Undercarriage wheel cabin gap measuring equipment and method

Abstract

The invention belongs to the technical field of aircraft structure design, and discloses an undercarriage wheel cabin gap measuring device and method.The device comprises a fixing assembly and a rotating assembly, the fixing assembly is fixedly installed on the inner side outside a hub shaft of an undercarriage, and the rotating assembly is rotatably installed on the outer side outside the hub shaft of the undercarriage; a motor assembly is arranged on the fixed assembly, and the motor assembly is connected with the rotating assembly and drives the rotating assembly to rotate around a hub shaft of the aircraft landing gear; a support is arranged on the rotating assembly, and the distance measuring device is detachably installed on the support. After the undercarriage wheel cabin gap measuring equipment is installed on the undercarriage wheel shaft, the laser range finder is used for measuring the distance, the gap between the airplane wheel tire and the undercarriage wheel cabin can be obtained through later data processing, and the problem that the gap is difficult to measure is solved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft structure design, and relates to a landing gear wheel bay measuring device, in particular to a landing gear wheel bay gap measuring device and method. BACKGROUND

[0002] When designing the landing gear, it is necessary to ensure that there is enough gap between the aircraft wheel tire and the landing gear wheel bay after the landing gear is retracted into the landing gear wheel bay. After actual installation, it is difficult to measure the gap because the hatch is closed.

[0003] 202410126672 gives an idea of measuring the landing gear wheel bay, which uses a visual device to scan the landing gear wheel bay and model it, but this scheme has high cost, and it needs to be scanned and modeled again for different aircraft, which not only increases the measurement cost, but also greatly increases the design cost. SUMMARY

[0004] In order to solve the above problems, the present application provides a landing gear wheel bay gap measuring device and method, which can be used to measure the gap between the aircraft wheel tire and the landing gear wheel bay after the landing gear is retracted into the landing gear wheel bay.

[0005] The technical scheme of the present application is as follows: A landing gear wheel bay gap measuring device, comprising a fixed component and a rotating component, the fixed component is fixedly installed on the inner side of the hub shaft of the aircraft landing gear, the rotating component is rotatably installed on the outer side of the hub shaft of the aircraft landing gear, a motor assembly is provided on the fixed component, the motor assembly connects and drives the rotating component to rotate around the hub shaft of the aircraft landing gear; a bracket is provided on the rotating component, and a distance measuring device is detachably mounted on the bracket.

[0006] Further, the distance measuring device is a laser range finder.

[0007] Further, the bracket is a cross-shaped structure, the top of the vertical bracket of the bracket is flush with the outer circle of the landing gear tire of the aircraft, and the ends of the horizontal bracket of the bracket are flush with the ends in the thickness direction of the landing gear tire of the aircraft.

[0008] Further, the distance measuring device is connected with the bracket through a clamp, and the clamp can be installed and fixed at any position of the bracket and can be detached.

[0009] Further, the fixed component further comprises a fixed base connected with the hub shaft of the aircraft landing gear, the fixed base is provided with a rotary electrical connector at the outward end of the hub shaft, one side of the fixed base is connected with the motor assembly, the other side of the fixed base is provided with a power control assembly, and the power control assembly is connected with the motor assembly through an electrical control line.

[0010] Further, the rotating assembly comprises a rotating base, and an external gear is arranged at an inner side end of the hub shaft of the rotating base.

[0011] Further, the rotating assembly is provided with at least two insertion slots, and the support is inserted into one of the insertion slots in an interference fit.

[0012] Further, the rotating base is further connected with an electric connector, and the electric connector is electrically connected with the distance measuring device.

[0013] Further, the electric connector is connected with the metal strip in the insertion slot through a guide, the surface of the support is provided with a groove, the groove is provided with a metal strip, the support is connected with the metal strip between the two metal strips after being inserted into the insertion slot, and the distance measuring device is electrically connected with the metal strip of the support through a clamp.

