Novel skid type undercarriage structure

Abstract

The invention belongs to the technical field of aircraft landing gears, and particularly relates to a novel skid type landing gear structure which comprises two sliding pipes arranged at different inclination angles; the front cross beam is connected to the front ends of the two sliding pipes; the rear cross beam is connected to the rear ends of the two sliding pipes; the fuselage joint is mounted on the front cross beam and the rear cross beam and is used for connecting the front cross beam and the rear cross beam with a fuselage; wherein the front cross beam and the rear cross beam are both bent upwards to form an arc bow shape, and the load of the undercarriage and the aircraft is reduced; the weight of the skid undercarriage and the aircraft is reduced; the buffering performance of the skid undercarriage is improved; and the manufacturing cost of the aircraft is reduced.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft landing gear, and in particular relates to a novel skid-type landing gear structure. Background Art

[0002] For the landing gear, the most important function is to reduce the landing load of the entire aircraft through buffering performance. For the skid landing gear, its buffering performance is achieved through the elastic deformation of the skid structure. However, the skid landing gear with this structure has limited elastic deformation, so the buffering performance is poor.

[0003] With the development of modern aircraft, the requirements for weight are more stringent, which means higher requirements for the cushioning performance of the landing gear. Therefore, this traditional layout of the skid landing gear structure is increasingly difficult to meet the performance requirements of the aircraft. Therefore, in many cases, the landing gear has to be designed as a wheeled landing gear with an oil-gas buffer, but this landing gear structure is complex and the cost will be greatly increased. Summary of the invention

[0004] In order to solve the above problems, the present application provides a novel skid-type landing gear structure, comprising:

[0005] Slide pipes, including two arranged at different inclination angles;

[0006] A front crossbeam, connected to the front ends of the two sliding tubes;

[0007] a rear cross member connected to the rear ends of the two sliding tubes;

[0008] A fuselage joint, mounted on the front crossbeam and the rear crossbeam, for connecting the front crossbeam and the rear crossbeam to the fuselage;

[0009] Among them, the front crossbeam and the rear crossbeam are both bent upward to form an arc-shaped bow.

[0010] Preferably, the front end of the slide tube tilts upward to facilitate the adjustment of the posture of the aircraft when it touches the ground.

[0011] Preferably, the sliding tube is connected to the front cross beam and the rear cross beam via a joint, the joint comprises a sleeve and a mounting seat at one end of the sleeve, the mounting seat is fixedly connected to the surface of the sliding tube, and the sleeve is fixedly sleeved to both ends of the front cross beam and the rear cross beam.

[0012] Preferably, the plane where the front cross beam and the rear cross beam are located is inclined forward relative to the plane where the sliding tube is located.

[0013] Preferably, the front cross beam and the rear cross beam have a certain elastic deformation capacity.

[0014] Preferably, a cross beam is connected between two arms where the front cross beam is connected to the sliding tube or / and between two arms where the rear cross beam is connected to the sliding tube.

[0015] Preferably, a plurality of connection points at different heights are provided between the two arms connecting the front cross beam and the sliding tube or / and between the two arms connecting the rear cross beam and the sliding tube, and the cross beams are connected to connection points at different heights according to the deformation requirements of the front cross beam and the rear cross beam.

[0016] Preferably, the angle of the plane where the front cross beam and the rear cross beam are located relative to the plane where the slide tube is located matches the landing load of the aircraft.

[0017] Preferably, the front cross beam and the rear cross beam are straight bars in the middle.

[0018] Preferably, there are at least two fuselage joints on the front cross beam and at least two fuselage joints on the rear cross beam.

