Aircraft nose landing gear turning pin and placing tool

Abstract

The utility model provides an airplane nose landing gear turning pin and a placing tool, and relates to the technical field of airplane ground operation and maintenance. The aircraft nose landing gear turning pin comprises a pin section, a connecting section and an extending section which are connected in sequence, and a shaft hole penetrating through the pin section, the connecting section and the extending section in the axial direction. The placement tool comprises: a support comprising a main body having a positioning structure; the opposite sides of the main body are respectively provided with at least one extending part extending along the transverse direction; a mounting hole is formed in the extension part and is used for connecting the main body with a turning mechanism of the nose landing gear of the airplane; and the fastening assembly is arranged at the main body and is used for detachably connecting the turning pin of the nose landing gear of the aircraft with the positioning structure. A bottom-to-top insertion mode is changed into a top-to-bottom insertion mode, so that the possibility that the turning pin of the nose landing gear of the airplane falls off and is lost is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft ground operation and maintenance, in particular to an aircraft front landing gear turning pin and a placing tool. Background Art

[0002] When towing an aircraft on the ground, the original turning pin must be inserted into the turning mechanism of the front landing gear to limit the turning range of the front wheels; after the aircraft is towed into place, the mechanic removes the turning pin and keeps it separately.

[0003] The original turning pin was placed in the turning mechanism from bottom to top, which may cause the turning pin to fall off and be lost suddenly. Utility Model Content

[0004] In view of the above situation, the utility model provides a front landing gear turning pin and a placement tool for an aircraft, aiming to solve the technical problem that the original method of placing the turning pin is to insert it into the turning mechanism from bottom to top, which may cause the turning pin to suddenly fall off and be lost.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] In a first aspect, the present invention provides a turning pin for a front landing gear of an aircraft, comprising a pin section, a connecting section, and an extending section connected in sequence, and an axial hole axially extending through the pin section, the connecting section, and the extending section;

[0007] The pin segment is used in conjunction with the turning mechanism of the aircraft's front landing gear;

[0008] The outer diameters of the pin section, the connecting section and the extending section decrease in sequence.

[0009] In some embodiments of the present invention, the connecting section has external threads.

[0010] In some embodiments of the present invention, the diameter of the shaft hole is 8.20 mm and the length is 130 mm; the outer diameter of the pin section is 16 mm and the length is 40 mm; the size of the external thread on the connecting section is M14.0 1.5mm, the length of the connecting section is 30mm; the outer diameter of the extension section is 12mm and the length is 60mm.

[0011] In a second aspect, the utility model provides a placement tool, comprising:

[0012] The bracket comprises a main body having a positioning structure; opposite sides of the main body each having at least one extension extending in a transverse direction; the extension having a mounting hole, the mounting hole being used to connect the main body to a turning mechanism of an aircraft's front landing gear;

[0013] A fastening assembly is arranged at the main body and is used for detachably connecting the turning pin of the front landing gear of the aircraft to the positioning structure.

[0014] In some embodiments of the present invention, the positioning structure is threadedly connected to the connecting section.

[0015] In some embodiments of the present invention, the positioning structure includes a positioning hole, and the pin segment can pass through the positioning hole.

[0016] In some embodiments of the present invention, the fastening assembly includes at least two fastening nuts threadedly connected to the connecting section, and the fastening nuts are distributed on opposite sides of the main body.

[0017] In some embodiments of the present invention, the main body is arched.

[0018] In some embodiments of the present invention, the main body includes a first vertical portion, a flat portion, and a second vertical portion connected in sequence.

[0019] In some embodiments of the present invention, the first vertical portion, the straight portion, and the second vertical portion are sequentially connected in a smooth transition.

[0020] The embodiments of the present invention have at least the following advantages or beneficial effects:

[0021] First, by setting up the placement tool, the aircraft nose landing gear turning pin can be connected to the aircraft nose landing gear turning mechanism from top to bottom, that is, the bottom-up insertion method is changed to a top-down insertion method, thereby reducing the possibility of the aircraft nose landing gear turning pin falling off or losing.

[0022] Second, the shape of the bracket is simple and easy to manufacture; the bracket can be fastened to the turning mechanism of the front landing gear of the aircraft using the original bolts and holes, and the installation is easy.

[0023] 3. The shaft hole is arranged so that the turning pin of the front landing gear of the aircraft does not hinder the disassembly and assembly of the safety pin.

[0024] 4. The extension replaces the gasket.