[0014] A landing gear wheel bay clearance measuring method uses the landing gear wheel bay clearance measuring device, and comprises the following steps: S1, the wheel on the landing gear is removed, the measuring device is mounted on the hub shaft of the landing gear, and is fixed through a limiting nut; S2, at least one distance measuring device is mounted on the support; S3, the motor assembly is started to drive the rotating assembly to rotate around the hub shaft for one circle, and the distance measuring device records the distance parameter of one circle; S4, the distance parameter recorded by the distance measuring device is input into a computer, and the clearance between the tire of the wheel and the landing gear wheel bay corresponding to the position of the distance measuring device is obtained; S5, the position of the distance measuring device on the support is replaced, S3 and S4 are repeated, and the clearance between the tire of the wheel and the landing gear wheel bay at other positions is obtained.

[0015] Advantages of the present application are as follows: 1, when the landing gear is designed, it is necessary to ensure that the clearance between the tire of the wheel and the landing gear wheel bay is sufficient after the landing gear is retracted into the landing gear wheel bay, so as to ensure the safety of the structure when the wheel rotates. After the landing gear is actually installed, the door is in a closed state, and the clearance is difficult to measure by manpower. The landing gear wheel bay clearance measuring device is installed on the landing gear wheel shaft, the distance is measured by using a laser distance measuring device, and the clearance between the tire of the wheel and the landing gear wheel bay can be obtained through later data processing, so that the problem that the clearance is difficult to measure is solved.

[0016] 2, the present application has low cost and high efficiency, and can adaptively measure various different landing gear wheel bays of aircrafts, and the support is designed in an insertion slot installation mode, so that different aircraft tire sizes can be adapted by replacing the support. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. The drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0018] Figure 1 Figure 1 is a schematic diagram of the landing gear wheel bay gap measuring device of the present application.

[0019] Figure 2 Figure 1 is a schematic diagram of the landing gear wheel bay gap measuring device of the present application.

[0020] Figure 3 Figure 1 is a schematic diagram of the landing gear wheel bay gap measuring device of the present application.

[0021] Figure 4 Figure 1 is a schematic diagram of the landing gear wheel bay gap measuring device of the present application.

[0022] Figure 5 Figure 1 is a schematic diagram of the landing gear wheel bay gap measuring device of the present application.

[0023] 1, fixed assembly, 2, rotating assembly, 3, limit nut, 4, landing gear strut; 1-1, fixed base, 1-2, motor and reducer, 1-3, rotary electrical connector, 1-4, power supply and control assembly; 2-1, rotating base, 2-2, electrical connector, 2-3, laser distance meter, 2-4, clamp, 2-5, bracket. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the following will combine the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0025] The features and exemplary embodiments of the various aspects of the present application will be described in detail below with reference to the drawings. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely illustrative of the present application and does not limit the scope of the present application. The present application is not limited to the specific settings and methods described below, but covers any modifications, equivalents, and alternatives falling within the spirit of the present application. In the drawings and the following description, well-known structures and techniques are not shown in order to avoid unnecessary obscurity of the present application.

[0026] In the description of the present application, it should be noted that the directions or positional relationships indicated by "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like are based on the directions or positional relationships described in the drawings, and are only for the convenience of describing the present application and simplifying the description, and cannot be understood as limiting the present application. In addition, the ordinal numbers (for example, "first" and "second") are used to distinguish objects, and are not limited to the order, and cannot be understood as indicating or implying relative importance.

[0027] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, "mounting", "connection", and "connection" should be understood in a broad sense, which can be direct connection or indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0028] It should be noted that, in the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other, and each embodiment can be mutually referred to and quoted. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0029] Embodiment 1: A landing gear wheel compartment gap measuring device, comprising a fixed component 1 and a rotating component 2, the fixed component 1 is fixedly installed on the inner side of the hub shaft of the aircraft landing gear, the rotating component 2 is rotatably installed on the outer side of the hub shaft of the aircraft landing gear, the fixed component 1 is provided with a motor assembly 1-2, the motor assembly 1-2 is connected and drives the rotating component 2 to rotate around the hub shaft of the aircraft landing gear; the rotating component 2 is provided with a bracket 2-5, and a distance measuring device is detachably installed on the bracket 2-5.

