Main landing gear and aircraft

Abstract

The present invention discloses a main landing gear and an aircraft, wherein the main landing gear comprises two wheel groups, a connecting shaft and two support plates; each of the wheel groups comprises at least one tire, the two ends of the connecting shaft are connected to the two wheel groups one-to-one, the support plate has a first connecting end and a second connecting end opposite to each other, the first connecting ends of the two support plates are fixedly connected to the connecting shaft, and the second connecting ends of the two support plates are used for hinged connection with the fuselage; wherein the cross section of the support plate along the direction perpendicular to its own plate surface gradually expands from the first connecting end to the second connecting end, and the two support plates are arranged oppositely, the relative position distance between the two support plates increases from the second connecting end to the first connecting end, and the two wheel groups are respectively located on the side of the two support plates facing away from each other. The technical solution of the present invention not only enhances the strength and stability of the landing gear, improves the stability and safety of aircraft take-off and landing, but also reduces the weight of the landing gear.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a main landing gear and an aircraft. Background Art

[0002] The landing gear is a very important mechanism on the aircraft body. The landing gear is used to provide ground support for the aircraft's takeoff, taxiing and landing. The stability of the landing gear plays a decisive role in the safety of the aircraft's takeoff and landing. The landing gear of light aircraft is divided into fixed and retractable types. The retractable landing gear is generally configured in high-end light aircraft, and its wheel group structure and control mechanism are relatively complex; the fixed landing gear is commonly used in most light aircraft, generally including a front double wheel group and a rear single wheel group. At present, the main landing gear of light aircraft on the market is mostly made of metal or composite materials, which increases the production cost and the overall weight of the aircraft, and is not easy to take off in short distances. In addition, the front double wheel group is mostly located under the wing, and each is connected to the fuselage only by a connecting rod, without other auxiliary connection structures, and the strength and stability are insufficient. When such aircraft take off and land in complex terrain environments, such as on the uneven ground of beaches and mountains, the connecting rod of the wheel group cannot withstand the very large impact force and breaks, seriously affecting the safety of flight. Summary of the invention

[0003] The main purpose of the present invention is to provide a main landing gear, aiming to enhance the strength and stability of the landing gear, improve the stability and safety of aircraft take-off and landing, and reduce the weight of the landing gear.

[0004] To achieve the above-mentioned object, the main landing gear proposed by the present invention is applied to an aircraft, and the aircraft includes a body, including:

[0005] Two wheel sets, each of the wheel sets includes at least one tire;

[0006] A connecting shaft, both ends of which are connected to the two wheel sets in a one-to-one manner; and

[0007] Two support plates, each of which has a first connecting end and a second connecting end opposite to the other, the first connecting ends of the two support plates being fixedly connected to the connecting shaft, and the second connecting ends of the two support plates being used for being hinged to the machine body;

[0008] Among them, the cross-section of the support plate along the direction perpendicular to its own plate surface gradually expands from the first connecting end to the second connecting end, and the two support plates are arranged opposite to each other, and the relative position distance between the two support plates increases from the second connecting end to the first connecting end, and the two wheel groups are respectively located on the sides of the two support plates facing away from each other.

[0009] Optionally, the first connecting ends of the two support plates are provided with mounting holes, the connecting shaft is passed through the two mounting holes, and fixing parts are installed on the sides of the two first connecting ends facing away from each other, and the connecting shaft is fixedly connected to the first connecting ends through the fixing parts.

[0010] Optionally, a limiting sleeve is installed on the connecting shaft, and the limiting sleeve has a limiting effect on the wheel set. The limiting sleeve abuts against the fixing member and abuts against a side of the wheel set close to the support plate.

[0011] Optionally, the second connecting end is provided with a plurality of connecting holes, and an aviation hinge is fixedly connected to the connecting holes, and the second connecting end is hinged to the body through the aviation hinge.

[0012] Optionally, the main landing gear further includes:

[0013] a reinforcing connecting rod, one end of which is fixedly connected to the supporting plate, and the other end of which is connected to the connecting shaft; and

[0014] A reinforcing connecting rod, one end of which is fixedly connected to the connecting shaft, and the other end of which is hinged to the wing of the fuselage.

