Landing gear for vertical takeoff and landing aircraft

Abstract

The present invention provides a landing gear for a vertical takeoff and landing aircraft, comprising: a top connecting plate for connecting with the vertical takeoff and landing aircraft, and a bottom connecting plate oppositely arranged with respect to the top connecting plate, wherein the top connecting plate and the bottom connecting plate are connected by a plurality of main struts distributed at equal angles. The main strut includes a first rod section arranged horizontally, and a second rod section bent and extended from the first rod section, and the second rod section forms an angle with the first rod section. The purpose of the present invention is to provide a landing gear for a vertical takeoff and landing aircraft with a relatively large ground contact area.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and more particularly, to a landing gear for a vertical takeoff and landing aircraft. Background Art

[0002] For a vertical takeoff and landing aircraft, when it lands with a load, the landing gear usually has to bear a large impact energy. Especially during an unconventional landing, the quality of the landing gear plays a crucial role in protecting the aircraft.

[0003] An existing landing gear that can be used for a helicopter-type unmanned aerial vehicle is applicable to multiple terrains. This landing gear includes four legs. When landing, the contact surface between the aircraft and the ground is only the four legs, with a small contact surface and a large impact intensity. Moreover, during an abnormal landing or a landing with a load, it may cause damage to the aircraft and the load carried on the aircraft. Summary of the Invention

[0004] Aiming at the problems existing in the related art, the purpose of the present invention is to provide a landing gear for a vertical takeoff and landing aircraft with a relatively large contact area with the ground.

[0005] To achieve the above purpose, the present invention provides a landing gear for a vertical takeoff and landing aircraft, including: a top connecting plate for connecting with the vertical takeoff and landing aircraft, and a bottom connecting plate disposed opposite to the top connecting plate. Among them, the top connecting plate and the bottom connecting plate are connected by a plurality of main struts distributed at equal angles. The main strut includes a horizontally arranged first rod section, and a second rod section bent and extended from the first rod section. The second rod section forms an angle with the first rod section.

[0006] According to an embodiment of the present invention, the central axis of the top connecting plate coincides with the central axis of the bottom connecting plate. The landing gear includes a shock absorption structure, and opposite ends of the shock absorption structure are respectively connected to the top connecting plate and the bottom connecting plate.

[0007] According to an embodiment of the present invention, the shock absorption structure includes a sleeve disposed in the direction of the central axis of the top connecting plate and an elastic element received in the sleeve. One end of the sleeve is installed on the upper surface of the bottom connecting plate, and the elastic element can perform a telescopic movement relative to the sleeve in the direction of the central axis of the top connecting plate.

[0008] According to an embodiment of the present invention, a cylindrical portion is provided on the lower surface of the top connecting plate. Opposite ends of the elastic element respectively press against the inner bottom surface of the sleeve and the lower surface of the cylindrical portion, and at least a part of the cylindrical portion extends into the sleeve.

[0009] According to an embodiment of the present invention, the number of the main struts is four. The four main struts are arranged around the central axis of the top connecting plate at equal angles, and the projections of the four main struts on the horizontal plane form a cross-shaped structure.

[0010] According to an embodiment of the present invention, a transition section is formed between the first rod section and the second rod section, and the transition section is an inverted fillet of an included angle.

[0011] According to an embodiment of the present invention, the main support rod further includes a connecting section horizontally extending from the second rod section, the connecting section is fixedly connected to the top connecting plate, and the connecting section is parallel to the first rod section.

[0012] According to an embodiment of the present invention, a plurality of first clamping grooves are concavely provided on the side wall of the top connecting plate, and the plurality of connecting sections are respectively inserted into the plurality of first clamping grooves and connected to the top connecting plate through first bolts.

[0013] According to an embodiment of the present invention, a plurality of second clamping grooves are concavely provided on the side wall of the bottom connecting plate, and the free ends of the plurality of first rod sections are respectively inserted into the plurality of second clamping grooves and connected to the bottom connecting plate through second bolts.

[0014] According to an embodiment of the present invention, a first buffer gasket and a second buffer gasket are respectively provided on the bottom surfaces of the first rod section and the bottom connecting plate, and the bottom planes of the first buffer gasket and the second buffer gasket are on the same horizontal plane.

