Damping buffer module applied to sled type undercarriage of aircraft

Abstract

The utility model provides a damping buffer module applied to an aircraft sleigh type undercarriage. The damping buffer module is used for connecting an arch beam and a sleigh pipe in the aircraft sleigh type undercarriage. The damping buffer module comprises a buffer connecting piece connected with the arched beam, a bottom connecting piece fixed on the sleigh pipe, a buffer, a buffer bracket and a fixed rod; a first lug is arranged at the bottom of the buffer connecting piece, and a second lug is arranged on the side wall; the first end of the buffer is hinged to the first lug through a first shaft shoulder screw, and the second end of the buffer is hinged to the bottom connecting piece through a second shaft shoulder screw. The first end of the buffering support is hinged to the second lug piece, the second end of the buffering support is fixedly connected to the bottom connecting piece, and a knob plunger is arranged on the buffering support. The first end of the fixing rod is hinged to the bottom connecting piece through the second shaft shoulder screw, the second end of the fixing rod is provided with a limiting clamping groove matched with the first shaft shoulder screw, and the fixing rod is further provided with a limiting hole matched with the knob plunger. According to the utility model, the buffering performance of the sled type undercarriage during landing is improved.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aircraft landing gear, in particular to a damping buffer module applied to an aircraft sled type landing gear. Background Art

[0002] The sled landing gear is a component that supports the entire aircraft, so it is an indispensable and important part of the aircraft. When the aircraft is landing and taking off, the ground will cause great impact and turbulence to the aircraft, which can easily cause adverse effects on the structure and safety performance of the aircraft. Therefore, a buffer device is usually installed on the landing gear to absorb the impact performance generated and reduce the overload caused by landing and takeoff.

[0003] The sled landing gear of unmanned aerial vehicles is generally made of bent metal pipes. During landing operations, the impact kinetic energy can only be absorbed through the elastic deformation of the metal pipes, but the effect is not good and cannot adapt to landing conditions with different terrains. This landing gear made of bent metal pipes has great rigidity and will produce a large overload factor during landing, which in turn affects the structural strength of the aircraft itself and also affects the safety performance of the aircraft.

[0004] Therefore, how to improve the cushioning performance of the ski-type landing gear during landing, thereby improving the safety of the aircraft, remains a problem that needs to be urgently solved in the industry. Utility Model Content

[0005] Features and advantages of the invention are set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.

[0006] In order to overcome the problems of the prior art, the utility model provides a damping buffer module applied to an aircraft sled landing gear, which is used to connect the arched beam and the sled tube in the aircraft sled landing gear; the damping buffer module includes a buffer connector, a bottom connector, a buffer, a buffer bracket, and a fixing rod, wherein:

[0007] The buffer connecting piece is used to be connected to the arched beam, the bottom of the buffer connecting piece is provided with a first ear piece, and the side wall is provided with a second ear piece;

[0008] The bottom connecting piece is used to be fixed on the sled tube;

[0009] The first end of the buffer is hinged to the first ear piece through a first shoulder screw, and the second end is hinged to the bottom connector through a second shoulder screw;

[0010] The first end of the buffer bracket is hinged to the second ear piece, and the second end is fixedly connected to the bottom connecting member, and the buffer bracket is provided with a knob plunger;

[0011] The first end of the fixing rod is hinged to the bottom connecting piece through the second shoulder screw, and the second end is provided with a limiting slot matching the first shoulder screw. The fixing rod is also provided with a limiting hole matching the knob plunger.

[0012] Preferably, a groove is provided on the buffer connecting member, and a thrust bearing is installed in the groove.

[0013] Preferably, the buffer is connected to the arched beam via a thrust bearing connector, the main body of the thrust bearing connector is a limiting sleeve, a limiting shaft section is provided at the bottom of the sleeve, and a notch matching the second ear piece is provided on the limiting shaft section.

[0014] Preferably, a slot axis is provided at the center of the slot, and a thread is provided at the top of the slot axis.

[0015] Preferably, the first shoulder screw is provided with a long optical axis section and a short optical axis section, and both ends are tapped with threads.

[0016] Preferably, the bottom connecting member comprises a half-tube body hugging the ski tube and a connecting ear piece arranged on the half-tube body.

[0017] Preferably, the connecting ear piece is provided with a hinge through hole for hingedly connecting the buffer and a fixing through hole for fixing the buffer bracket.

[0018] Preferably, it also includes a wear-resistant gasket, which is attached to the outer wall surface of the sled tube and is opposite to the bottom connecting piece.

[0019] Preferably, it further comprises a first self-locking nut for fastening the fixing rod after the limiting groove of the fixing rod is inserted into the first shoulder screw.

[0020] Preferably, the second ear faces the ski tube on the opposite side.

