixed block is a symmetric structure as a whole.

3. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 2, characterized in that: The two side edges of the fixed block are beveled edges, such that the width of the fixed block gradually decreases from the front end to the rear end, and the front edge of the fixed block is a concave arc edge.

4. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 3, characterized in that: The rear end of the fixed block is in the shape of a triangular tip.

5. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 1, characterized in that: Protective layers are respectively provided on the two side edges, the front edge of the fixed block, and the side walls of the connection holes.

6. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 5, characterized in that: The protective layer is a copper bushing.

7. The tooling for measuring the rotational torque of the nose landing gear of a civil airliner according to claim 1, characterized in that: The length of the extension rod is 2 meters.

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