Winding forming composite material plate spring type undercarriage

Abstract

The utility model discloses a composite material plate spring type undercarriage formed by winding, which belongs to the technical field of undercarriages and comprises an undercarriage main body, a butt joint hoop is mounted on the undercarriage main body and clamped on an external fuselage, and a fuselage connecting pin is mounted in the middle of the undercarriage main body. One end of the fuselage connecting pin is connected with an external fuselage, the two ends of the undercarriage body are fixedly provided with the airplane wheel connecting metal connectors, the airplane wheel connecting metal connectors are provided with connecting holes, the external airplane wheel is installed on the airplane wheel connecting metal connectors through the connecting holes, and the external airplane wheel is installed on the airplane wheel connecting metal connectors. The undercarriage body is manufactured by winding the carbon fiber prepreg on the aluminum alloy pipe, the aluminum alloy pipe is manufactured in a 3D printing mode, the undercarriage body is manufactured by winding the carbon fiber prepreg on the aluminum alloy pipe, production is facilitated, meanwhile, the thickness of the carbon fiber prepreg can be determined according to strength calculation, and therefore the safety degree is improved.

Description

Technical Field

[0001] The utility model relates to a winding-molded composite material leaf spring type landing gear, belonging to the technical field of landing gears. Background Art

[0002] Leaf spring landing gear has a simple structure, high reliability, low cost and simple maintenance, and has always been favored by small aircraft and small drones. With the rapid development of small aircraft and drones, lightweight, compact space and low overload of landing gear have become important requirements of modern small aircraft. Usually, for leaf spring landing gear, under the same sinking speed, the overload of the aircraft is mainly adjusted by the deformation of the landing gear. At the same sinking speed, the smaller the overload, the greater the deformation is required to ensure it. The leaf spring landing gear is mainly adjusted by the deformation of the leaf spring structure. The load it bears and its deformation affect each other. For example, the publication number is CN208306979U, an aircraft main landing gear, which is a tube spring landing gear, including a tube spring main strut, a bushing, an axle, a wheel, a tire and a mounting bracket. A fairing on a tubular spring main strut, one end of which is connected to a tire via an axle and a wheel, and the other end is connected to the fuselage, the bushing being mounted on the tubular spring main strut and close to the fuselage, the tubular spring main strut being insertable into a mounting hole of a mounting bracket under the fuselage floor and being fixed in the mounting hole by bolts, the tubular spring main strut and the bushing mounted on the tubular spring main strut jointly reducing and absorbing the impact energy generated by the aircraft contacting the ground during takeoff, landing, and taxiing, thereby effectively alleviating the aircraft's bumping and shaking, however, the above-mentioned leaf spring landing gear adopts a metal structure, which has a heavy structural weight and a high machining cost. In view of this, the present invention is proposed. Utility Model Content

[0003] The purpose of the present invention is to provide a winding-molded composite leaf spring landing gear in order to solve the above-mentioned problems. The landing gear has the advantages of simple structure, light weight, low price, and no need for demoulding. The landing gear body is made by winding carbon fiber prepreg on an aluminum alloy tube. Compared with metal leaf spring landing gear, the weight is significantly reduced, the production is convenient, and the thickness of the carbon fiber prepreg can be determined according to strength calculation, thereby improving the safety level. At the same time, the utility model has strong adaptability and is suitable for small and medium-sized aircraft. The shape of the landing gear can be changed as needed, and it is easy to modify and has strong versatility.

[0004] The present invention achieves the above-mentioned object through the following technical scheme: a winding-molded composite leaf spring landing gear, comprising a landing gear body, a butt joint clamp installed on the landing gear body, the butt joint clamp being clamped on the external fuselage, and a fuselage connecting pin being installed in the middle position of the landing gear body, one end of the fuselage connecting pin being connected to the external fuselage, and wheel connecting metal joints being fixedly installed at both ends of the landing gear body, and external wheels being mounted on the wheel connecting metal joints. When in use, the butt joint clamp is first installed on the landing gear body, and then the landing gear body is clamped on the fuselage connecting frame through the butt joint clamp, and then reinforced through the fuselage connecting pin, and then the wheels are mounted on the wheel connecting metal joints.

