Main landing gear structure of airplane

Abstract

The utility model is applicable to the technical field of aircraft parts, discloses a main landing gear structure of an aircraft, and aims to solve the technical problem that the taxiing distance of the aircraft is longer due to smaller wind resistance of the aircraft in the prior art. The utility model provides an aircraft main landing gear structure which comprises an aircraft body, an inner support and an outer support, the inner support is installed inside the aircraft body, the outer support is fixed on the outer side of the aircraft body, and the outer support is divided into a main landing gear plate and a main landing gear inner frame. Wherein the two sides of the main landing inner frame are movably connected with the main landing gear plate through bolts, and the main landing inner frame is fixed to the fuselage. Pressure on the fuselage can be shared on the fixed side frames on the two sides through supporting of the fixed side frames on the two sides; damage to the joint of the main landing gear plate and the main landing gear inner frame is effectively reduced, and the service life of the main landing gear plate and the main landing gear inner frame is prolonged.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft parts, and in particular to an aircraft main landing gear structure. Background Technology

[0002] Landing gear is an important component of an aircraft that provides load-bearing capacity and ground steering control. It is an essential support system for aircraft takeoff, landing, taxiing, ground movement, and parking. It can withstand the impact load during landing and smoothly absorb collision energy.

[0003] Currently, most aircraft on the market use main landing gear. During takeoff, landing, or taxiing, the aircraft experiences a significant impact from contact with the ground, resulting in a large load. Consequently, the main landing gear connection points bear considerable force, causing significant damage. Because aircraft need to reduce wind resistance during flight, they are designed with special streamlines. To further reduce wind resistance, during taxiing, the lower wind resistance causes the aircraft to taxi a longer distance, making it difficult to stop in time. Summary of the Invention

[0004] The purpose of this utility model is to overcome the shortcomings of the prior art and provide an aircraft main landing gear structure, which aims to solve the technical problem that the aircraft has low wind resistance and therefore a long taxiing distance.

[0005] To achieve the above objectives, this utility model proposes an aircraft main landing gear structure, including a fuselage, an inner support, and an outer support. The inner support is installed inside the fuselage, and the outer support is fixed to the outside of the fuselage.

[0006] The outer support is divided into two parts: the main landing gear plate and the main landing gear inner frame. The main landing gear plate is movably connected to both sides of the main landing gear inner frame by bolts. The main landing gear inner frame is fixed to the fuselage. A wheel hub brake assembly is installed at the bottom of the main landing gear plate. A fixed side frame is also fixed to the main landing gear plate to increase the stability of the outer support.

[0007] Preferably, the fixed side frame and the main landing gear plate are fixed together to the inner frame of the main landing gear with bolts, and the interior of the fixed side frame is hollow.

[0008] Preferably, the main landing gear plate and the main landing gear inner frame are slidably connected, wherein the two end faces of the main landing gear inner frame are respectively provided with an outer groove and an inner groove, the main landing gear plate slides in the inner groove, and the outer groove and the inner groove are connected by a sliding hole.

[0009] As preferred, the both side end faces of the outer groove are rotationally connected with a baffle, a torsion spring is used on the rotation axis of the baffle, and a plurality of main opening blocks are fixed on the one side end face of the baffle and arranged in a semi-arc shape.

[0010] As preferred, a connecting protrusion is fixed on the end face of the main landing gear plate, the connecting protrusion slides in the sliding hole, a connecting plate is arranged in the outer groove, the connecting plate is fixed on the connecting protrusion through bolts, a plurality of auxiliary opening blocks are fixed on the one side edge of the connecting plate and arranged in a semi-arc shape.

[0011] Compared with the prior art, the aircraft main landing gear structure has the following beneficial effects:

[0012] 1. The pressure on the fuselage can be distributed on the two fixed side frames through the support of the two fixed side frames, so that the damage to the connection between the main landing gear plate and the main landing inner frame is effectively reduced, and the service life is prolonged.

[0013] 2. The aircraft can be quickly stopped and the sliding distance is shortened during the sliding process of the fuselage landing through the additional wind resistance of the baffle.

[0014] The features and advantages of the present application will be described in detail with reference to the embodiments and the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 is a perspective view of the embodiment of the present application.

[0016] Figure 2 is a perspective view of the support of the embodiment of the present application.

[0017] Figure 3 is a sectional view of the connection of the present application

[0018] Figure 4 is an exploded view of the connection of the present application.

[0019] Among them:

[0020] 10-fuselage; 11-inner support; 12-main landing gear plate; 13-hub brake group; 14-main landing inner frame; 15-fixed side frame; 16-bolt; 17-baffle; 18-connecting plate; 19-sliding hole; 20-outer groove; 21-inner groove; 22-main opening block; 23-auxiliary opening block; 24-connecting protrusion. DETAILED DESCRIPTION

[0021] To make the purpose, technical scheme and advantages of the present application more clear, specific embodiments will be further described in detail below with reference to the drawings. However, it should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the scope of the present application. In addition, in the following description, the description of known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present application.

[0022] In the description of the present application, it should be noted that when an element is referred to as "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0023] In the description of the present application, it should be noted that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship when the product is used. It is only for the convenience of describing the present application and simplifying the description, and is not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third", etc. are only used for differentiation and cannot be understood as indicating or implying relative importance. Therefore, the features limited by "first" and "second" can explicitly or implicitly include one or more of the features. In the description of the present application, "a plurality of" means two or more, unless otherwise specifically limited. "Several" means one or more, unless otherwise specifically limited.