[0015] The beneficial technical effects of the present invention are as follows:

[0016] The landing gear for a vertical takeoff and landing aircraft according to the present invention, the main support rod for supporting the aircraft includes a first rod section coplanar with the bottom connecting plate. In this way, by the bottom connecting plate and the first rod section jointly contacting the ground, the contact area between the landing gear and the ground during landing is increased, and the impact strength on the fuselage and the load on the aircraft during landing is reduced; and, since the second rod section of the main support rod inclines away from the main support rod, the first rod section can have a longer length, further increasing the contact area between the landing gear and the ground when the aircraft lands, effectively absorbing the impact energy during landing, thereby ensuring the safe and stable landing of the aircraft. Brief Description of the Drawings

[0017] Figure 1 is a perspective view of a landing gear according to an embodiment of the present invention;

[0018] Figure 2 is a cross-sectional view of a landing gear according to an embodiment of the present invention;

[0019] Figure 3 is a top view of a landing gear according to an embodiment of the present invention;

[0020] Figure 4 is a schematic diagram of a landing gear during an abnormal landing according to an embodiment of the present invention. Detailed Embodiments

[0021] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0022] As Figures 1 to 4 shown, the present invention provides a landing gear for a vertical takeoff and landing aircraft, including: a top connecting plate 1 for connecting with the vertical takeoff and landing aircraft, and a bottom connecting plate 5 disposed opposite to the top connecting plate. Among them, the top connecting plate 1 and the bottom connecting plate 5 are connected by a plurality of main body struts 2 distributed at equal angles. The main body strut 2 includes a horizontally arranged first rod segment and a second rod segment bent and extended from the first rod segment. The second rod segment forms an angle with the first rod segment. The main body strut 2 is made of a metal material or a composite material such as carbon fiber. The angle formed between the first rod segment and the second rod segment gives the first rod segment and the second rod segment a resilience, and thus has a certain buffering function.

[0023] In the above embodiment, the main body strut 2 of the landing gear for the vertical takeoff and landing aircraft, which supports the aircraft, includes a first rod segment coplanar with the bottom connecting plate 5, that is to say, the bottom connecting plate 5 and the first rod segment are on the same horizontal plane. In this way, by the bottom connecting plate 5 and the first rod segment contacting the ground together, the contact area between the landing gear and the ground during landing is increased, and the impact intensity on the fuselage and the load on the aircraft during landing is reduced; and, since the first rod segment of the main body strut 2 inclines away from the main body strut 2, the first rod segment can have a longer length, further increasing the contact area between the landing gear and the ground when the aircraft lands, effectively absorbing the impact energy during landing, thereby ensuring the safe and stable landing of the aircraft.

[0024] That is to say, the second rod segment of the main body strut 2 extends obliquely from the plane where the top connecting plate 1 is located to the plane where the bottom connecting plate 5 is located, so as to increase the contact area of the bottom connecting plate 5 and the first rod segment and ensure the smooth landing of the aircraft.

[0025] In addition, the vertical takeoff and landing aircraft in the above embodiment may include, but is not limited to, small and medium-sized unmanned aircraft and manned models.

[0026] According to the embodiment of the present invention, the central axis of the top connecting plate 1 coincides with the central axis of the bottom connecting plate 5. In other words, the top connecting plate 1 and the bottom connecting plate 5 are disposed opposite to each other and parallel to each other, making the overall structure of the landing gear more stable. The landing gear includes a shock absorption structure 6. The opposite ends of the shock absorption structure 6 are respectively connected to the top connecting plate 1 and the bottom connecting plate 5. In this way, when the aircraft lands, the shock absorption structure 6 can effectively absorb the impact energy during landing, thereby ensuring the safe and stable landing of the aircraft.

[0027] According to an embodiment of the present invention, the shock-absorbing structure 6 includes a sleeve provided in the central axis direction of the top connecting plate 1 and an elastic element received in the sleeve. One end of the sleeve is mounted on the upper surface of the bottom connecting plate 5, and the elastic element can perform telescopic movement relative to the sleeve in the central axis direction of the top connecting plate 1. When the aircraft lands, the ground contacts the bottom connecting plate 5, and then squeezes the shock-absorbing structure 6 to compress the elastic element, thereby achieving the purpose of buffering. The elastic element can be an element with elastic function such as a spring or rubber.

[0028] According to an embodiment of the present invention, a cylindrical portion extends downward from the lower surface of the top connecting plate 1. The opposite ends of the elastic element respectively abut against the inner bottom surface of the sleeve and the lower surface of the cylindrical portion, and at least part of the cylindrical portion extends into the sleeve to press against the elastic element and prevent the elastic element from deforming and causing buffer failure.

[0029] Alternatively, in an alternative embodiment, the shock-absorbing structure 6 may also include a telescopic rod in the middle and a spring surrounding or disposed around the telescopic rod. Or a hydraulic telescopic rod can be used as the shock-absorbing structure 6. Of course, according to the specific usage situation, the shock-absorbing structure 6 may also include other structures with shock-absorbing functions, and the present invention is not limited thereto.

