WO2018090810A1

WO2018090810A1 - Landing gear and aircraft

Info

Publication number: WO2018090810A1
Application number: PCT/CN2017/107969
Authority: WO
Inventors: 刘若鹏; 栾琳; 潘均英; 黄兹驰
Original assignee: 深圳光启空间技术有限公司
Priority date: 2016-11-17
Filing date: 2017-10-27
Publication date: 2018-05-24

Abstract

Disclosed are a landing gear (100) and an aircraft. The landing gear (100) is mounted on the aircraft and is used for take-off and landing of the aircraft. The landing gear (100) comprises: an elastic buffer member connected to the aircraft, and a supporting structure (150) rotatably connected to the elastic buffer member, wherein the supporting structure (150) comprises an outer side face used for contacting the ground, and the outer side face is a smooth cambered surface. When the aircraft lands, the elastic buffer member absorbs impact energy during descent of the aircraft, providing better buffering and damping effects when the aircraft lands. An outer side face, used for contacting the ground, of the supporting structure (150) is a smooth cambered surface, so that the aircraft lands more stably and smoothly, and the invention has a simple structure and is light in weight.

Description

Landing gear and aircraft technology

[0001] The present invention relates to the field of aircraft and, more particularly, to a landing gear and an aircraft.

Background technique

[0002] The landing gear is an accessory device used in the lower part of the aircraft for take-off landing or ground taxiing to support the aircraft and for ground movement, and is an integral part of the aircraft.

technical problem

[0003] A rear sill landing gear and a damper device are used in the prior art, but the device is a wheeled landing gear and cannot be converted into a ski-type landing gear, and the spring stroke is short, and the shock absorbing effect is not good. Another prior art uses a resilient ball damper as a cushioning device to provide cushioning for the drone landing gear, but the device also has a short stroke and can only be used for small drones, if installed in a large unmanned The weight of the on-board structure will become very heavy. In summary, the aircraft has higher requirements for the cushioning effect of the landing gear.

Problem solution

Technical solution

[0004] According to an aspect of the present invention, a landing gear for landing of an aircraft is provided, the landing gear comprising: an elastic cushioning member coupled to the aircraft; and a support structure rotatably coupled to the elastic cushioning member The support structure includes an outer side surface for contacting the ground, and the outer side surface is a smooth curved surface.

In accordance with another aspect of the present invention, an aircraft is provided that is provided with a landing gear as described in the preceding paragraph.

According to the landing gear and the aircraft of the present invention, the elastic cushioning member absorbs the impact energy of the descending weir of the aircraft during the landing of the aircraft, thereby providing a better cushioning and damping effect for the aircraft landing gear. The support structure is used for the smooth contact with the outer surface of the ground, which makes the landing of the aircraft more stable and smooth, and the structure is simple and light.

Advantageous effects of the invention

Beneficial effect

In a preferred embodiment, the elastic buffer member multi-link mechanism and the elastic member, the multi-link mechanism may be The four-bar linkage mechanism, the elastic member may be a tension spring. The landing gear can utilize the quick return characteristics of the four-bar mechanism to provide a certain take-off acceleration for the aircraft during the take-off of the aircraft by the contraction of the spring. Brief description of the drawing

DRAWINGS

1 shows a structural schematic view of a landing gear landing on an aircraft in accordance with an embodiment of the present invention.

2 shows a schematic view of a structure in which a landing gear is raised in an aircraft according to an embodiment of the present invention.

Embodiments of the invention

[0010] The present invention will be described in more detail below with reference to the accompanying drawings. For the sake of clarity, the various parts in the figures are not drawn to scale. Moreover, some well-known parts may not be shown. Many specific details of the invention are described below, but the invention may be practiced without these specific details, as will be understood by those skilled in the art.

[0011] It should be understood that, in describing the structure of the device, when a layer or a region is referred to as being "above" or "above" another layer, another region may be directly located at another layer or another region. The above, or other layers or regions are included between the other layer and another region. Also, if the device is flipped, the layer, one area will be located on the other layer, and the other area "below" or "below".