[0005] Preferably, in order to improve the strength of the landing gear body and facilitate production, the landing gear body is made of carbon fiber prepreg wound on an aluminum alloy tube, and the aluminum alloy tube is made by 3D printing.

[0006] Preferably, in order to be able to install the butt joint clamp on the landing gear body and facilitate the installation of the landing gear body, the butt joint clamp includes an upper annular clamp and a lower annular clamp, and connecting bolts are installed on both sides of the upper end of the upper annular clamp, and the other end of the connecting bolts extends to the lower end of the lower annular clamp.

[0007] Preferably, in order to connect and fix the upper annular clamp and the lower annular clamp, a connecting nut is threadedly installed on the lower end of the connecting bolt, and the connecting nut is located on both sides of the lower end of the lower annular clamp.

[0008] Preferably, in order to facilitate the connection between the butt joint clamp and the external fuselage connection frame, two ears are fixedly installed on both sides of the upper end of the upper annular clamp, and the two ears are connected to the external fuselage connection frame.

[0009] Preferably, in order to connect the landing gear body to the fuselage, a mounting hole is provided in the middle of the landing gear body, and the fuselage connecting pin is installed in the mounting hole.

[0010] Preferably, in order to enable the wheel to be mounted on the wheel connecting metal joint, a connecting hole is provided on the wheel connecting metal joint, and the external wheel is mounted on the wheel connecting metal joint through the connecting hole.

[0011] The beneficial effects of the present invention are as follows: the landing gear body is made by winding carbon fiber prepreg around an aluminum alloy tube, which significantly reduces weight compared to metal leaf spring landing gear, facilitates production, and can determine the thickness of the carbon fiber prepreg based on strength calculations, thereby improving safety. At the same time, the utility model has strong adaptability and is suitable for small and medium-sized aircraft. The shape of the landing gear can be changed as needed, is easy to modify, and has strong versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0013] Figure 2 It is a structural schematic diagram of the landing gear main body in the utility model.

[0014] Figure 3 It is a structural schematic diagram of the butt joint clamp in the utility model.

[0015] In the figure: 1. Landing gear body; 2. Butt joint clamp; 201. Upper annular clamp; 202. Lower annular clamp; 203. Connecting bolt; 204. Connecting nut; 205. Double ears; 3. Fuselage connecting pin; 4. Wheel connecting metal joint; 5. Mounting hole; 6. Connecting hole. DETAILED DESCRIPTION

[0016] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0017] See also Figure 1-3 As shown, a winding-molded composite leaf spring landing gear includes a landing gear body 1, a butt joint clamp 2 is installed on the landing gear body 1, the butt joint clamp 2 is clamped to the external fuselage, and a fuselage connecting pin 3 is installed in the middle position of the landing gear body 1, one end of the fuselage connecting pin 3 is connected to the external fuselage, and wheel connecting metal joints 4 are fixedly installed at both ends of the landing gear body 1, and the external wheel is installed on the wheel connecting metal joint 4. When in use, the butt joint clamp 2 is first installed on the landing gear body 1, and then the landing gear body 1 is clamped to the fuselage connection frame through the butt joint clamp 2, and then reinforced by the fuselage connecting pin 3, and then the wheel is installed on the wheel connecting metal joint 4.

