Fixed-wing aircraft undercarriage structure

Abstract

The utility model discloses an undercarriage structure of a fixed-wing aircraft, which comprises a middle fuselage and a fuselage consisting of an upper fuselage and a lower fuselage which are positioned at the upper end and the lower end of the middle fuselage, and is characterized in that a fuselage diagonal bracing plate I and a fuselage diagonal bracing plate II which are connected with the middle fuselage are symmetrically arranged on two sides of the lower fuselage; a first fixing support and a second fixing support which are symmetrically arranged are arranged on the sides, away from each other, of the first machine body inclined supporting plate and the second machine body inclined supporting plate. The cross section of the undercarriage is square, and the corner angles of the square are consistent with the flight landing direction, so that the take-off and landing overload capacity of the undercarriage is improved; a buckling position is arranged on the undercarriage; the first fixing support and the second fixing support are made of plastic materials and correspondingly provided with plastic inverted buckles matched with the buckle positions. The undercarriage is inserted into the square groove of the fixing frame, the undercarriage is buckled by the inverted buckles of the first fixing support and the second fixing support, and the mounting mode is convenient and fast, and mounting can be completed without tools.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a landing gear structure of a fixed-wing aircraft. Background Art

[0002] The landing gear is a device used to support the gravity of the aircraft and bear the corresponding load when the aircraft is parked, taxiing, taking off and landing on the ground. The process of an aircraft taking off from the ground has a landing or recovery stage. With the rapid development of aircraft, it is widely used in civil and scientific research fields. For the convenience of transportation, the fuselage and landing gear of the aircraft are usually separated. The landing gear needs to be installed when in use. However, most aircraft and landing gear are currently fixed with screws. The assembly process is cumbersome and inconvenient to disassemble.

[0003] Currently, no effective solution has been proposed for the problems in the related technologies. Utility Model Content

[0004] In view of the problems in the related technology, the utility model proposes a fixed-wing aircraft landing gear structure to overcome the above technical problems existing in the existing related technology.

[0005] To this end, the specific technical solutions adopted by the utility model are as follows:

[0006] A fixed-wing aircraft landing gear structure, including a middle fuselage and an upper fuselage and a lower fuselage located at the upper and lower ends of the middle fuselage, characterized in that fuselage diagonal brace plates 1 and 2 connected to the middle fuselage are symmetrically arranged on both sides of the lower fuselage, and fixed brackets 1 and 2 are symmetrically arranged on the sides of the fuselage diagonal brace plates 1 and 2 that are away from each other, and landing gears that are cross-arranged and pass through the middle fuselage are arranged on the fixed brackets 1 and 2, and wheels are arranged at the bottom ends of the landing gears.

[0007] Preferably, a through hole is provided in the middle fuselage at a position where the two sets of landing gears penetrate, and fixing frames corresponding to the two sets of landing gears are respectively provided in the through hole.

[0008] Preferably, the fixing frame is provided with a square groove which is sleeved on the landing gear.

[0009] Preferably, the fixing bracket 1 and the fixing bracket 2 are provided with undercuts, and the landing gear is provided with buckle positions matching the undercuts.

[0010] Preferably, the wheel is connected to the landing gear via a wheel axle, and the landing gear is provided with a fixing piece connected to the wheel axle.

[0011] Preferably, the landing gear is provided with a connecting piece connected to one end of the wheel axle, and a fairing is provided on one side of the connecting piece.

[0012] Preferably, the upper fuselage is an integrated structure including a vertical tail, and the cross-sectional edges of the landing gear are consistent with the take-off or landing direction of the aircraft.

[0013] The beneficial effects of the utility model are as follows: the cross section of the landing gear is a square, and the edges and corners of the square are consistent with the flight and landing direction, thereby improving the take-off and landing overload capacity of the landing gear;

[0014] There are buckles on the landing gear; fixed bracket 1 and fixed bracket 2 are made of plastic material, and there are corresponding plastic buckles that match the buckles; the landing gear is inserted into the square groove of the fixed bracket, and the buckles of fixed bracket 1 and fixed bracket 2 buckle the landing gear. This installation method is convenient and quick and can be completed without the help of tools. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a structural schematic diagram of a fixed-wing aircraft landing gear structure according to an embodiment of the utility model;

[0017] Figure 2 is an exploded view of a landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model;

[0018] Figure 3 It is a structural schematic diagram of a fixed frame in a landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model;

[0019] Figure 4 It is a structural schematic diagram of a fixed bracket 1 in a landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model;

[0020] Figure 5 It is a partial exploded view of a landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model;

[0021] Figure 6 It is a front view of a landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model;

[0022] Figure 7 yes Figure 6 A local enlarged schematic diagram of point A in the middle.

[0023] In the figure:

[0024] 1. Middle fuselage; 2. Upper fuselage; 3. Lower fuselage; 4. Fuselage diagonal support plate 1; 5. Fuselage diagonal support plate 2; 6. Fixed bracket 1; 7. Fixed bracket 2; 8. Landing gear; 9. Wheel; 10. Through hole; 11. Fixed bracket; 12. Buckle position; 13. Wheel axle; 14. Fixing piece; 15. Connecting piece; 16. Fairing. DETAILED DESCRIPTION

[0025] To further illustrate each embodiment, the present invention provides drawings, which are part of the disclosure of the present invention and are mainly used to illustrate the embodiments. They can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, ordinary technicians in the field should be able to understand other possible implementation methods and advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are generally used to represent similar components.