[0015] Optionally, the second connection end is fixedly connected with a connecting piece, one end of the reinforcing connecting rod is fixedly connected to the second connection end through the connecting piece, a positioning hole is further provided on the connecting shaft, and the other end of the reinforcing connecting rod is fixed to the positioning hole by passing a connecting pin.

[0016] Optionally, a porous sleeve is fixedly connected to the connecting shaft, the porous sleeve abuts against the side of the two wheel groups facing away from each other, one end of the reinforcement connecting rod is fixedly connected to the connecting shaft through the porous sleeve, and the other end of the reinforcement connecting rod is hinged to the wing of the body through a connecting screw.

[0017] Optionally, the support plate is formed by stacking and connecting multiple layers of raw material plates, and the raw material plates are connected and fixed by installing connecting rings.

[0018] Optionally, the material of the multiple layers of raw material boards constituting the support plate is wood material.

[0019] The present invention further provides an aircraft, comprising an aircraft body and a main landing gear as described in the above embodiment, wherein the main landing gear is fixedly mounted on the aircraft body.

[0020] The technical solution of the present invention is that in the main landing gear, two wheel groups are connected to the two ends of the connecting shaft one by one, the first connecting ends of the two support plates are fixedly connected to the connecting shaft, and the second connecting ends of the two support plates are hinged to the body. The support plates are plate-shaped and have a large force-bearing area. When the aircraft takes off and lands in a complex terrain environment, the support plates can share the impact force between the wheel group and the ground and absorb vibration, reduce the working pressure of the connecting shaft, and make the connecting shaft less likely to break, thereby extending the service life of the connecting shaft; and the cross section of the support plate along the direction perpendicular to its own plate surface gradually expands from the first connecting end to the second connecting end, thereby increasing the contact area between the support plate and the body, so that the support plate can absorb more vibration and impact force, thereby reducing the vibration of the body; in addition, the two support plates are arranged oppositely, and the relative position distance between the two support plates increases from the second connecting end to the first connecting end, thereby enhancing the stability between the support plate and the connecting shaft, and the two wheel groups are respectively located on the sides of the two support plates that are away from each other, increasing the distance between the two wheel groups, lowering the center of gravity of the aircraft, thereby improving the stability and safety of the aircraft landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0022] Figure 1 It is a structural schematic diagram of an embodiment of the main landing gear of the present invention;

[0023] Figure 2 for Figure 1 Front view of the middle main landing gear;

[0024] Figure 3 for Figure 1 A top view of the middle main landing gear;

[0025] Figure 4 for Figure 1 A schematic diagram of the structure of the support plate of the middle main landing gear;

[0026] Figure 5 for Figure 1 Schematic diagram of the structure of the connecting ring of the support plate of the middle main landing gear.

[0027] Description of Figure Numbers:

[0028]

[0029]

[0030] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0031] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0032] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" 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, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0034] The present invention provides a main landing gear 1 .

[0035] Specifically, the main landing gear 1 is a fixed landing gear used on aircraft, especially on light aircraft. The main landing gear 1 is used to provide ground support for take-off, taxiing and landing of the aircraft. A light aircraft is taken as an example for detailed description below.

[0036] Reference Figures 1 to 3 , Figure 1 It is a structural schematic diagram of an embodiment of a main landing gear 1 of the present invention; Figure 2 for Figure 1 A front view of the middle main landing gear 1; Figure 3 for Figure 1 A top view of the main landing gear 1.

[0037] In the embodiment of the present invention, the main landing gear 1 includes two wheel groups 10, a connecting shaft 20 and two support plates 30; Figure 1 As shown, each wheel group 10 includes at least one tire, which can be one, two or more tires, and multiple tires can be arranged in series. The number of tires can be determined according to the parameters of the aircraft itself, the specific purpose of the aircraft and the specific flight environment. For general private light aircraft, the tires of each wheel group 10 of the main landing gear 1 are set as few as possible, which can reduce the weight of the aircraft and enable the aircraft to take off quickly on a short runway; while for light aircraft with larger size and heavier weight, such as light aircraft used to transport cargo, each wheel group 10 of its main landing gear 1 can be provided with multiple tires, and multiple tires can increase the contact area between the tire and the ground, reduce the impact force between the aircraft and the ground when landing, and reduce vibration.