[0025] Other features and advantages of the present invention will be set forth in the following description, and in part will become apparent from the description, or may be understood by practicing the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 This is a schematic diagram showing the position of the turning mechanism of the front landing gear of the aircraft;

[0028] Figure 2 This is a schematic structural diagram of a turning mechanism for a front landing gear of an aircraft in the prior art;

[0029] Figure 3 This is a structural diagram of the turning pin of the aircraft's front landing gear;

[0030] Figure 4 Assembly drawings for placing tools and the aircraft's nose landing gear turning pin;

[0031] Figure 5 Schematic diagram of the structure of the bracket.

[0032] icon:

[0033] 1- turning mechanism of the front landing gear of the aircraft, 11- first through hole, 12- second through hole, 13- bolt, 14- gasket,

[0034] 2-aircraft front landing gear turning pin, 21-pin section, 22-connecting section, 23-extension section, 24-axis hole,

[0035] 3-bracket, 31-main body, 311-first vertical portion, 312-straight portion, 313-second vertical portion, 32-positioning hole, 33-extension portion, 331-mounting hole,

[0036] 41-Tighten the nut. DETAILED DESCRIPTION

[0037] In the following, only certain exemplary embodiments are briefly described. As those skilled in the art will appreciate, the described embodiments may be modified in various different ways without departing from the spirit or scope of the embodiments of the present invention.

[0038] In the description of the embodiments of the present invention, it should be understood that the terms "vertical", "top", "inside", "outside", "axial", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention 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 cannot be understood as a limitation on the embodiments of the present invention.

[0039] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the embodiments of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0040] In the embodiments of the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connected," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; they can refer to direct connection or indirect connection through an intermediate medium; they can refer to internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on specific circumstances.

[0041] The embodiments of the present utility model are described in detail below.

[0042] First, see Figure 1~Figure 2 , first, the turning mechanism and turning pin (not shown in the figure) of the existing aircraft front landing gear are further introduced to better understand the placement tool to be introduced below.

[0043] See also Figure 2 The top of the turning mechanism of the front landing gear of the aircraft is provided with two first through holes arranged at intervals, and a second through hole is provided between the two first through holes.

[0044] Two bolts for assembling corresponding components pass through the first through holes from top to bottom respectively, and gaskets used in conjunction with the bolts are sleeved on the upper parts of the bolts.

[0045] The turning pin is provided with a through hole penetrating through both ends of the turning pin along the axial direction.

[0046] When towing an aircraft on the ground, the original turning pin needs to be passed through the second through hole from bottom to top, and then the safety pin used in conjunction with it (not shown in the figure, this application has not made any improvements to the safety pin) needs to be passed vertically through the turning pin to cooperate with other components; only after completing these preparatory work can the aircraft be towed.

[0047] Second, see Figures 1 to 5 The present application provides a turning pin for a front landing gear of an aircraft, comprising a pin section, a connecting section and an extending section coaxially connected in sequence, and an axial hole axially passing through the pin section, the connecting section and the extending section.

[0048] The outer diameters of the pin section, the connecting section and the extending section decrease in sequence. The outer diameter of the pin section is smaller than the diameter of the second through hole. The connecting section is provided with an external thread. The safety pin can pass through the shaft hole.

[0049] The diameter of the shaft hole is 8.20mm and the length is 130mm; the outer diameter of the pin section is 16mm and the length is 40mm; the size of the external thread on the connecting section is M14.0 The outer diameter of the extension section is 12mm and the length is 60mm.

[0050] The nose landing gear turning pins of the above aircraft are different from the original turning pins to adapt to the placement tool described below.

[0051] Thirdly, see Figures 1 to 5 , the present application provides a placement tool, including a bracket and a fastening assembly.

[0052] The bracket includes a main body, which has a positioning structure; opposite sides of the main body respectively have at least one extension portion extending in the transverse direction, and the length of the extension portion is set as needed; the extension portion has a mounting hole, each mounting hole can be aligned with a first through hole, and the bolt can pass through the mounting hole and the first through hole from top to bottom.

[0053] The fastening assembly is arranged at the main body and is used for detachably connecting the connecting section with the positioning structure, thereby fastening the turning pin of the front landing gear of the aircraft to the bracket.