[0019] Preferably, the plane where the front cross beam (1) and the rear cross beam (2) are located is inclined forward relative to the plane where the slide tube (4) is located, the front cross beam (1) and the slide tube (4) are hinged, the front cross beam (1) and the slide tube (4) have a rotational freedom in the pitch direction within a preset angle range, an elastic sheet connected between the front cross beam (1) and the slide tube (4) is provided at the angle between the front cross beam (1) and the slide tube (4), the rear cross beam (2) and the slide tube (4) are hinged, the rear cross beam (2) and the slide tube (4) have a rotational freedom in the pitch direction within a preset angle range, and an elastic sheet connected between the rear cross beam (2) and the slide tube (4) is provided at the angle between the rear cross beam (2) and the slide tube (4).

[0020] Preferably, limit blocks are respectively arranged before and after the hinge point between the front cross beam (1) and the slide tube (4), and the cross beam (1) has a certain angle of rotational freedom between the front and rear limit blocks; limit blocks are respectively arranged before and after the hinge point between the rear cross beam (2) and the slide tube (4), and the rear cross beam (2) has a certain angle of rotational freedom between the front and rear limit blocks.

[0021] Preferably, the elastic sheet has a preload force that causes the front cross beam (1) and the rear cross beam (2) to rotate backwards. When the landing gear lands and is loaded, the elastic sheet bends, the front cross beam (1) and the rear cross beam (2) rotate forwards, and the elastic sheet absorbs the load impact.

[0022] The advantages of the present application include: reducing the load on the landing gear and the aircraft; reducing the weight of the skid landing gear and the aircraft; improving the buffering performance of the skid landing gear; and reducing the manufacturing cost of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the novel skid-type landing gear structure of Example 1. DETAILED DESCRIPTION

[0024] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0025] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0026] Implementation 1:

[0027] like Figure 1 As shown, in order to solve the above problems, the present application provides a novel skid-type landing gear structure, including:

[0028] Sliding pipe 4, including two arranged at different inclination angles;

[0029] A front crossbeam 1 connected to the front ends of two sliding tubes 4;

[0030] A rear cross beam 2 connected to the rear ends of the two sliding tubes 4;

[0031] A fuselage joint 3, mounted on the front crossbeam 1 and the rear crossbeam 2, for connecting the front crossbeam 1 and the rear crossbeam 2 to the fuselage;

[0032] The front cross beam 1 and the rear cross beam 2 are both bent upward to form a circular arc shape.

[0033] The front end of the slide tube 4 tilts upwards, making it easier for the slide tube 4 to slide on the ground.

[0034] The sliding tube 4 is connected to the front cross beam 1 and the rear cross beam 2 through a joint 5, and the joint 5 includes a sleeve and a mounting seat at one end of the sleeve. The mounting plate is fixedly connected to the surface of the sliding tube 4, and the sleeve is fixedly sleeved at both ends of the front cross beam 1 and the rear cross beam 2.

[0035] The plane where the front cross beam 1 and the rear cross beam 2 are located is inclined forward relative to the plane where the sliding tube 4 is located.

[0036] The front cross beam 1 and the rear cross beam 2 have a certain elastic deformation capability.

[0037] The angle of the plane where the front cross beam 1 and the rear cross beam 2 are located relative to the plane where the slide tube 4 is located matches the load on the landing of the aircraft.

[0038] The front cross beam 1 and the rear cross beam 2 are straight bars in the middle.

[0039] There are at least two fuselage joints 3 on the front cross beam 1 and the rear cross beam 2 respectively.

[0040] Embodiment 2:

[0041] A novel skid-type landing gear structure, comprising:

[0042] Sliding pipe 4, including two arranged at different inclination angles;

[0043] A front crossbeam 1 connected to the front ends of two sliding tubes 4;

[0044] A rear cross beam 2 connected to the rear ends of the two sliding tubes 4;

[0045] A fuselage joint 3, mounted on the front crossbeam 1 and the rear crossbeam 2, for connecting the front crossbeam 1 and the rear crossbeam 2 to the fuselage;

[0046] The front cross beam 1 and the rear cross beam 2 are both bent upward to form a circular arc shape.