[0012] If for the sake of description directly above another layer, another region, this article will use the expression "A directly above B" or "A is above and adjacent to B". In the present application, "A directly in B" means that A is located in B, and A is directly adjacent to B.

[0013] The present invention first provides a landing gear for providing support for an aircraft landing gear, comprising: an elastic cushioning member and a support structure. Wherein, the elastic buffering member is connected to the aircraft, and the supporting structure is rotatably connected to the elastic buffering member. The support structure includes an outer side for contacting the ground, the outer side being a smooth arc. The landing gear can be installed at the bottom of the aircraft. After the aircraft is lowered, the elastic buffering member absorbs the impact energy of the descending raft of the aircraft, thereby providing a better cushioning and damping effect for the aircraft landing raft, and the outer side of the supporting structure is smooth. The curved surface makes the aircraft fall and rise and has a smooth transition process, and the fuselage is more stable.

[0014] An embodiment of the landing gear of the present invention will be specifically described below with reference to FIGS. 1 and 2, and the landing gear of the present invention is disposed on an aircraft, although not shown. 1 and 2 are schematic structural views of a landing gear according to an embodiment of the present invention, wherein FIG. 1 is a structure after the aircraft is landed, and FIG. 2 is a structure after the aircraft is taken off. The landing gear 100 includes an elastic cushioning member for connection with the aircraft and a support structure 150 rotatably coupled to the elastic cushioning member. The support structure 150 includes an outer side surface for contacting the ground surface, the outer side surface being a smooth curved surface.

[0016] The elastic cushioning member may include: a multi-link mechanism and an elastic member, wherein the multi-link mechanism includes a plurality of links, at least one of the plurality of links being coupled to the aircraft. An elastic member is coupled between the plurality of links for buffering relative movement between the plurality of links.

[0017] Further, the multi-link mechanism further includes: a first link 110, a second link 120, a third link 13 0, and a fourth link 140; wherein, the first link 110 is used Installed on the aircraft, in the present embodiment, the first links 110 are horizontally arranged. One ends of the second link 120 and the fourth link 140 are connected to the first link 110, and the other end is connected to the third link 130 located below the first link 110 to form a planar four-bar linkage.

[0018] In a preferred embodiment, the first link 110, the second link 120, and the fourth link 140 are all long straight rods; the second link 120 is hinged at the midpoint of the first link 110 The fourth link is hinged at a quarter of the left end of the first link 110, and the fourth link 140 and the second link 120 are further hinged to the leftmost and rightmost ends of the third link 130; The distance between the connection points of the second link 120 and the fourth link 140 on a link 110 is greater than the distance between the two links on the third link 130.

[0019] It can be understood that the plurality of links included in the multi-link mechanism are not limited to a specific rod-shaped structure, as long as it is a structure that substantially functions as a connecting rod, for example, a tubular structure, a long strip structure, Both are substantially identical to the multi-link mechanism of the present invention, and the structural form and materials used can be selected according to the strength requirements of the load bearing.

[0020] Further, the support structure 150 is formed on the third link 130 and rotates with the third link 130. In this embodiment, the support structure 150 has a sickle shape and has an arcuate outer side surface. As described above, the first link 110 is fixed, and the second link 120 and the fourth link 140 can respectively rotate around the hinge point of the first link 110 And the free ends of the two are hinged to both ends of the third link 130 such that the support structure 150 can follow the third link 130 at the second link 120 and The movement of the fourth link 140 under the constraint is described. Moreover, since the outer side surface of the support structure 150 is a smooth curved surface, it is applied to the aircraft and is provided for the slow landing of the aircraft. The punching effect is better. For example, the landing gear 100 is mounted on a vertical take-off and landing rotor drone, and when the rotor drone is lowered to the ground, the landing gear 100 includes a support structure 150 that is in contact with the ground, in which there is no The man-machine slowly descends, and the contact points of the arc-shaped outer side surface with the ground are sequentially contacted along the smooth curved surface, so that the landing of the rotor drone is more stable.