[0018] like Figure 3As shown, the landing gear body 1 is made of carbon fiber prepreg wound on an aluminum alloy tube, and the aluminum alloy tube is made by 3D printing. The butt joint clamp 2 includes an upper annular clamp 201 and a lower annular clamp 202. Connecting bolts 203 are installed on both sides of the upper end of the upper annular clamp 201. The other end of the connecting bolt 203 extends to the lower end of the lower annular clamp 202. The lower end of the connecting bolt 203 is threadedly installed with a connecting nut 204. The connecting nut 204 is located on both sides of the lower end of the lower annular clamp 202. Two ears 205 are fixedly installed on both sides of the upper end of 201, and the two ears 205 are connected to the external fuselage connection frame. When in use, the upper annular clamp 201 and the lower annular clamp 202 are first sleeved on the landing gear body 1, and then the upper annular clamp 201 and the lower annular clamp 202 are connected by connecting bolts 203 and connecting nuts 204, so that the upper annular clamp 201 and the lower annular clamp 202 can be clamped to the landing gear body 1. Then, the landing gear body 1 is clamped to the external fuselage connection frame through the two ears 205.

[0019] like Figure 1 As shown, a mounting hole 5 is provided in the middle of the landing gear body 1 , and a fuselage connecting pin 3 is installed in the mounting hole 5 . When in use, the landing gear body 1 and the fuselage are connected via the fuselage connecting pin 3 .

[0020] like Figure 1 As shown, a connection hole 6 is opened on the wheel connection metal joint 4, and the external wheel is installed on the wheel connection metal joint 4 through the connection hole 6. When in use, the wheel is installed on the wheel connection metal joint 4 through the connection hole 6.

[0021] When the present invention is in use, the upper annular clamp 201 and the lower annular clamp 202 are first sleeved on the landing gear body 1, and then the upper annular clamp 201 and the lower annular clamp 202 are connected by the connecting bolt 203 and the connecting nut 204, so that the upper annular clamp 201 and the lower annular clamp 202 can be clamped on the landing gear body 1, and then the landing gear body 1 is clamped on the external fuselage connection frame through the double ears 205, and the landing gear body 1 and the fuselage are connected by the fuselage connection pin 3, and the wheel is installed on the wheel connection metal joint 4 through the connection hole 6.

[0022] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the present invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be encompassed within the present invention. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0023] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A spiral wound composite leaf spring landing gear, characterized by: The invention comprises a landing gear body (1), a docking joint clamp (2) is installed on the landing gear body (1), the docking joint clamp (2) is clamped on the external fuselage, and a fuselage connection pin (3) is installed in the middle position of the landing gear body (1), one end of the fuselage connection pin (3) is connected to the external fuselage, and wheel connection metal joints (4) are fixedly installed at both ends of the landing gear body (1), and the external wheel is installed on the wheel connection metal joint (4).

2. The filament winding composite leaf spring landing gear according to claim 1, characterized in that: The landing gear body (1) is made of carbon fiber prepreg wound on an aluminum alloy tube, and the aluminum alloy tube is made by 3D printing.

3. The spiral wound composite leaf spring landing gear according to claim 1, characterized in that: The butt joint clamp (2) comprises an upper annular clamp (201) and a lower annular clamp (202), wherein connecting bolts (203) are installed on both sides of the upper end of the upper annular clamp (201), and the other end of the connecting bolts (203) extends to the lower end of the lower annular clamp (202).

4. The spiral wound composite leaf spring landing gear according to claim 3, characterized in that: The lower end of the connecting bolt (203) is threadedly mounted with a connecting nut (204), and the connecting nut (204) is located on both sides of the lower end of the lower annular clamp (202).

5. The winding composite leaf spring landing gear according to claim 4, characterized in that: Two ears (205) are fixedly mounted on both sides of the upper end of the upper annular clamp (201), and the two ears (205) are connected to the external fuselage connection frame.

6. The spiral wound composite leaf spring landing gear according to claim 1, characterized in that: A mounting hole (5) is provided in the middle of the landing gear body (1), and the fuselage connecting pin (3) is mounted in the mounting hole (5).

7. The spiral wound composite leaf spring landing gear according to claim 1, characterized in that: The wheel connection metal joint (4) is provided with a connection hole (6), and the external wheel is mounted on the wheel connection metal joint (4) through the connection hole (6).

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