[0024] In the description of the present application, it should be noted that, unless otherwise specifically defined and limited, the terms "set", "mount", "connected", "connected" should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances. Embodiment one

[0025] Reference Figure 1 and Figure 2The utility model embodiment provides a kind of aircraft main landing gear structure, including fuselage 10, inner support 11 and outer support, inner support 11 is installed in the inside of fuselage 10, outer support is fixed in the outside of fuselage 10, outer support is divided into main landing gear plate 12 and main landing inner frame 14 two parts, wherein the two sides of main landing inner frame 14 are movably connected with main landing gear plate 12 by bolt 16, main landing inner frame 14 is fixed on fuselage 10, the bottom of main landing gear plate 12 is equipped with wheel hub brake set 13, main landing gear plate 12 is also equipped with fixed side frame 15, the stability of outer support is increased by fixed side frame 15, fixed side frame 15 and main landing gear plate 12 are fixed on main landing inner frame 14 by bolt 16, and the inside of fixed side frame 15 is hollowly arranged, and its side is arc-shaped arrangement, so that it is more fitted to the surface of fuselage 10.

[0026] The utility model embodiment can be supported by the fixed side frame 15 of both sides, and the pressure on the fuselage 10 is distributed on the fixed side frame 15 on both sides, so that the damage to the connection between the main landing gear plate 12 and the main landing inner frame 14 is effectively reduced, and the service life is prolonged. Embodiment two

[0027] Refer to Figure 3 And Figure 4 In the embodiment, the main landing gear plate 12 and the main landing inner frame 14 are also in sliding connection, wherein the two side end faces of the main landing inner frame 14 are respectively provided with an outer groove 20 and an inner groove 21, the main landing gear plate 12 slides in the inner groove 21, the outer groove 20 and the inner groove 21 are communicated through a sliding hole 19, the two side end faces of the outer groove 20 are rotatably connected with a baffle 17, a torsional spring is used on the rotating shaft of the baffle 17, and a plurality of main opening blocks 22 are further fixed on one side end face of the baffle 17, and the main opening blocks 22 are semi-arc-shaped.

[0028] A connecting lug 24 is fixed on the end face of the main landing gear plate 12, the connecting lug 24 slides in the sliding hole 19, a connecting plate 18 is further arranged in the outer groove 20, the connecting plate 18 is fixed on the connecting lug 24 through the bolt 16, a plurality of secondary opening blocks 23 are fixed on one side edge of the connecting plate 18, and the secondary opening blocks 23 are semi-arc-shaped, wherein the secondary opening blocks 23 and the main opening blocks 22 are staggered.

[0029] In use, when the fuselage 10 is in the air, the torsion spring on the baffle 17 drives the baffle 17 to tightly adhere to the inside of the outer groove 20, at this time the wind resistance is not affected, when the fuselage 10 lands, through the weight of the fuselage 10 itself, the main landing inner frame 14 is pressed downward, the main landing gear plate 12 moves close to the main landing inner frame 14, the connecting block 24 and the connecting plate 18 are driven to move close to the main landing inner frame 14, at this time the auxiliary opening block 23 on the connecting plate 18 abuts against the main opening block 22, the baffle 17 is opened through the arc-shaped setting, at this time the baffle 17 opens a certain gap, in the process of moving of the fuselage 10, the wind resistance blows the baffle 17 to continue to rotate, until it is in the vertical state, at this time the maximum wind resistance is reached, so through the wind resistance of the baffle 17, in the process of landing of the fuselage 10, it can be quickly stopped, the sliding distance is shortened, and when there is no need to slide or in the air, the baffle 17 is tightly closed to the outer groove 20 through the elastic force of the torsion spring, it cannot be opened.

[0030] The above merely describes the preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement or improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft main landing gear structure comprising a fuselage (10), an inner support (11) and an outer support; characterized in that: The inner support (11) is installed inside the fuselage (10), and the outer support is fixed outside the fuselage (10); The outer support is divided into a main landing gear plate (12) and a main landing gear inner frame (14), wherein the main landing gear plate (12) is movably connected to the two sides of the main landing gear inner frame (14) through bolts (16), the main landing gear inner frame (14) is fixed on the fuselage (10), the bottom of the main landing gear plate (12) is provided with a hub brake group (13), and a fixed side frame (15) is further fixed on the main landing gear plate (12) to increase the stability of the outer support.

2. An aircraft main landing gear structure as claimed in claim 1, characterised in that: The fixed side frame (15) and the main landing gear plate (12) are fixed on the main landing gear inner frame (14) through bolts (16), and the fixed side frame (15) is hollow inside.

3. An aircraft main landing gear structure as claimed in claim 1, characterised in that: The main landing gear plate (12) and the main landing gear inner frame (14) are further connected in a sliding mode, wherein the two side end faces of the main landing gear inner frame (14) are respectively provided with an outer groove (20) and an inner groove (21), the main landing gear plate (12) slides in the inner groove (21), and the outer groove (20) and the inner groove (21) are communicated through a sliding hole (19).

4. An aircraft main landing gear structure as claimed in claim 3, characterised in that: The two side end faces of the outer groove (20) are rotatably connected with baffle plates (17), torsional springs are arranged on the rotating shafts of the baffle plates (17), and a plurality of main opening blocks (22) are further fixed on one side end face of each baffle plate (17).

5. An aircraft main landing gear structure as claimed in claim 3, characterised in that: The end face of the main landing gear plate (12) is fixed with a connecting protrusion (24), the connecting protrusion (24) slides in the sliding hole (19), a connecting plate (18) is further arranged in the outer groove (20), the connecting plate (18) is fixed on the connecting protrusion (24) through bolts (16), a plurality of secondary opening blocks (23) are fixed on one side edge of the connecting plate (18), and the secondary opening blocks (23) are arranged in a semicircular mode.

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