[0054] To install the tool, remove and retain the two bolts, remove the two washers, and assemble the bracket with the nose landing gear turning pin. Insert the pin segment of the nose landing gear turning pin from top to bottom through the second through-hole, aligning the mounting hole on the bracket's extension with the first through-hole. Insert the bolts from top to bottom through the mounting hole and the first through-hole. This allows the bracket to be secured to the nose landing gear turning mechanism using the existing bolt and hole positions. Make any necessary adjustments and insert the safety pin through the shaft hole, ensuring the nose landing gear turning pin does not interfere with the safety pin's removal and installation.

[0055] The specific implementation of the placement tool will be described below with examples.

[0056] Example 1

[0057] See also Figures 1 to 5In this embodiment, the positioning structure includes a positioning hole, through which the pin segment and the connecting segment can pass; the fastening assembly includes at least two fastening nuts threadedly connected to the connecting segment, and these fastening nuts are distributed on opposite sides (upper and lower sides) of the main body, so that the connecting segment can be easily connected to the main body through these fastening nuts.

[0058] In other embodiments, the main body and the connecting section may be connected by methods other than threaded connection.

[0059] Example 2

[0060] See also Figures 1 to 5 In this embodiment, the main body is in an arched shape. In a specific implementation scenario, the main body includes a first vertical portion, a straight portion, and a second vertical portion that are smoothly connected in sequence. The first vertical portion and the second vertical portion are both connected to an extension portion extending in opposite directions. The mounting hole is on the extension portion, and the positioning hole is on the straight portion.

[0061] In other implementation scenarios, the extension directions of the first vertical portion and the second vertical portion may be the same.

[0062] In combination with the above, the above-mentioned aircraft nose landing gear turning pin and placement tool have at least the following advantages:

[0063] First, by redesigning the nose landing gear turning pin and adding a placement tool, the pin can be connected to the nose landing gear turning mechanism from top to bottom. In other words, the insertion method is changed from bottom to top, reducing the possibility of the pin falling off or being lost.

[0064] Second, the shape of the bracket is simple and easy to manufacture; the bracket can be fastened to the turning mechanism of the front landing gear of the aircraft using the original bolts and holes, and the installation is easy.

[0065] 3. The shaft hole is arranged so that the turning pin of the front landing gear of the aircraft does not hinder the disassembly and assembly of the safety pin.

[0066] 4. The extension replaces the gasket.

[0067] Finally, it should be noted that the above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Those skilled in the art will appreciate that the present invention is susceptible to various modifications and variations. The embodiments and features of the embodiments of this application may be combined arbitrarily without conflict. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A turning pin for an aircraft nose landing gear, characterized in that: It comprises a pin section, a connecting section and an extending section connected in sequence, and an axial hole axially passing through the pin section, the connecting section and the extending section; The pin segment is used in conjunction with the turning mechanism of the aircraft's front landing gear; The outer diameters of the pin section, the connecting section and the extending section decrease in sequence.

2. The aircraft nose landing gear turning pin according to claim 1, characterized in that: The connecting section is provided with external threads.

3. The aircraft nose landing gear turning pin according to claim 2, characterized in that: The diameter of the shaft hole is 8.20mm and the length is 130mm; the outer diameter of the pin section is 16mm and the length is 40mm; the size of the external thread on the connecting section is M14.0 1.5mm, the length of the connecting section is 30mm; the outer diameter of the extension section is 12mm and the length is 60mm.

4. A placement tool, characterized in that: include: The bracket comprises a main body having a positioning structure; opposite sides of the main body each having at least one extension extending in a transverse direction; the extension having a mounting hole, the mounting hole being used to connect the main body to a turning mechanism of an aircraft's front landing gear; A fastening assembly is provided at the main body and is used to detachably connect the aircraft nose landing gear turning pin according to claim 1 to the positioning structure.

5. The placement tool according to claim 4, characterized in that The positioning structure is threadedly connected to the connecting section.

6. The placement tool according to claim 5, characterized in that The positioning structure includes a positioning hole, and the pin segment can pass through the positioning hole.

7. The placement tool according to claim 6, characterized in that The fastening assembly includes at least two fastening nuts threadedly connected to the connecting section, and the fastening nuts are distributed on opposite sides of the main body.

8. The placement tool according to any one of claims 4 to 7, characterized in that: The main body is arched.

9. The placement tool according to claim 8, characterized in that The main body includes a first vertical portion, a flat portion and a second vertical portion connected in sequence.

10. The placement tool according to claim 9, characterized in that The first vertical portion, the straight portion and the second vertical portion are connected in sequence with smooth transition.

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