[0021] The utility model provides a damping buffer module applied to an aircraft sled landing gear, which utilizes a buffer to absorb impact kinetic energy generated by an aircraft landing operation, thereby improving the buffering performance of the sled landing gear during landing and enhancing the safety of the aircraft.

[0022] By reading the specification, ordinary technicians in this field will have a better understanding of the characteristics and contents of these technical solutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The present invention will be described in detail below with reference to the accompanying drawings and in combination with examples, and the advantages and implementation methods of the present invention will become more obvious. The contents shown in the accompanying drawings are only used to explain the present invention and do not constitute any limitation to the present invention. In the accompanying drawings:

[0024] Figure 1 The present invention is a schematic structural diagram of a damping buffer module applied to an aircraft ski-type landing gear according to an embodiment of the present invention.

[0025] Figure 2 It is a structural schematic diagram of the damping buffer module of an embodiment of the utility model.

[0026] Figure 3 This is a schematic diagram of the state of the damping buffer module of an embodiment of the utility model performing supporting work.

[0027] Figure 4 This is a schematic diagram of the state of the damping buffer module of an embodiment of the utility model performing buffering work.

[0028] Reference numerals:

[0029] 110-bow beam, 120-sled tube, 130-damping buffer module, 20-thrust bearing, 21-first shoulder screw, 22-second shoulder screw, 23-first self-locking nut, 30-buffer connector, 31-first ear, 32-second ear, 33-slot, 34-slot axis, 40-buffer, 50-bottom connector, 51-half sleeve body, 52-connecting ear, 53-hinged through hole, 54-fixed through hole, 55-wear-resistant gasket avoidance groove, 60-fixing rod, 61-through hole, 62-limiting slot, 63-limiting hole, 70-buffer bracket, 71-first through hole, 72-knob plunger mounting hole, 73-second through hole, 80-knob plunger, 81-first shoulder screw, 83-second shoulder screw, 85-fixed sleeve, 90-wear-resistant gasket. DETAILED DESCRIPTION

[0030] In the description of the present invention, unless otherwise specified, "multiple" means two or more; the orientations or positional relationships indicated by the terms "upper", "lower", "inner", "outer", "top", "bottom", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0031] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it 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 or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the relevant drawings. The preferred embodiments of the present application are given in the drawings. However, the present application can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present application more thoroughly and comprehensively understood.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application.

[0034] like Figures 1 to 4 As shown, the utility model provides a damping buffer module 130 applied to an aircraft sled landing gear, and the damping buffer module 130 is used to connect the arched beam 110 and the sled tube 120 in the aircraft sled landing gear, that is, the arched beam 110 is connected to the sled tube 120 through the damping buffer module 130, and a damping buffer module 130 is provided at each intersection of the arched beam 110 and the sled tube 120. Generally, there are two or more arched beams 110, which are fixed to the bottom of the aircraft body and arranged along the length direction of the aircraft body; there are two sled tubes 120, which are respectively fixed on both sides of the arched beam 110 to form a sled landing gear, and the sled landing gear can be applied to aircraft with vertical take-off and landing. When there are two arched beams 110 and two sled tubes 120, four damping buffer modules 130 need to be provided.

[0035] The damping buffer module 130 includes a buffer connector 30, a bottom connector 50, a buffer 40, a buffer bracket 70, and a fixing rod 60. The buffer connector 30 is connected to the arched beam 110, the bottom connector 50 is fixed to the sled tube 120, and the buffer 40, the buffer bracket 70, and the fixing rod 60 are arranged between the buffer connector 30 and the bottom connector 50.

[0036] In a specific implementation, the bottom connector 50 includes a half-tube body 51 that hugs the sled tube and a connecting ear piece 52 disposed on the half-tube body 51. The connecting ear piece 52 is provided with a hinge through hole 53 for hingedly connecting the buffer 40 and a fixing through hole 54 for fixing the buffer bracket 70.

[0037] The bottom of the buffer connector 30 is provided with a first ear piece 31, and the side wall is provided with a second ear piece 32; the first ear piece 31 and the second ear piece 32 are provided with matching holes. Preferably, the second ear piece 32 faces the opposite side of the ski tube, that is, the second ear piece 32 faces the inside.

[0038] The first end of the buffer 40 is hinged to the first ear piece 31 through the first shoulder screw 21. The first shoulder screw 31 is provided with a long optical axis section and a short optical axis section, and both ends are tapped with threads. The long optical axis section of the first shoulder screw 31 passes through the matching hole on the first ear piece 31 and the matching hole set at the first end of the buffer 40, and is fastened with a self-locking nut to form a hinge structure, and the short optical axis section faces the inner side of the landing gear.