[0021] Of course, it can be understood that the support structure 150 of the embodiment has a sickle shape, and those skilled in the art can implement various shapes of support structures as long as they are used for contact with the ground. The outer side is smooth and curved.

[0022] It should be further noted that the lower end of the support structure 150 may directly contact the ground, or a horizontal support rod may be installed at a lower end thereof to form a ski-type landing gear, or a roller may be installed at a lower end thereof, according to the aircraft. The takeoff and landing characteristics are selected such as vertical takeoff and landing or taxi takeoff and landing.

[0023] Further, the elastic member adopts a tension spring 160, and two ends of the tension spring 160 are respectively connected to the first extension portion 121 of the second link 120 and the third link 130, and the function thereof is mainly The relative movement of the third link 130 is buffered. Preferably, the first extension portion 121 and the second link 120 form a "7"-shaped structure, and the corner thereof is hinged with the first link, and the third link 130 is at the fourth link 140 The hinge has a second extending portion 131. The two ends of the tension spring 160 are respectively connected to the first extending portion 121 and the second extending portion 131. The first extending portion 121 and the second extending portion 131 can be substantially The opposite directions are provided to facilitate the connection of the tension springs 160. The first extending portion 121 and the second extending portion 131 have through holes, and hooks at both ends of the tension spring 160 can be hooked with the through holes, thereby realizing the tension spring 160 and the The connection of the multi-link mechanism buffers the relative movement between the links included in the multi-link mechanism.

[0024] It should be noted that the elastic member is not limited to the use of the tension spring 160. Accordingly, the connection manner between the elastic member and the connecting rod included in the multi-link mechanism is not limited to the embodiment. The hook is hooked to the through hole, and the elastic member is not limited to being connected to the second link 120 and the third link 130. The purpose of the resilient member is to cushion the relative motion between the plurality of links, thereby allowing the aircraft to land smoothly.

[0025] The elastic cushioning member further includes a limiting structure for preventing an excessive stroke of the plurality of links from moving relative to each other.

In this embodiment, the first extending portion 121 and the main body of the second link 120 are disposed at a predetermined angle, so that the second link 120 is rotated to a predetermined position, the first extending portion 121 and the Flight In contact with the first extension portion 121, the first extension portion 121 is rigid, and when the first extension portion 121 is in contact with the aircraft, the multi-link mechanism cannot continue to move, and the support structure 150 cannot continue to rotate. Steady state. In the above embodiment, the first extension portion 121 also serves as a limiting structure. The dotted line in Fig. 1 shows the outline of the portion of the first extension portion 121 that is blocked by the first link 110. For convenience of explanation, the aircraft to which the landing gear 100 belongs is lowered, and the end of the support structure 150 first contacts the ground. The contact points of the arc-shaped outer side surface and the ground are sequentially contacted along the smooth curved surface, and the second link 120 rotates along the hinge point of the first link 110 to rotate with the hinge point, when rotated to FIG. In position 吋, the first extension portion 121 is in contact with the aircraft, so that the second link 120 can no longer rotate in the direction of the needle in FIG. 1 to play a limiting role.

[0026] It is to be understood that the limiting structure is not limited to the first extending portion 121, and the limiting function may be implemented by setting a limiting screw, a limiting protrusion, and the like on the plurality of connecting links. The purpose is to prevent the stroke of the relative movement of the plurality of links from being excessive.

[0027] During the landing of the aircraft, the support structure 150 moves together with the third link 130, and the first extension portion 121 and the second extension portion 131 are correspondingly moved. The tension spring 160 is gradually elongated during the descending process of the aircraft, absorbing the impact energy of the aircraft descending, and buffering the relative movement of the links, so that the aircraft is more stable. Preferably, the third link 130 can be perpendicular to the ground during the movement to provide a better support effect.

