Mounting structure of skid type undercarriage of multi-rotor aircraft

Abstract

The utility model discloses a mounting structure of a skid type undercarriage of a multi-rotor aircraft, which relates to the technical field of aircraft undercarriages, and is characterized by comprising a fuselage skin connected with a fuselage through rivets; the fuselage framework is arranged at the bottom of the fuselage and is wrapped in the fuselage skin; the undercarriage framework is arranged between the fuselage skin and the fuselage framework, and the two ends of the undercarriage framework penetrate out of the fuselage skin; the undercarriage is connected with the end, penetrating out of the fuselage skin, of the undercarriage framework; and the skid is connected with the end part, deviating from the undercarriage framework, of the undercarriage. The mounting structure of the skid type undercarriage of the multi-rotor aircraft has the advantage that the undercarriage can be conveniently disassembled and assembled without damaging the skin of the aircraft body.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft landing gears, and more specifically to an installation structure of a skid-type landing gear for a multi-rotor aircraft. Background Art

[0002] The landing gear is an accessory device at the lower part of an aircraft for supporting the aircraft during takeoff, landing or ground taxiing and for ground movement. For a helicopter, the landing gear is the only component that supports the entire aircraft. Therefore, it is an indispensable part of the aircraft. The landing gear of a helicopter provides support during takeoff and landing so that the aircraft can take off and land normally.

[0003] The existing Chinese patent with the publication number CN212047867U discloses an installation structure of an unmanned aircraft landing gear. The structure includes a U-shaped tube, a longitudinal fixing tube, a transverse fixing tube, a support tube, a shock pad, a connecting device and a shock spring. By providing the connecting device, the connecting device is connected to the unmanned aircraft through the threaded rod inside the connecting device. The fixing block inside the connecting device is connected to the landing gear through the connecting hole, and the connecting device can be disassembled up and down. A shock spring and a shock pad are also provided. The shock spring buffers the impact force generated when the unmanned aircraft descends, and the shock pad protects the landing gear, and the shock pad has a certain shock absorption effect.

[0004] Although the existing landing gear installation structure can install the landing gear, the overall landing gear is installed on the fuselage skin. When maintenance or disassembly is required, the fuselage skin will be damaged. And when selecting and applying materials for the fuselage skin, the overall integrity and stress performance need to be strictly controlled. When maintaining or disassembling the landing gear, the performance of the fuselage skin will be affected. Therefore, there is an urgent need for a landing gear that can be conveniently disassembled and assembled without damaging the fuselage skin. Content of the Utility Model

[0005] Aiming at the deficiencies of the existing technology, the purpose of the utility model is to provide an installation structure of a skid-type landing gear for a multi-rotor aircraft, which is convenient for disassembling and assembling the landing gear without damaging the fuselage skin.

[0006] To achieve the above purpose, the utility model provides the following technical solutions:

[0007] An installation structure of a skid-type landing gear for a multi-rotor aircraft, comprising:

[0008] A fuselage skin, which is connected to the airframe by rivets;

[0009] A fuselage frame, which is arranged at the bottom of the airframe and is covered inside the fuselage skin;

[0010] The landing gear framework is disposed between the fuselage skin and the fuselage framework, and both ends thereof penetrate out from the fuselage skin.

[0011] The landing gear is connected to the end of the landing gear framework that penetrates out of the fuselage skin.

[0012] The skid is connected to the end of the landing gear that is away from the landing gear framework.

[0013] As a further improvement of the present utility model, a docking groove is provided at the end of the landing gear framework. When the landing gear is connected to the landing gear framework, it is inserted into the docking groove. Mounting holes are respectively formed on the landing gear and the landing gear framework, and the mounting holes are used to provide mounting positioning when the landing gear and the landing gear framework are bolt-connected.

[0014] As a further improvement of the present utility model, it further includes a fairing, and the fairing is connected to the fuselage skin and covers the landing gear framework and the landing gear installation position.

[0015] As a further improvement of the present utility model, a bottom clearance of the fuselage is formed between the fuselage skin and the fuselage framework. The landing gear is fixedly arranged in the bottom clearance of the fuselage and is fixedly connected to the fuselage framework.

[0016] As a further improvement of the present utility model, a bent ear portion is formed at the end of the landing gear framework where the landing gear is connected.

[0017] The beneficial effects of the present utility model:

[0018] By providing a fuselage framework between the fuselage skin and the airframe, a bottom clearance for installing the landing gear framework is formed between the fuselage framework and the fuselage skin. The landing gear framework is fixedly connected to the fuselage framework, and both ends thereof respectively penetrate out from the fuselage skin. The part of the landing gear framework that penetrates out is connected to the landing gear, so that the fuselage skin will not be affected during the disassembly and assembly of the landing gear, thereby improving the integrity of the fuselage skin. A fairing is provided at the landing gear installation position, which not only forms a protection for the landing gear installation, but also can effectively reduce the air resistance at the landing gear, thereby improving the overall stability. Description of the Drawings

[0019] Figure 1 It is a three-dimensional structure schematic diagram of the overall installation structure of the present utility model;

[0020] Figure 2 It is a schematic diagram of the landing gear installation method.