[0039] The second end of the buffer 40 is hinged to the bottom connecting member 50 through the second shoulder screw 22. The second shoulder screw 32 is also provided with a long optical axis section and a short optical axis section, and both ends are tapped with threads. The long optical axis section of the second shoulder screw 22 passes through the hinge through hole 53 on the bottom connecting member 50 and is fastened with a self-locking nut to form a hinge structure, and the short optical axis section faces the inner side of the landing gear.

[0040] The first end of the buffer bracket 70 is hinged to the second ear piece 32, and the second end is fixedly connected to the bottom connector 50. In a specific implementation, the first end of the buffer bracket 70 is provided with a first through hole 71, which is fastened to the matching hole on the second ear piece 32 of the buffer connector 30 by a first shoulder screw 81 to form a hinge structure.

[0041] The second end of the buffer bracket 70 is provided with a second through hole 73, and the second shoulder screw 83 passes through the second through hole 73 of the buffer bracket 70 and the fixing through hole 54 on the connecting ear piece 52 to fix the buffer bracket 70 to the bottom connecting member 50 to form a rigid body. It should be noted that the number of the second through holes 73 and the second shoulder screws 83 is equal and not less than 2. In this embodiment, there are 2 second through holes 72 and 2 second shoulder screws 83, and of course, 3 are also feasible. The buffer bracket 70 is also provided with a knob plunger mounting hole 72 for fixing the knob plunger 80. The knob plunger mounting hole 72 can be set in the middle position of the buffer bracket.

[0042] A through hole 61 is provided at the first end of the fixing rod 60, and a short optical axis section of the second shoulder screw 22 passes through the through hole 61 and is fastened with a self-locking nut, thereby hingedly connecting the fixing rod to the bottom connecting member 50 to form a rocker arm structure.

[0043] The second end of the fixing rod 60 is provided with a limiting slot 62 matching the first shoulder screw 21. The limiting slot 62 can be rotated and inserted into the first shoulder screw 21 by rotating the fixing rod 60, and the fixing rod 60 can be tightened by the first self-locking nut 23 after the limiting slot 62 of the fixing rod is inserted into the first shoulder screw.

[0044] The fixing rod 60 is also provided with a limiting hole 63 matching with the knob plunger, which can just catch the positioning shaft section of the knob plunger 80. When the aircraft is in flight, the fixing rod 60 is pushed inward and positioned by the positioning pin on the knob plunger. When the aircraft is in ground transportation, the fixing rod 60 is straightened so that the limiting slot 62 at the upper end is caught in the short optical shaft section of the first shoulder screw and fastened by the first self-locking nut on the side.

[0045] In one embodiment of the utility model, a wear-resistant gasket 90 is also included. The cross section of the wear-resistant gasket 90 is arc-shaped, and is attached to the outer wall surface of the sled tube 120 and fixed to the sled tube 120 by rivets. In specific implementation, two wear-resistant gaskets are provided at the bottom of the sled tube 120, one at the front and the other at the back, and are opposite to the bottom connecting member 50. At this time, a wear-resistant gasket avoidance groove 55 is provided on one side of the semi-sleeve structure 51 of the bottom connecting member. The wear-resistant gasket 90 is provided with four fixing holes, two of which on one side share the holes of the bottom connecting member 50, so as to reduce the number of holes in the sled tube.

[0046] In one embodiment of the utility model, the buffer 40 is connected to the arched beam 110 through the thrust bearing connector 10, and the thrust bearing connector 10 is fixed to the end of the arched beam through rivet connection. More specifically, the main body of the thrust bearing connector 10 is a limiting sleeve, and the barrel is provided with a plurality of rivet fixing holes 11, and the bottom of the limiting sleeve is provided with a limiting shaft section 12, and the limiting shaft section 12 is provided with a notch groove matching the second ear piece 32. After installation, the second ear piece 32 on the buffer connector is interlocked with the notch groove, and the width of the notch groove is greater than the width of the second ear piece of the buffer connector 15, so that the buffer connector can achieve a certain angle of rotation.

[0047] The buffer connector 30 is provided with a slot 33, in which the thrust bearing 20 is mounted, and the slot 33 is used to position and connect the thrust bearing 20 with the outer ring. More specifically, the center of the slot 33 is provided with a slot axis 34, and the slot axis 34 is provided with a positioning optical axis section and a thread, and the thread can be provided at the top of the slot axis 34. The slot axis 34 passes through the axial through hole of the thrust bearing 20 and the thrust bearing connector 10, and is fastened with a nut and a gasket.

[0048] In this embodiment, the thrust bearing connector and the buffer connector mounted on the arch beam support the entire aircraft, and a thrust bearing 14 is provided between the second ear pieces of the thrust bearing connector 13 and the buffer connector 15, through which loads can be transmitted and relative rotation can be performed.