[0028] In an aircraft lifter mounted with the above-described landing gear 100, referring to FIG. 2, the tension spring 160 is contracted during the lifting process, utilizing the snapback characteristic of the four-bar linkage mechanism, the tension spring The third link 130 is pulled to move along with the support structure 150 to provide a certain takeoff acceleration for the aircraft.

[0029] An embodiment of the present invention further provides an aircraft, and the bottom of the aircraft is provided with the landing gear of the above embodiment. The elastic cushioning member of the landing gear absorbs the impact energy of the descending raft of the aircraft to provide a better cushioning and damping effect for the aircraft landing raft. The supporting structure is used for the smooth contact with the outer surface of the ground, which makes the landing of the aircraft more stable and smooth. Through the cooperation of the four-bar linkage mechanism and the elastic member, the aircraft is provided with a certain take-off acceleration.

[0030] The landing gear may be directly in contact with the ground on the aircraft, or a horizontal support rod may be installed at the lower end of the support structure 150 to form a ski-type landing gear, or a roller may be installed at the lower end thereof, depending on the take-off and landing characteristics of the aircraft. Choose between vertical takeoff and landing or taxi takeoff and landing. [0031] It should be noted that, in this context, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply these entities. There is any such actual relationship or order between operations. Furthermore, the terms "including", "comprising" or "comprising" or "comprising" are intended to encompass a non-exclusive inclusion, such that a process, method, article, or device that includes a plurality of elements includes not only those elements but also Other elements, or elements that are inherent to such a process, method, item, or device. An element that is defined by the phrase "comprising a ..." does not exclude the presence of additional elements in the process, method, item, or device that comprises the element.

[0032] The embodiments in accordance with the present invention are not described in detail, and the invention is not limited to the specific embodiments. Obviously, many modifications and variations are possible in light of the above description. The present invention has been chosen and described in detail to explain the embodiments of the present invention and the embodiments of the invention. The invention is to be limited only by the scope of the appended claims and the appended claims.

Claims

Claim

[Claim 1] A landing gear for landing and landing of an aircraft, characterized in that: the landing gear comprises: an elastic cushioning member coupled to the aircraft;

a support structure, rotatably connected to the elastic buffering member,

Wherein, the support structure comprises an outer side surface for contacting the ground, and the outer side surface is a smooth curved surface.

[Claim 2] The landing gear according to claim 1, wherein the elastic cushioning member includes a multi-link mechanism including a plurality of links, at least one of the plurality of links and the aircraft Connection;

An elastic member is coupled between the plurality of links for buffering relative movement between the plurality of links.

[Claim 3] The landing gear according to claim 2, wherein the multi-link mechanism includes

a first link, a second link, a third link, and a fourth link, wherein the first link is mounted on the aircraft, and one end of the second link and the fourth link are connected On one link, the other end is connected to a third link located below the first link.

[Claim 4] The landing gear according to claim 3, wherein the support structure is integrally formed on the third link and rotates with the third link.

[Claim 5] The landing gear according to claim 3, wherein the elastic member is a tension spring.

[Claim 6] The landing gear according to claim 5, wherein both ends of the tension spring are connected to the second link and the third link, respectively.

[Claim 7] The landing gear according to claim 6, wherein the second link has a first extension portion at a hinge with the first link, and the third link is The hinge of the fourth link has a second extension portion,

Both ends of the tension spring are respectively connected to the first extension portion and the second extension portion.

[Claim 8] The landing gear according to claim 2, wherein the elastic cushioning member is further included Includes:

The limiting structure is configured to prevent an excessive stroke of the plurality of links from moving relative to each other.

[Claim 9] The landing gear according to claim 7, wherein the first extension portion is disposed at a predetermined angle with a body of the second link, such that the second link is rotated to a predetermined position The first extension is in contact with the aircraft.

[Claim 10] The landing gear according to claim 1, wherein the support structure has a sickle shape

[Aspect 11] An aircraft characterized by being provided with the landing gear according to any one of claims 1 to 9.