[0038] The two ends of the connecting shaft 20 are connected one-to-one with the two wheel groups 10, and the two wheel groups 10 can rotate around the connecting shaft 20. It can be understood that in order to prevent the connecting shaft 20 from bending and deforming during frequent take-offs and landings, and to prevent the connecting shaft 20 from being broken due to excessive impact load, the connecting shaft 20 is made of high-strength and high-toughness materials to extend the overall service life of the main landing gear 1.

[0039] Reference Figure 1 and Figure 4 The support plate 30 has a first connecting end 310 and a second connecting end 320 opposite to each other. The first connecting ends 310 of the two support plates 30 are fixedly connected to the connecting shaft 20, and the second connecting ends 320 of the two support plates 30 are hinged to the fuselage. The support plate 30 is used to support the connecting shaft 20. The support plate 30 is a plate-shaped structure with a large force-bearing area. It can share the impact force between the wheel set 10 and the ground transmitted by the connecting shaft 20, prevent the connecting shaft 20 from frequently bearing excessive impact loads and reducing the service life, and enhance the overall strength of the main landing gear 1. Furthermore, the cross section of the support plate 30 along the direction perpendicular to its own plate surface gradually expands from the first connecting end 310 to the second connecting end 320. Such a configuration allows the end of the support plate 30 connected to the fuselage to have a larger contact area, which can absorb more impact force and vibration, thereby reducing excessive vibration transmitted to the aircraft fuselage and improving the comfort of the driver.

[0040] Reference Figure 1The two support plates 30 are arranged opposite to each other, and the relative position distance between the two support plates 30 increases from the second connection end 320 to the first connection end 310. The relative distance between the first connection ends 310 of the two support plates 30 is large, while the relative distance between the second connection ends 320 of the two support plates 30 is small, so that the two support plates 30, the connecting shaft 20 and the fuselage are connected in a "trapezoidal" shape, thereby enhancing the stability of the support plates 30 and the connecting shaft 20. Such an arrangement can protect the support plates 30 themselves, so that the component force of the connecting shaft 20 acting on the support plates 30 falls on the support plates 30, reducing the bending deformation of the support plates; at the same time, the two wheel groups 10 are respectively located on the sides of the two support plates 30 that are away from each other, so that the wheelbase of the two wheel groups 10 is large enough, thereby lowering the center of gravity of the aircraft, so that the aircraft can land more stably on the ground when landing, and prevent rollover.

[0041] In the present invention, in the main landing gear 1, two wheels 10 are connected to the two ends of the connecting shaft 20 one by one, the first connecting ends 310 of the two support plates 30 are fixedly connected to the connecting shaft 20, and the second connecting ends 320 of the two support plates 30 are hinged to the body. The support plates 30 are plate-shaped and have a large force-bearing area. When the aircraft takes off and lands in a complex terrain environment, the support plates 30 can share the impact force between the wheels 10 and the ground and absorb vibration, thereby reducing the working pressure of the connecting shaft 20, making the connecting shaft 20 less likely to break, thereby extending the service life of the connecting shaft 20; moreover, the cross section of the support plate 30 along the direction perpendicular to its own plate surface It gradually expands from the first connection end 310 to the second connection end 320, thereby increasing the contact area between the support plate 30 and the body, so that the support plate 30 can absorb more vibration and impact force, thereby reducing the vibration of the body; in addition, the two support plates 30 are arranged opposite to each other, and the relative position distance between the two support plates 30 increases from the second connection end 320 to the first connection end 310, thereby enhancing the stability between the support plate 30 and the connecting shaft 20, and the two wheel groups 10 are respectively located on the sides of the two support plates 30 that are away from each other, increasing the distance between the two wheel groups 10, lowering the center of gravity of the aircraft, thereby improving the stability of the aircraft landing.

