Undercarriage structure convenient to mount

Abstract

The utility model relates to the technical field of aircrafts, and discloses an undercarriage structure convenient to install, which comprises an outer fuselage and undercarriages arranged on the two sides of the outer fuselage, the outer fuselage comprises a bottom plate and side plates fixed on the two sides, a framework plate is arranged between the side plates on the two sides, and the framework plate is used for arranging an aircraft. Two stringers are further arranged in the cavity formed by the framework plate and the bottom plate, and the stringers are arranged on the two sides of the cavity. By adopting split type installation, the undercarriage can be suitable for different types under the condition that the outer diameters of undercarriage cross beams are consistent, and the problems that various undercarriage installation parts need to be reserved and funds are wasted due to the fact that existing undercarriage installation modes are not uniform are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a landing gear structure which is easy to install. Background Art

[0002] In daily life, short-distance transportation or passenger transport often uses ground transportation, such as buses, cars, trucks, etc. These modes of transportation are often restricted by ground roads and often experience traffic congestion; in terms of aircraft, manned aircraft are suitable for short-distance transportation and will be widely used and developed now and in the future.

[0003] During the use of aircraft, different landing gears will be used according to different scenarios and different models. However, the existing landing gear installation methods are not uniform, which leads to the need for multiple spare landing gear mounting parts, resulting in a waste of funds.

[0004] Therefore, we propose a landing gear structure that is easy to install to solve the above problems. Utility Model Content

[0005] (1) Technical problems solved

[0006] In response to the shortcomings of the existing technology, the utility model provides a landing gear structure that is easy to install. By adopting a split installation, it can be applied to different models under the condition that the outer diameter of the landing gear beam is consistent, thereby solving the problem that the existing landing gear installation method is not uniform, which leads to the need to spare multiple landing gear mounting parts and causes waste of funds.

[0007] (2) Technical solution

[0008] In order to achieve the above-mentioned purpose of improving battery replacement efficiency and installation efficiency, the present invention provides the following technical solutions: a landing gear structure that is easy to install, comprising an outer fuselage and landing gears arranged on both sides of the outer fuselage, the outer fuselage comprising a bottom plate and side plates fixed on both sides, a frame plate arranged between the side plates on both sides, the frame plate being used to arrange the aircraft, a long stringer is also arranged between the cavity formed by the frame plate and the bottom plate, there are two long strings, the long stringers are placed on both sides of the cavity, and multiple pairs of fixing brackets are also arranged on the long stringers, the long stringers are mainly used to improve the strength of the outer fuselage and provide installation for the fixing brackets, the fixing brackets are generally two pairs, and can also be three or four pairs, determined according to the quality and safety requirements of the aircraft, the fixing brackets are provided with a mounting hole 1 at the long stringer, the side plates are further provided with a mounting hole 2 corresponding to the mounting hole 1, and the mounting hole 2 corresponding to the mounting hole 1 is equal in size, the landing gears on both sides are inserted into the cavity through the mounting hole 1 and the mounting hole 2, and the ends of the landing gears on both sides located in the cavity are connected by a connecting pipe, and the connecting pipe and the landing gear are both hollow structures.

[0009] As an optimization of the present invention, the landing gear includes a front crossbeam and a rear crossbeam, and the front crossbeam and the rear crossbeam are respectively placed at the front and rear of the outer fuselage, and the bottoms of the front crossbeam and the rear crossbeam form a horizontal plane. By setting the front crossbeam and the rear crossbeam, the stability of the outer fuselage can be improved.

[0010] As an optimization of the present invention, the landing gear also includes a skid, which is connected by a front crossbeam and a rear crossbeam on the same side of the fixed ear piece. The skid is used to fix the position between the front crossbeam and the rear crossbeam to provide increased support force when the aircraft lands.

[0011] As an optimization of the present invention, an opening is opened at one end of the front cross beam and the rear cross beam located in the cavity, and a pin hole is opened at both ends of the connecting tube. Pins or screws are fixed to the connecting tube and the front cross beam and the rear cross beam through the opening and the pin hole. The outer wall of the connecting tube is equal to the inner wall of the front cross beam and the rear cross beam, or the inner wall of the connecting tube can be equal to the outer wall of the front cross beam and the rear cross beam.

[0012] As an optimization of the present invention, the bottom plate and the side panels are formed by integral bending, which can improve the stability of the outer fuselage, and reinforcing ribs can also be provided at the bending positions.

[0013] As an optimization of the present invention, the landing gear is one or more of a crossbeam, a sliding frame, and a buffer frame, and is used to provide landing for various types of aircraft.

[0014] (3) Beneficial effects

[0015] Compared with the prior art, the present invention provides a landing gear structure that is easy to install and has the following beneficial effects:

[0016] The utility model can realize the fixed installation of the landing gear by arranging the long stringer, the fixing bracket, the connecting pipe and other structures; can install and disassemble the parts of the landing gear by arranging the skid, the front crossbeam and the rear crossbeam; and can be applied to different models by adopting the split installation when the outer diameter of the landing gear crossbeam is consistent. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the three-dimensional structure of the utility model;

[0018] Figure 2 This is a schematic diagram of the front structure of the utility model.