[0030] As Figures 2 to 3 shown, according to an embodiment of the present invention, the number of the main support rods 2 provided is four, and the four main support rods 2 are arranged at equal angles around the central axis of the top connecting plate 1, and the projections of the four main support rods 2 on the horizontal plane form a cross-shaped structure. The cross-shaped structure can not only play a buffering role when the aircraft lands, but also assist in stabilizing the center of gravity of the overall fuselage.

[0031] Of course, it can be understood that in an alternative embodiment, the main support rods 2 may also be asymmetrically arranged. For example, the landing gear may include five main support rods arranged at equal intervals. Further, in an alternative embodiment of the present invention, the main support rods 2 include metal, alloy or composite material.

[0032] Referring again to Figure 1 and Figure 2 , according to an embodiment of the present invention, a transition section is formed between the first rod section and the second rod section, and the transition section is an inverted rounded corner of an angle. So that the main support rod 2 can generate a certain deformation when the aircraft lands and absorb part of the impact energy.

[0033] According to an embodiment of the present invention, the second rod section further includes a connecting section extending horizontally, and the connecting section is fixedly connected to the top connecting plate 1. The connecting section is parallel to the first rod section, which facilitates the fixed connection of the two ends of the main support rod 2 to the parallel top connecting plate 1 and bottom connecting plate 5.

[0034] According to an embodiment of the present invention, a plurality of first card slots are concavely provided on the side wall of the top connecting plate 1. The plurality of connecting segments are respectively inserted into the plurality of first card slots and are connected to the top connecting plate 1 through the first bolts 4. Of course, according to specific situations, the number of the first bolts 4 and the main body struts 2 can be adjusted. Moreover, it should also be understood that the main body strut 2 and the top connecting plate 1 can also be connected by other means such as plug connectors.

[0035] In the above embodiment, a plurality of first threaded holes are provided on the top connecting plate. The central axis of the first threaded hole is parallel to the central axis of the connecting plate. The free end of the connecting segment is provided with a second threaded hole. The central axes of the first threaded hole and the second threaded hole are coincidentally arranged, which is convenient for the first bolt to be screwed in to form a firm connection.

[0036] According to an embodiment of the present invention, a plurality of second card slots are concavely provided on the side wall of the bottom connecting plate 5. The free ends of the plurality of first rod segments are respectively inserted into the plurality of second card slots and are connected to the bottom connecting plate 5 through the second bolts 7.

[0037] According to an embodiment of the present invention, a first buffer gasket 8 and a second buffer gasket 9 are respectively provided on the bottom surfaces of the first rod segment and the bottom connecting plate 5. The bottom planes of the first buffer gasket 8 and the second buffer gasket 9 are in the same horizontal plane, so that the entire bottom plane of the landing gear is in the same plane to facilitate smooth landing.

[0038] According to an embodiment of the present invention, as Figure 3 shown, the first rod segment and the second rod segment are in the same plane in the vertical direction, and the two are bent in the vertical plane to form an elastic buffer space.

[0039] As Figure 1 shown, an embodiment of the present invention relates to a landing gear applicable to vertical takeoff and landing aircraft (including but not limited to small and medium-sized unmanned aircraft and manned models), which is composed of a cross-shaped main frame, a four-way connecting plate (top connecting plate 1), a five-way connecting plate (bottom connecting plate 5), a strong spring (which can also be a shock absorber), rubber gaskets and several screws. Among them, the main frame includes four main body struts 2.

[0040] As shown in the figure, the top connecting plate 1 is an upper four-way connecting plate with four card slots. It includes a telescopic rod at the bottom, which squeezes the spring during landing to achieve the purpose of buffering. On the other hand, the weight of the telescopic rod can assist in stabilizing the center of gravity of the overall fuselage.

[0041] The main frame structure of the landing gear can be made of alloy or composite materials, with a certain degree of toughness, and a total of four main struts 2. Each main strut 2 adopts an integrally formed C-shaped structure. The main strut 2 can be a round rod or a square rod. The upper four-way connecting plate connects the four main struts 2 through the first bolt 4, and the specific connection method can be flexibly adjusted according to the type of the aircraft.

[0042] The top connecting plate 1 also includes screw mounting holes 3, and the landing gear can be fixedly connected to the main body of the aircraft through these four screw mounting holes 3.