[0042] Reference Figure 4 The first connection end 310 of the support plate 30 is provided with a mounting hole 330, and the connecting shaft 20 is inserted into the mounting hole 330. Since the relative position distance of the two support plates 30 is set to increase from the second connection end 320 to the first connection end 310, the mounting hole 330 and the support plate 30 are opened at an angle, thereby increasing the effective contact area between the mounting hole 330 and the connecting shaft 20, which can reduce the impact load and reduce the bending deformation of the connecting shaft 20. A fixing member 340 is also installed on the side of the first connection ends 310 of the two support plates 30 that are away from each other, and the connecting shaft 20 is fixed to the first connection end 310 of the support plate 30 through the fixing member 340.

[0043] Understandably, referring to Figure 1 and Figure 2 , a limiting sleeve 210 is fixedly installed on the connecting shaft 20, and the limiting sleeve 210 limits the wheel set 10, so that the wheel set 10 is limited to a fixed position on the connecting shaft 20 and rotates around the connecting shaft 20 to prevent lateral displacement. In the embodiment of the present application, the limiting sleeve 210 abuts against the fixing member 340 and abuts against a side of the wheel set 10 close to the support plate 30, so that the wheel set 10 is limited to the side of the two support plates 30 facing away from each other. Among them, the limiting sleeve 210 and the connecting shaft 20 can be connected by interference fit or by screws. In order to facilitate installation and disassembly during later maintenance, the embodiment of the present application preferably adopts screw connection.

[0044] Reference Figure 1 and Figure 4 The second connection end 320 is provided with a plurality of connection holes 350, and connection screws are passed through the connection holes 350 to fix the connection with aviation hinges 360. The support plate 30 is hinged to the aircraft body through the aviation hinges 360. The support plate 30 and the body are hinged with the aviation hinges 360, which not only makes it easy to install and disassemble the support plate 30, but also can generate a small rotation to release the deformation of the support plate 30 during the take-off and landing of the aircraft.

[0045] Reference Figures 1 to 3 In order to further enhance the strength and stability of the main landing gear 1, the main landing gear 1 further includes a reinforcing link 40 and a reinforcing link 50. One end of the reinforcing link 40 is fixedly connected to the support plate 30, and the other end is fixedly connected to the connecting shaft 20. One end of the reinforcing link 50 is fixedly connected to the connecting shaft 20, and the other end is hinged to the wing of the aircraft. It can be understood that the reinforcing link 40 and the reinforcing link 50 can be provided in multiple groups.

[0046] Further, refer to Figures 1 to 3 The second connecting end 320 of the support plate 30 is fixedly connected to the connecting piece 370, one end of the reinforcing link 40 is hinged to the connecting piece 370, a positioning hole 220 is opened in the middle of the connecting shaft 20, and the other end of the reinforcing link 40 is fixedly connected to the connecting shaft 20 by passing a connecting pin through the positioning hole 220. In this way, a "triangle" structure is formed between the reinforcing link 40, the support plate 30 and the connecting shaft 20, which further enhances the strength and stability between the support plate 30 and the connecting shaft 20, and further prevents the connecting shaft 20 and the support plate 30 from excessive bending deformation.

[0047] Continue to refer to Figures 1 to 3A porous sleeve 230 is fixedly connected to the connecting shaft 20, and the porous sleeve 230 is located at both ends of the connecting shaft 20 and abuts against the sides of the two wheel groups 10 that are away from each other. One end of the reinforcement connecting rod 50 is fixedly connected to the connecting shaft 20 through the porous sleeve 230, and the other end of the reinforcement connecting rod 50 is hinged to the wing of the aircraft. Similarly, a "triangle" structure is formed between the reinforcement connecting rod 50, the wing and the fuselage, which can enhance stability, and the reinforcement connecting rod 50 can transfer part of the impact force received by the connecting shaft 20 to the wing, thereby further reducing the impact load borne by the connecting shaft 20 and the support plate 30.

[0048] Furthermore, in order to reduce the production cost of the support plate 30, the support plate 30 can be formed by stacking and connecting multiple layers of raw material plates, and each layer of raw material plates is connected and fixed by a connecting ring 380. The connecting ring 380 includes two connecting parts 382, ​​two sleeve parts 381 and a deformation part 383, wherein the connecting part 382, ​​the sleeve part 381 and the deformation part 383 are connected in sequence, and the two sleeve parts 381 and the two connecting parts 382 are symmetrically arranged. The sleeve part 381 corresponds to the shape of the raw material plate and wraps the outer periphery of the raw material plate. The connecting part 382 is provided with a bolt hole and the raw material plate is connected and tightened by connecting bolts. The deformation part 383 is connected between the sleeve parts 381. The deformation part 383 can produce elastic deformation to increase or decrease the relative distance between the two sleeve parts 381 and the two connecting parts 382, ​​so that the connecting ring 380 can adapt to raw material plates of different thicknesses and has high versatility.