[0047] The front end of the slide tube 4 tilts upwards, making it easier for the slide tube 4 to slide on the ground.

[0048] The sliding tube 4 is connected to the front cross beam 1 and the rear cross beam 2 through a joint 5. The joint 5 includes a sleeve and a mounting seat at one end of the sleeve. The mounting seat is fixedly connected to the surface of the sliding tube 4. The sleeve is fixedly sleeved with both ends of the front cross beam 1 and the rear cross beam 2.

[0049] The plane where the front cross beam 1 and the rear cross beam 2 are located is inclined forward relative to the plane where the sliding tube 4 is located.

[0050] The front cross beam 1 and the rear cross beam 2 have a certain elastic deformation capability.

[0051] A crossbeam is connected between two arms where the front crossbeam 1 is connected to the sliding tube 4 or / and between two arms where the rear crossbeam 2 is connected to the sliding tube 4.

[0052] Example 3

[0053] A novel skid-type landing gear structure, comprising:

[0054] Sliding pipe 4, including two arranged at different inclination angles;

[0055] A front crossbeam 1 connected to the front ends of two sliding tubes 4;

[0056] A rear cross beam 2 connected to the rear ends of the two sliding tubes 4;

[0057] A fuselage joint 3, mounted on the front crossbeam 1 and the rear crossbeam 2, for connecting the front crossbeam 1 and the rear crossbeam 2 to the fuselage;

[0058] The front cross beam 1 and the rear cross beam 2 are both bent upward to form a circular arc shape.

[0059] The front end of the slide tube 4 tilts upwards, making it easier for the slide tube 4 to slide on the ground.

[0060] The plane where the front cross beam 1 and the rear cross beam 2 are located is inclined forward relative to the plane where the sliding tube 4 is located, and the front cross beam 1 and the rear cross beam 2 have a certain elastic deformation capacity.

[0061] The angle of the plane where the front cross beam 1 and the rear cross beam 2 are located relative to the plane where the slide tube 4 is located matches the load on the landing of the aircraft.

[0062] The plane where the front cross beam 1 and the rear cross beam 2 are located is inclined forward relative to the plane where the slide tube 4 is located. The front cross beam 1 and the slide tube 4 are hinged, and there is a rotational freedom in the pitch direction within a preset angle range between the front cross beam 1 and the slide tube 4. An elastic sheet connected between the front cross beam 1 and the slide tube 4 is provided at the angle between the front cross beam 1 and the slide tube 4. The rear cross beam 2 and the slide tube 4 are hinged, and there is a rotational freedom in the pitch direction within a preset angle range between the rear cross beam 2 and the slide tube 4. An elastic sheet connected between the rear cross beam 2 and the slide tube 4 is provided at the angle between the rear cross beam 2 and the slide tube 4.

[0063] Limit blocks are respectively set before and after the hinge point between the front crossbeam 1 and the sliding tube 4, and the crossbeam 1 has a certain angle of rotational freedom between the front and rear limit blocks. Limit blocks are respectively set before and after the hinge point between the rear crossbeam 2 and the sliding tube 4, and the rear crossbeam 2 has a certain angle of rotational freedom between the front and rear limit blocks.

[0064] The elastic sheet has a preload force to rotate the front beam 1 and the rear beam 2 backward. When the landing gear lands and is loaded, the elastic sheet bends, the front beam 1 and the rear beam 2 rotate forward, and the elastic sheet absorbs the load impact.

[0065] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A novel skid-type landing gear structure, characterized in that: include: A slide pipe (4), comprising two slide pipes arranged at different inclination angles; A front crossbeam (1) connected to the front ends of the two sliding tubes (4); A rear cross beam (2) connected to the rear ends of the two sliding tubes (4); A fuselage joint (3) is installed on the front crossbeam (1) and the rear crossbeam (2) and is used to connect the front crossbeam (1) and the rear crossbeam (2) to the fuselage; The front cross beam (1) and the rear cross beam (2) are both bent upward to form a circular arc shape.