[0021] Reference numerals: 1, fuselage skin; 2, fuselage framework; 3, fairing; 4, landing gear; 5, skid; 6, landing gear framework. Specific Embodiments

[0022] The present utility model will be further described in detail below in conjunction with the accompanying drawings and embodiments. The same components are denoted by the same reference numerals. It should be noted that the terms "front", "rear", "left", "right", "upper" and "lower" used in the following description refer to the directions in the accompanying drawings, and the terms "bottom surface" and "top surface", "inner" and "outer" respectively refer to the directions towards or away from the geometric center of a specific component.

[0023] Reference Figure 1 and Figure 2 As shown, a specific embodiment of the installation structure of a skid-type landing gear of a multi-rotor aircraft according to the present utility model includes a fuselage skin 1, a fuselage frame 2, a landing gear 4 and a skid 5. The fuselage skin 1 is connected to the fuselage by riveting and covers the outside of the fuselage. The fuselage frame 2 is arranged between the fuselage skin 1 and the bottom of the fuselage, so that a bottom clearance is formed between the fuselage skin 1 and the fuselage through the fuselage frame 2. A landing gear frame 6 is arranged in the bottom clearance. The landing gear frame 6 is horizontally arranged in the bottom clearance and both ends thereof pass through the bottom clearance and are connected and fixed to the fuselage frame 2. Both ends of the landing gear frame 6 passing through the bottom clearance are respectively connected to the landing gear 4. The landing gear frame 6 and the landing gear 4 are connected by bolts. Docking grooves are formed at both ends of the landing gear frame 6. When installing the landing gear 4, the landing gear 4 is inserted into the docking grooves. Mounting holes are respectively formed on the landing gear frame 6 and the landing gear 4. After the landing gear 4 is inserted into the docking grooves, the mounting holes on the landing gear 4 correspond to the mounting holes on the landing gear frame 6, so as to connect and fix the landing gear 4 and the landing gear frame 6 by bolts. One end of the landing gear 4 away from the landing gear frame 6 is connected to the skid 5. By providing the skid 5, support for the fuselage is formed when on the ground.

[0024] A fairing 3 is further arranged at the installation position of the landing gear 4 and the landing gear frame 6. The fairing 3 is used to cover the installation position of the landing gear 4 after the landing gear 4 and the landing gear frame 6 are installed. The fairing 3 is also connected to the fuselage skin 1, so as to achieve the purpose of protecting the installation position of the landing gear 4, and can also improve the support for the fuselage skin 1.

[0025] Working principle: When installing the landing gear 4, the whole fuselage is lifted off the ground, components such as the fairing 3 are removed, and installation components such as bolts are disassembled. At this time, without bolt connection, the landing gear 4 can be freely detached. During installation, the landing gear 4 is aligned with the docking grooves at the ends of the landing gear frame 6, and the position is determined to be correct through the mounting hole positions. After the position is appropriate, bolts are installed to fix the landing gear 4 and the landing gear frame 6. In practical applications, the disassembly and installation processes do not involve the disassembly of the fuselage skin 1. Also, because the landing gear 4 and the fuselage frame 2 are made into an integral body and the installation points of the landing gear 4 are on the outside, the shape continuity of the fuselage skin 1 is maintained.

[0026] The above are only the preferred embodiments of the present utility model, and the protection scope of the present utility model is not limited to the above embodiments. All technical solutions falling within the concept of the present utility model belong to the protection scope of the present utility model. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present utility model, several improvements and refinements should also be regarded as within the protection scope of the present utility model.

Claims

1. An installation structure of a skid landing gear for a multi-rotor aircraft, characterized in that, Comprising: The fuselage skin (1), and the fuselage skin (1) is connected to the airframe by rivets; The fuselage frame (2), and the fuselage frame (2) is disposed at the bottom of the airframe and is covered within the fuselage skin (1); The landing gear frame (6), and the landing gear frame (6) is disposed between the fuselage skin (1) and the fuselage frame (2), and both ends thereof penetrate out of the fuselage skin (1); The landing gear (4), and the landing gear (4) is connected to the end of the landing gear frame (6) that penetrates out of the fuselage skin (1); The skid (5), and the skid (5) is connected to the end of the landing gear (4) departing from the landing gear frame (6).

2. The installation structure of the skid landing gear of a multi-rotor aircraft according to claim 1, wherein: A docking groove is provided at the end of the landing gear frame (6). When the landing gear (4) is connected to the landing gear frame (6), it is inserted into the docking groove. Mounting holes are respectively formed on the landing gear (4) and the landing gear frame (6), and the mounting holes are used to provide mounting positioning when the landing gear (4) and the landing gear frame (6) are bolt-connected.

3. The installation structure of a skid-type landing gear for a multi-rotor aircraft according to claim 2, characterized in that: It further includes a fairing (3), and the fairing (3) is connected to the fuselage skin (1) and covers the installation positions of the landing gear frame (6) and the landing gear (4).

4. The installation structure of a skid-type landing gear for a multi-rotor aircraft according to claim 3, characterized in that: A bottom clearance is formed between the fuselage skin (1) and the fuselage frame (2). The landing gear (4) is fixedly disposed in the bottom clearance and is fixedly connected to the fuselage frame (2).

5. The installation structure of a skid landing gear for a multi-rotor aircraft according to claim 4, characterized in that: A bent ear portion is formed at the end of the landing gear frame (6) connecting the landing gear (4).

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