[0049] It can be understood that in order to reduce the weight of the main landing gear 1 and thus reduce the overall weight of the aircraft, making it easier for the aircraft to take off, especially to achieve rapid take-off on a short runway, the raw material board can be made of wood material, which is light in weight, easy to process, extremely low in cost, and can be mass-produced. In addition, the strength of the support plate can be greatly enhanced by stacking the wood boards.

[0050] The present invention also provides an aircraft, which includes a fuselage and a main landing gear 1. The specific structure of the main landing gear 1 refers to the above embodiment. Since the present aircraft adopts all the technical solutions of all the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be described one by one here. The main landing gear 1 is fixedly installed on the fuselage.

[0051] The above descriptions are only optional embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A main landing gear, applied to an aircraft, the aircraft comprising a fuselage, characterized in that: include: Two wheel sets, each of the wheel sets includes at least one tire; A connecting shaft, both ends of which are connected to the two wheel sets in a one-to-one manner; and Two support plates, each of which has a first connecting end and a second connecting end opposite to the other, the first connecting ends of the two support plates being fixedly connected to the connecting shaft, and the second connecting ends of the two support plates being used for being hinged to the machine body; Wherein, the cross section of the support plate along the direction perpendicular to the plate surface thereof gradually expands from the first connection end to the second connection end, and the two support plates are arranged opposite to each other, and the relative position distance between the two support plates increases from the second connection end to the first connection end, and the two wheel sets are respectively located on the sides of the two support plates that are away from each other; The main landing gear further comprises a reinforcing link and a reinforcing link, one end of the reinforcing link is fixedly connected to the support plate, and the other end is connected to the connecting shaft; one end of the reinforcing link is fixedly connected to the connecting shaft, and the other end is hinged to the wing of the fuselage; The second connecting end is fixedly connected with a connecting piece, one end of the reinforcing connecting rod is fixedly connected with the second connecting end through the connecting piece, a positioning hole is also opened on the connecting shaft, and the other end of the reinforcing connecting rod is fixed at the positioning hole by passing a connecting pin; A porous sleeve is fixedly connected to the connecting shaft, one end of the reinforcing connecting rod is fixedly connected to the connecting shaft via the porous sleeve, and the other end of the reinforcing connecting rod is hinged to the wing of the body via a connecting screw.

2. The main landing gear according to claim 1, characterized in that: The first connecting ends of the two support plates are provided with mounting holes, the connecting shaft is passed through the two mounting holes, and fixing parts are installed on the sides of the two first connecting ends facing away from each other, and the connecting shaft is fixedly connected to the first connecting ends through the fixing parts.

3. The main landing gear according to claim 2, characterized in that: A limiting sleeve is installed on the connecting shaft, and the limiting sleeve has a limiting effect on the wheel set. The limiting sleeve abuts against the fixing member and abuts against a side of the wheel set close to the support plate.

4. The main landing gear according to claim 1, characterized in that: The second connecting end is provided with a plurality of connecting holes, and an aviation hinge is fixedly connected to the connecting holes. The second connecting end is hinged to the body through the aviation hinge.

5. The main landing gear according to claim 1, characterized in that: The porous sleeve is in contact with the sides of the two wheel sets which are away from each other.

6. The main landing gear according to claim 1, characterized in that: The support plate is formed by stacking and connecting multiple layers of raw material plates, and the raw material plates are connected and fixed by installing connecting rings.

7. The main landing gear according to claim 6, characterized in that The material of the multiple layers of raw material boards constituting the support plate is wood material.

8. An aircraft, characterized in that: It comprises a fuselage and a main landing gear as described in claims 1 to 7, wherein the main landing gear is fixedly mounted on the fuselage.

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