2. The novel skid-type landing gear structure according to claim 1, characterized in that: The front end of the slide tube (4) tilts upward, so that the slide tube (4) can contact the ground and adjust its posture when the aircraft lands.

3. The novel skid-type landing gear structure according to claim 1, characterized in that: The slide tube (4) is connected to the front cross beam (1) and the rear cross beam (2) via a joint (5), wherein the joint (5) comprises a sleeve and a mounting seat located at one end of the sleeve, wherein the mounting seat is fixedly connected to the surface of the slide tube (4), and the sleeve is fixedly sleeved to both ends of the front cross beam (1) and the rear cross beam (2).

4. The novel skid-type landing gear structure according to claim 1, characterized in that: The plane where the front cross beam (1) and the rear cross beam (2) are located is inclined forward relative to the plane where the sliding tube (4) is located.

5. The novel skid-type landing gear structure as claimed in claim 4, characterized in that: The front cross beam (1) and the rear cross beam (2) have a certain elastic deformation capability.

6. The novel skid-type landing gear structure as claimed in claim 4, characterized in that: A crossbeam is connected between the two arms where the front crossbeam (1) is connected to the sliding tube (4) or / and between the two arms where the rear crossbeam (2) is connected to the sliding tube (4).

7. The novel skid-type landing gear structure according to claim 6, characterized in that: A plurality of connection points at different heights are arranged between the two arms connecting the front cross beam (1) and the slide tube (4) or / and between the two arms connecting the rear cross beam (2) and the slide tube (4), and the cross beams are connected to the connection points at different heights according to the deformation requirements of the front cross beam (1) and the rear cross beam (2).

8. The novel skid-type landing gear structure as claimed in claim 6, characterized in that: The angle of the plane where the front cross beam (1) and the rear cross beam (2) are located relative to the plane where the slide tube (4) is located matches the load on the landing of the aircraft.

9. The novel skid-type landing gear structure as claimed in claim 6, characterized in that: The front cross beam (1) and the rear cross beam (2) are straight rods in the middle.

10. The novel skid-type landing gear structure as claimed in claim 6, characterized in that: The fuselage joints (3) are at least two on the front cross beam (1) and the rear cross beam (2).

11. The novel skid-type landing gear structure according to claim 4, characterized in that: The plane where the front cross beam (1) and the rear cross beam (2) are located is inclined forward relative to the plane where the slide tube (4) is located; the front cross beam (1) and the slide tube (4) are hinged; there is a rotational freedom in a pitch direction within a preset angle range between the front cross beam (1) and the slide tube (4); an elastic sheet connected between the front cross beam (1) and the slide tube (4) is provided at the angle between the front cross beam (1) and the slide tube (4); the rear cross beam (2) and the slide tube (4) are hinged; there is a rotational freedom in a pitch direction within a preset angle range between the rear cross beam (2) and the slide tube (4); and an elastic sheet connected between the rear cross beam (2) and the slide tube (4) is provided at the angle between the rear cross beam (2) and the slide tube (4).

12. The novel skid-type landing gear structure according to claim 11, characterized in that: Limit blocks are respectively arranged at the front and rear of the hinge point between the front cross beam (1) and the slide tube (4), and the cross beam (1) has a certain degree of rotational freedom between the front and rear limit blocks; limit blocks are respectively arranged at the front and rear of the hinge point between the rear cross beam (2) and the slide tube (4), and the rear cross beam (2) has a certain degree of rotational freedom between the front and rear limit blocks.

13. The novel skid-type landing gear structure according to claim 12, characterized in that: The elastic sheet has a preload force that causes the front cross beam (1) and the rear cross beam (2) to rotate backwards. When the landing gear lands and is loaded, the elastic sheet bends, the front cross beam (1) and the rear cross beam (2) rotate forwards, and the elastic sheet absorbs the impact of the load.

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