[0030] The distance measuring device is a laser range finder 2-3.

[0031] The support 2-5 is a cross-shaped structure, the top of the vertical support of the support 2-5 is flush with the outer circle of the landing gear tire of the aircraft, and the two ends of the horizontal support of the support 2-5 are flush with the two ends in the thickness direction of the landing gear tire of the aircraft.

[0032] The distance measuring device is connected with the support 2-5 through the clamp 2-4, and the clamp 2-4 can be installed, fixed and detached at any position of the support 2-5.

[0033] The fixing assembly 1 further comprises a fixing base 1-1 connected with the hub shaft of the landing gear of the aircraft, the fixing base 1-1 is provided with a rotary electrical connector 1-3 at the outward end of the hub shaft, one side of the fixing base 1-1 is connected with the motor assembly 1-2, and the other side of the fixing base 1-1 is provided with a power supply control assembly 1-4, and the power supply control assembly 1-4 is connected with the motor assembly 1-2 through an electrical control line.

[0034] The rotating assembly 2 comprises a rotary base 2-1, and the rotary base 2-1 is provided with an external gear at the inward end of the hub shaft.

[0035] The rotating assembly 2 is provided with at least two insertion slots, and the support 2-5 is inserted into one of the insertion slots in an interference manner.

[0036] The rotary base 2-1 is further connected with an electrical connector 2-2, and the electrical connector 2-2 is electrically connected with the distance measuring device.

[0037] The electrical connector 2-2 is connected with the metal strip in the guide connection slot, the surface of the support 2-5 is provided with a groove, the groove is provided with a metal strip, the metal strips on the two sides of the support 2-5 are connected after the support 2-5 is inserted into the insertion slot, and the distance measuring device is electrically connected by the communication between the metal strips of the support 2-5 through the clamp 2-4.

[0038] A landing gear wheel bay gap measuring method using the landing gear wheel bay gap measuring device, comprising the following steps: S1, the wheel on the landing gear is removed, the measuring device is installed on the hub shaft of the landing gear and fixed through a limiting nut; S2, at least one distance measuring device is installed on the support 2-5; S3, the motor assembly 1-2 is started to drive the rotating assembly 2 to rotate around the hub shaft for one revolution, and the distance measuring device records the distance parameter for one revolution; S4, the distance parameter recorded by the distance measuring device is input into a computer to obtain the gap between the tire of the wheel and the landing gear wheel bay corresponding to the position of the distance measuring device; S5, the position of the distance measuring device on the support 2-5 is changed, and S3 and S4 are repeated to obtain the gap between the tire of the wheel and the landing gear wheel bay at other positions. Embodiment 2: As Figure 1The image shows a landing gear wheel well clearance measuring instrument, which consists of a fixed assembly 1 and a rotating assembly 2. The rotating assembly 2 is mounted on the fixed assembly 1 and can rotate around a pivot axis.

[0039] like Figure 2 The fixed assembly 1 shown mainly consists of a fixed base 1-1, a motor and reducer 1-2, a rotary electrical connector 1-3, and a power supply and control assembly 1-4. The motor and reducer 1-2, the rotary electrical connector 1-3, and the power supply and control assembly 1-4 are all fixedly connected to the fixed base 1-1. The motor and reducer 1-2 and the rotary electrical connector 1-3 are connected to the power supply and control assembly 1-4 via wires.

[0040] like Figure 3 The rotating assembly 2 shown mainly consists of a rotating base 2-1, an electrical connector 2-2, a laser rangefinder 2-3, a clamp 2-4, and a bracket 2-5. The electrical connector 2-2 is fixedly connected to the rotating base 2-1. The bracket 2-5 is fixedly connected to the rotating base 2-1 and can be installed in different mounting slots of the rotating base 2-1 according to actual usage needs. The laser rangefinder 2-3 is fixedly connected to the clamp 2-4. The bracket 2-5 has guide rails in both horizontal and vertical directions, and the clamp 2-4 can be installed on either guide rail according to actual usage needs. After the laser rangefinder 2-3 is fixed, it must be ensured that the laser emission axis of the laser rangefinder 2-3 is coplanar with the rotation axis of the rotating base 2-1. The wires of the laser rangefinder 2-3 are connected to the electrical connector 2-2.