[0049] The sled landing gear with damping and shock absorption provided in the present application requires loosening the locating pin of the knob plunger, rotating the limiting slot of the fixing rod to the first shoulder screw, and fixing it with the first self-locking nut, thereby limiting the operation of the buffer, when the unmanned aerial vehicle is being transported and slid on the ground.

[0050] In another embodiment of the present application, fixed sleeves 85 can be provided at the front and rear ends of the sled tubes on both sides to facilitate the transport wheel pin holes for transporting the aircraft on the ground, or transporting it in and out of the hangar. The entire aircraft can be lifted by passing through the fixed sleeves at the front and rear ends through the transport wheel equipment, and the aircraft can be moved by manpower.

[0051] When the unmanned aerial vehicle is flying in the air and landing, it is necessary to loosen the first self-locking nut, rotate the limit slot of the fixing rod to the pin positioning position of the knob plunger, use the knob plunger to position the limit fixing rod, so that the buffer is compressed and operated. Under the action of the hinge structure at the upper and lower ends of the buffer, the sled tube is flipped outward by the hinge structure formed by the second ear of the buffer beam connector and the buffer bracket, so as to further absorb the impulse during landing and reduce the impact load.

[0052] The damping buffer module applied to the aircraft sled landing gear provided by the utility model has a simple structure and can effectively absorb the impulse during landing through the compression of the buffer and the hinge structures at the upper and lower ends of the buffer, thereby reducing the impact load.

[0053] The preferred embodiments of the present invention are described above with reference to the accompanying drawings. A person skilled in the art may implement the present invention in a variety of variations without departing from the scope and essence of the present invention. For example, a feature shown or described as part of one embodiment may be used in another embodiment to obtain another embodiment. The above are only preferred feasible embodiments of the present invention, and do not limit the scope of rights of the present invention. Any equivalent changes made using the contents of the present invention specification and the accompanying drawings are included in the scope of rights of the present invention.

Claims

1. A damping buffer module applied to an aircraft ski-type landing gear, used to connect a bow beam and a ski tube in the aircraft ski-type landing gear, characterized in that: The damping buffer module includes a buffer connector, a bottom connector, a buffer, a buffer bracket, and a fixing rod, wherein: The buffer connecting piece is used to be connected to the arched beam, the bottom of the buffer connecting piece is provided with a first ear piece, and the side wall is provided with a second ear piece; The bottom connecting piece is used to be fixed on the sled tube; The first end of the buffer is hinged to the first ear piece through a first shoulder screw, and the second end is hinged to the bottom connector through a second shoulder screw; The first end of the buffer bracket is hinged to the second ear piece, and the second end is fixedly connected to the bottom connecting member, and the buffer bracket is provided with a knob plunger; The first end of the fixing rod is hinged to the bottom connecting piece through the second shoulder screw, and the second end is provided with a limiting slot matching the first shoulder screw. The fixing rod is also provided with a limiting hole matching the knob plunger.

2. The damping and buffering module for aircraft ski-type landing gear according to claim 1, characterized in that: The buffer connecting piece is provided with a slot, and a thrust bearing is installed in the slot.

3. The damping and buffering module for aircraft ski-type landing gear according to claim 2, characterized in that: The buffer is connected to the arched beam through a thrust bearing connector. The main body of the thrust bearing connector is a limiting sleeve, a limiting shaft section is provided at the bottom of the sleeve, and a notch matching the second ear piece is provided on the limiting shaft section.

4. The damping and buffering module for aircraft ski-type landing gear according to claim 2, characterized in that: A slot axis is arranged at the center of the slot, and a thread is arranged at the top of the slot axis.

5. The damping and buffering module for aircraft ski-type landing gear according to claim 1, characterized in that: The first shoulder screw rod is provided with a long optical axis section and a short optical axis section, and has threads tapped at both ends.

6. The damping and buffering module for aircraft ski-type landing gear according to claim 1, characterized in that: The bottom connecting member comprises a half-tube body hugging the ski tube and a connecting ear piece arranged on the half-tube body.

7. The damping and buffering module for aircraft ski-type landing gear according to claim 6, characterized in that: The connecting ear piece is provided with a hinge through hole for hingedly connecting the buffer and a fixing through hole for fixing the buffer bracket.

8. The damping and buffering module for aircraft ski-type landing gear according to claim 6, characterized in that: It also includes a wear-resistant gasket, which is attached to the outer wall surface of the sled tube and is opposite to the bottom connecting piece.

9. The damping and buffering module for aircraft ski-type landing gear according to claim 1, characterized in that: It also includes a first self-locking nut, which is used to fasten the fixing rod after the limiting groove of the fixing rod is locked into the first shoulder screw.

10. The damping and buffering module for aircraft ski-type landing gear according to claim 1, characterized in that: The second ear piece faces the ski tube on the opposite side.

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