[0026] According to an embodiment of the utility model, a fixed-wing aircraft landing gear structure is provided.

[0027] Embodiment 1;

[0028] like Figure 1-7 As shown, according to the landing gear structure of a fixed-wing aircraft according to an embodiment of the utility model, the structure comprises a middle fuselage 1 and a fuselage consisting of an upper fuselage 2 and a lower fuselage 3 located at the upper and lower ends of the middle fuselage 1, and is characterized in that fuselage diagonal brace plates 1 4 and fuselage diagonal brace plates 2 5 connected to the middle fuselage 1 are symmetrically arranged on both sides of the lower fuselage 3, and a symmetrically arranged fixed bracket 1 6 and a fixed bracket 2 7 are arranged on the side away from each other of the fuselage diagonal brace plates 1 4 and the fuselage diagonal brace plates 2 5, and landing gears 8 which are cross-arranged and pass through the middle fuselage 1 are arranged on the fixed brackets 1 6 and the fixed brackets 2 7, and wheels 9 are arranged at the bottom ends of the landing gears 8.

[0029] Embodiment 2:

[0030] like Figure 1-7 As shown, the middle fuselage 1 is provided with a through hole 10 at the penetration point of the two groups of the landing gears 8, and the through hole 10 is respectively provided with a fixing frame 11 connected to the two groups of the landing gears 8, and the fixing frame 11 is provided with a square groove sleeved on the landing gear 8, and the fixing bracket 1 6 and the fixing bracket 2 7 are provided with an undercut 12, and the landing gear 8 is provided with a buckle position matching the undercut 12.

[0031] Embodiment three;

[0032] like Figure 1-7As shown, the wheel 9 is connected to the landing gear 8 through the axle 13, the landing gear 8 is provided with a fixing member 14 connected to the axle 13, the landing gear 8 is provided with a connecting member 15 connected to one end of the axle 13, and a fairing 16 is provided on one side of the connecting member 15. The upper fuselage 2 is an integrated structure including a vertical tail, and the cross-sectional edges of the landing gear 8 are consistent with the take-off or landing direction of the aircraft.

[0033] In summary, with the help of the above technical solution of the utility model, the landing gear material is carbon fiber material, and the strength of carbon fiber is 5-10 times higher than that of steel. And the density of carbon fiber is only about 20% of the density of steel. The landing gear assembly includes a carbon rod, a wheel, a fairing, a trimming piece fixing, an axle, and an axle fixing frame, which are bonded with glue; the cross section of the landing gear 8 is a square, and the edges and corners of the square are consistent with the flight landing direction, which improves the take-off and landing overload capacity of the landing gear; there are buckles on the landing gear 8; the fixed bracket 1 6 and the fixed bracket 2 7 are made of plastic material, and there are corresponding plastic buckles matching the buckles; the landing gear 8 is inserted into the square groove of the fixing frame 11, and the buckles 12 of the fixed bracket 1 6 and the fixed bracket 2 7 buckle the landing gear 8. This installation method is convenient and quick and can be installed without the help of tools.

[0034] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A fixed-wing aircraft landing gear structure, comprising a middle fuselage (1) and a fuselage consisting of an upper fuselage (2) and a lower fuselage (3) located at upper and lower ends of the middle fuselage (1), characterized in that: A fuselage diagonal support plate 1 (4) and a fuselage diagonal support plate 2 (5) connected to the middle fuselage (1) are symmetrically arranged on both sides of the lower fuselage (3); a fixed bracket 1 (6) and a fixed bracket 2 (7) are symmetrically arranged on the side away from each other of the fuselage diagonal support plate 1 (4) and the fuselage diagonal support plate 2 (5); and landing gears (8) arranged in a cross-like manner and penetrating the middle fuselage (1) are arranged on the fixed brackets 1 (6) and the fixed brackets 2 (7); and wheels (9) are arranged at the bottom ends of the landing gears (8).

2. A fixed-wing aircraft landing gear structure according to claim 1, characterized in that: The middle fuselage (1) is provided with a through hole (10) at the point where the two sets of landing gears (8) pass through, and fixing frames (11) corresponding to and connected to the two sets of landing gears (8) are respectively provided in the through hole (10).

3. A fixed-wing aircraft landing gear structure according to claim 2, characterized in that: The fixing frame (11) is provided with a square groove which is sleeved on the landing gear (8).

4. A fixed-wing aircraft landing gear structure according to claim 3, characterized in that: The fixing bracket 1 (6) and the fixing bracket 2 (7) are provided with undercuts (12), and the landing gear (8) is provided with buckles matching the undercuts (12).

5. The fixed-wing aircraft landing gear structure according to claim 1, characterized in that: The wheel (9) is connected to the landing gear (8) via a wheel axle (13), and a fixing member (14) connected to the wheel axle (13) is provided on the landing gear (8).

6. A fixed-wing aircraft landing gear structure according to claim 5, characterized in that: The landing gear (8) is provided with a connecting piece (15) connected to one end of the wheel axle (13), and a fairing (16) is provided on one side of the connecting piece (15).

7. The fixed-wing aircraft landing gear structure according to claim 1, characterized in that: The upper fuselage (2) is an integrated structure including a vertical tail, and the cross-sectional edges and corners of the landing gear (8) are consistent with the take-off or landing direction of the aircraft.

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