[0041] like Figure 4 As shown, after the fixed assembly 1 and the rotating assembly 2 are installed on the wheel axle of the landing gear strut 4, the limit nut 3 is tightened to complete the installation of the landing gear wheel well clearance measuring instrument. Electrical connector 2-2 in the rotating assembly 2 is connected to the power supply and control assembly 1-4 via rotating electrical connector 1-3. The gear of the rotating base 2-1 meshes with the gear of the motor and reducer 1-2.

[0042] When the landing gear wheel bay clearance measuring instrument is working, the motor and reducer 1-2 drive the rotating component 2 to rotate one revolution, and the laser rangefinder 2-3 records the distance dimensions at each moment. The clearance between the wheel tire and the landing gear wheel bay can be obtained by subtracting the fixed dimensions of the wheel tire after post-processing.

[0043] like Figure 5 As shown, for commonly used aircraft wheels and tires, only three points need to be measured to roughly obtain the clearance between the aircraft wheel / tire and the landing gear wheel well. like Figure 1 The image shows a landing gear wheel well clearance measuring instrument, which consists of a fixed assembly 1 and a rotating assembly 2. The rotating assembly 2 is mounted on the fixed assembly 1 and can rotate around a pivot axis.

[0044] like Figure 2The fixed assembly 1 shown mainly consists of a fixed base 1-1, a motor and reducer 1-2, a rotary electrical connector 1-3, and a power supply and control assembly 1-4. The motor and reducer 1-2, the rotary electrical connector 1-3, and the power supply and control assembly 1-4 are all fixedly connected to the fixed base 1-1. The motor and reducer 1-2 and the rotary electrical connector 1-3 are connected to the power supply and control assembly 1-4 via wires.

[0045] like Figure 3 The rotating assembly 2 shown mainly consists of a rotating base 2-1, an electrical connector 2-2, a laser rangefinder 2-3, a clamp 2-4, and a bracket 2-5. The electrical connector 2-2 is fixedly connected to the rotating base 2-1. The bracket 2-5 is fixedly connected to the rotating base 2-1 and can be installed in different mounting slots of the rotating base 2-1 according to actual usage needs. The laser rangefinder 2-3 is fixedly connected to the clamp 2-4. The bracket 2-5 has guide rails in both horizontal and vertical directions, and the clamp 2-4 can be installed on either guide rail according to actual usage needs. After the laser rangefinder 2-3 is fixed, it must be ensured that the laser emission axis of the laser rangefinder 2-3 is coplanar with the rotation axis of the rotating base 2-1. The wires of the laser rangefinder 2-3 are connected to the electrical connector 2-2.

[0046] like Figure 4 As shown, after the fixed assembly 1 and the rotating assembly 2 are installed on the wheel axle of the landing gear strut 4, the limit nut 3 is tightened to complete the installation of the landing gear wheel well clearance measuring instrument. Electrical connector 2-2 in the rotating assembly 2 is connected to the power supply and control assembly 1-4 via rotating electrical connector 1-3. The gear of the rotating base 2-1 meshes with the gear of the motor and reducer 1-2.

[0047] When the landing gear wheel bay clearance measuring instrument is working, the motor and reducer 1-2 drive the rotating component 2 to rotate one revolution, and the laser rangefinder 2-3 records the distance dimensions at each moment. The clearance between the wheel tire and the landing gear wheel bay can be obtained by subtracting the fixed dimensions of the wheel tire after post-processing.

[0048] like Figure 5 As shown, for commonly used aircraft wheels and tires, it is only necessary to measure the clearance at 3 points to roughly obtain the clearance between the aircraft wheel / tire and the landing gear wheel well.