[0019] In the figure: 1. outer fuselage; 2. frame plate; 3. long stringer; 4. fixed bracket; 5. landing gear; 51. front crossbeam; 52. rear crossbeam; 53. skid; 6. connecting pipe. DETAILED DESCRIPTION

[0020] 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.

[0021] See also Figure 1-2 The support frame 2 is provided with a plurality of support brackets 4 on the support frame 2, and a plurality of support brackets 4 are provided on the support frame 2.

[0022] The landing gear 5 includes a front crossbeam 51 and a rear crossbeam 52, which are respectively arranged at the front and rear of the outer fuselage. The bottoms of the front crossbeam 51 and the rear crossbeam 52 form a horizontal plane. By arranging the front crossbeam 51 and the rear crossbeam 52, the stability of the outer fuselage 1 can be improved; the landing gear 5 also includes a skid 53, which is connected by the front crossbeam 51 and the rear crossbeam 52 on the same side of the fixing lug, and the skid 53 is used to fix the position between the front crossbeam 51 and the rear crossbeam 52 to provide a support force when the aircraft lands; an opening is opened at one end of the front crossbeam 51 and the rear crossbeam 52 located in the cavity, and a pin hole is opened at both ends of the connecting pipe 6, and a pin or screw is fixed to the connecting pipe 6 and the front crossbeam 51 and the rear crossbeam 52 through the opening and the pin hole. The outer wall of the connecting pipe 6 is equal to the inner wall of the front crossbeam 51 and the rear crossbeam 52, or the inner wall of the connecting pipe 6 can be equal to the outer wall of the front crossbeam 51 and the rear crossbeam 52.

[0023] The bottom plate and both side panels are formed by integral bending, which can improve the stability of the outer fuselage 1. Reinforcing ribs can also be provided at the bending positions to enhance the strength of the outer fuselage 1. The landing gear 5 is one or more of a crossbeam, a sliding frame, and a buffer frame, and is used to provide landing for various types of aircraft.

[0024] Working principle: When installing the landing gear 5, first lift the entire machine off the ground, insert one end of the front crossbeam 51 and the rear crossbeam 52 into the cavity through the installation hole 1 and the installation hole 2, then put the connecting pipe 6 onto the front crossbeam 51 and the rear crossbeam 52, align the opening and the latch hole, and fix them with latches or screws to complete the installation of the landing gear 5. When the landing gear 5 needs to be disassembled, the landing gear 5 can be fixed and disassembled by removing the latches or screws. Because this installation method avoids large-scale damage to the outer fuselage skin, and the installation method is only through latch perforation without special structural mounting parts, it is suitable for most models. In addition, because all structures involved in the disassembly of the landing gear 5 are installed by latch perforation, the requirement of convenient disassembly is met.

[0025] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A landing gear structure that is easy to install, comprising an outer fuselage (1) and landing gears (5) arranged on both sides of the outer fuselage (1), characterized in that: The outer fuselage (1) includes a bottom plate and side plates fixed on both sides, a frame plate (2) is provided between the side plates on both sides, a long girder (3) is also provided between the cavity formed by the frame plate (2) and the bottom plate, the long girder (3) is placed on both sides of the cavity, a plurality of pairs of fixing brackets (4) are also provided on the long girder (3), a first mounting hole is provided on the fixing bracket (4) and the long girder (3), a second mounting hole corresponding to the first mounting hole is also provided on the side plate, the landing gear (5) on both sides is passed through the first mounting hole and the second mounting hole into the cavity, and one end of the landing gear (5) on both sides located in the cavity is connected by a connecting pipe.

2. The landing gear structure that is easy to install according to claim 1, characterized in that: The landing gear (5) comprises a front crossbeam (51) and a rear crossbeam (52), wherein the front crossbeam (51) and the rear crossbeam (52) are respectively arranged at the front and rear of the outer fuselage, and the bottoms of the front crossbeam (51) and the rear crossbeam (52) form a horizontal plane.

3. The landing gear structure that is easy to install according to claim 2, characterized in that: The landing gear (5) further comprises a skid (53), and the skid (53) is connected via a front crossbeam (51) and a rear crossbeam (52) on the same side of the fixed lug.

4. The landing gear structure that is easy to install according to claim 2, characterized in that: An opening is provided at one end of the front crossbeam (51) and the rear crossbeam (52) located in the cavity, and pin holes are provided at both ends of the connecting pipe (6). Pins or screws are passed through the opening and the pin holes to fix the connecting pipe (6) and the front crossbeam (51) and the rear crossbeam (52).

5. The landing gear structure that is easy to install according to claim 1, characterized in that: The bottom plate and the side plates on both sides are formed by integral bending.

6. The landing gear structure that is easy to install according to claim 1, characterized in that: The landing gear (5) is one or more of a crossbeam, a sliding frame, and a buffer frame.

Images