[0043] Figure 1 The shown lower five-way connecting plate is connected to the four main struts 2 through the second bolt 7. The number of specific screw holes can be adjusted according to the strength requirements. The shock absorption structure 6 shown in the figure uses a spring, and different strength springs can be selected according to the size and type of the aircraft, or a shock absorber can be directly used.

[0044] A first buffer gasket 8 and a second buffer gasket 9 are respectively connected to the bottom of the main strut 2 and the bottom of the five-way connecting plate. The rubber gasket can be connected to the landing gear by, but not limited to, bonding, wrapping, etc.

[0045] When the aircraft lands normally, the first buffer gasket 8 and the second buffer gasket 9 first contact the ground, playing a first layer of buffer protection role. Due to inertia, the main body of the aircraft connected to the landing gear still maintains a downward trend, and will squeeze the spring or shock absorber through the four-way connecting plate, playing a second layer of buffer protection role. At the same time, the main strut 2 with a certain degree of toughness will also produce a certain deformation, absorbing part of the impact energy, playing a third layer of buffer protection role.

[0046] As Figure 4 shown, when the aircraft touches the ground with a certain corner or two corners of the landing gear first, due to the weight and position of the four-way connecting plate and the five-way connecting plate and the shock absorption structure 6 connected between them, which play a role in stabilizing the center of gravity similar to that of a tumbler, the aircraft will automatically correct the landing attitude to ensure the safe landing of the aircraft and protect the main body of the fuselage and the load on the aircraft from being damaged.

[0047] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A landing gear for a vertical take-off and landing aircraft, characterized in that, comprising: a top connecting plate (1) for connecting with the vertical take-off and landing aircraft, and a bottom connecting plate (5) oppositely arranged with the top connecting plate, wherein, the top connecting plate (1) and the bottom connecting plate (5) are connected by a plurality of main struts (2) distributed at equal angles, the main strut (2) includes a horizontally arranged first rod section, and a second rod section bent and extended from the first rod section, the second rod section forms an angle with the first rod section, wherein, the first rod section extends outward from the bottom connecting plate (5) in a direction away from the bottom connecting plate (5), the bottom connecting plate (5) and the first rod section are located on the same horizontal plane, and the first rod section is inclined away from the main strut (2), and wherein, the main strut (2) further includes a connecting section horizontally extending from the second rod section, the connecting section is fixedly connected to the top connecting plate (1), and the connecting section is parallel to the first rod section; wherein, the central axis of the top connecting plate (1) coincides with the central axis of the bottom connecting plate (5), the landing gear includes a shock absorption structure (6), and opposite ends of the shock absorption structure (6) are respectively connected to the top connecting plate (1) and the bottom connecting plate (5).

2. The landing gear according to claim 1, characterized in that, the shock absorption structure (6) includes a sleeve arranged in the direction of the central axis of the top connecting plate (1) and an elastic element received in the sleeve, one end of the sleeve is installed on the upper surface of the bottom connecting plate (5), and the elastic element can perform telescopic movement relative to the sleeve in the direction of the central axis of the top connecting plate (1).

3. The landing gear according to claim 2, characterized in that, a cylindrical portion is provided on the lower surface of the top connecting plate (1), opposite ends of the elastic element respectively abut against the inner bottom surface of the sleeve and the lower surface of the cylindrical portion, and at least a part of the cylindrical portion extends into the sleeve.

4. The landing gear according to claim 1, characterized in that, the number of the main struts (2) is four, the four main struts (2) are arranged at equal angles around the central axis of the top connecting plate (1), and the projections of the four main struts (2) on the horizontal plane are in a cross-shaped structure.

5. The landing gear according to claim 1, characterized in that, a transition section is formed between the first rod section and the second rod section, and the transition section is a fillet of the angle.

6. The landing gear according to claim 1, characterized in that, a plurality of first clamping grooves are recessed inwardly on the side wall of the top connecting plate (1), and the plurality of connecting sections are respectively inserted into the plurality of first clamping grooves and are connected to the top connecting plate (1) by first bolts (4).

7. The landing gear according to claim 1, characterized in that, The side wall of the bottom connecting plate (5) is recessed inwardly with a plurality of second clamping grooves, and the free ends of the plurality of first rod segments are respectively inserted into the plurality of second clamping grooves and are connected to the bottom connecting plate (5) by second bolts (7).

8. The landing gear according to claim 7, wherein, a first buffer gasket (8) and a second buffer gasket (9) are respectively arranged on the bottom surfaces of the first rod segment and the bottom connecting plate (5), and the bottom planes of the first buffer gasket (8) and the second buffer gasket (9) are in the same horizontal plane.

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