[0049] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A landing gear wheel well clearance measuring device, characterised in that, The device comprises a fixed component (1) and a rotating component (2), the fixed component (1) is fixedly installed on the outside of the hub shaft of the aircraft landing gear, the rotating component (2) is rotatably installed on the outside of the hub shaft of the aircraft landing gear, the fixed component (1) is provided with a motor assembly (1-2), the motor assembly (1-2) is connected and drives the rotating component (2) to rotate around the hub shaft of the aircraft landing gear; the rotating component (2) is provided with a support (2-5), and the distance measuring equipment is detachably installed on the support (2-5).

2. A landing gear wheel well clearance measuring device according to claim 1, characterised in that, The distance measuring equipment is a laser range finder (2-3).

3. A landing gear wheel well clearance measuring device according to claim 1, wherein, The support (2-5) is a cross-shaped structure, the top of the vertical support of the support (2-5) is flush with the outer circle of the tire of the landing gear of the aircraft, and the two ends of the horizontal support of the support (2-5) are flush with the two ends in the thickness direction of the tire of the landing gear of the aircraft.

4. A landing gear wheel well clearance measuring device according to claim 1, wherein, The distance measuring equipment is connected with the support (2-5) through a clamp (2-4), and the clamp (2-4) can be installed and fixed at any position of the support (2-5) and can be detached.

5. A landing gear wheel well clearance measuring device according to claim 1, wherein, The fixed component (1) further comprises a fixed base (1-1) connected with the hub shaft of the aircraft landing gear, the fixed base (1-1) is provided with a rotary electrical connector (1-3) at the end thereof outward along the hub shaft, one side of the fixed base (1-1) is connected with the motor assembly (1-2), and the other side of the fixed base (1-1) is provided with a power supply control assembly (1-4), and the power supply control assembly (1-4) is connected with the motor assembly (1-2) through an electrical control line.

6. A landing gear wheel well clearance measuring device according to claim 1, wherein, The rotating component (2) comprises a rotating base (2-1), and the rotating base (2-1) is provided with an external gear at the end thereof inward toward the hub shaft, and the external gear of the rotating base (2-1) is engaged with the output value of the motor assembly (1-2).

7. A landing gear wheel well clearance measuring device according to claim 6, characterised in that, The rotating component (2) is provided with at least two insertion slots, and the support (2-5) is inserted into one of the insertion slots in an interference manner.

8. A landing gear wheel well clearance measuring device according to claim 7, characterised in that, The rotating base (2-1) is further connected with an electrical connector (2-2), and the electrical connector (2-2) is electrically connected with the distance measuring equipment.

9. A landing gear wheel well clearance measuring device according to claim 8, characterised in that, The electrical connector (2-2) is connected with a metal strip in the insertion slot through a guide, the surface of the support (2-5) is provided with a groove, the groove is provided with a metal strip, and the metal strips on the two sides are connected after the support (2-5) is inserted into the insertion slot, and the distance measuring equipment is connected with the metal strips of the support (2-5) to complete the electrical connection.

10. A method of landing gear wheel well clearance measurement using a landing gear wheel well clearance measurement apparatus as claimed in any one of claims 1 to 9, characterised by, The device comprises the following steps: S1, the wheel on the landing gear is removed, the measuring equipment is installed on the hub shaft of the landing gear and fixed through a limiting nut; S2, at least one distance measuring equipment is installed on the support (2-5); S3, the motor assembly (1-2) is started to drive the rotating component (2) to rotate around the hub shaft for one revolution, and the distance measuring equipment records the distance parameters for one revolution; S4, the distance parameters recorded by the distance measuring equipment are input into a computer to obtain the clearance between the tire of the aircraft landing gear and the landing gear wheel cavity corresponding to the position of the distance measuring equipment; S5, the position of the distance measuring equipment on the support (2-5) is changed, and S3 and S4 are repeated to obtain the clearance between the tire of the aircraft landing gear and the landing gear wheel cavity at other positions.

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