WO2018214626A1 - 用于垂直起降飞行器的起落架 - Google Patents

用于垂直起降飞行器的起落架 Download PDF

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Publication number
WO2018214626A1
WO2018214626A1 PCT/CN2018/079744 CN2018079744W WO2018214626A1 WO 2018214626 A1 WO2018214626 A1 WO 2018214626A1 CN 2018079744 W CN2018079744 W CN 2018079744W WO 2018214626 A1 WO2018214626 A1 WO 2018214626A1
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WO
WIPO (PCT)
Prior art keywords
connecting plate
landing gear
landing
main body
top connecting
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PCT/CN2018/079744
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English (en)
French (fr)
Inventor
刘若鹏
栾琳
潘均英
Original Assignee
深圳光启合众科技有限公司
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Application filed by 深圳光启合众科技有限公司 filed Critical 深圳光启合众科技有限公司
Publication of WO2018214626A1 publication Critical patent/WO2018214626A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/62—Spring shock-absorbers; Springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs

Definitions

  • the present invention relates to the field of aircraft technology, and more particularly to a landing gear for a vertical take-off and landing aircraft.
  • the landing gear For a vertical take-off and landing aircraft, when it is landed with a load, the landing gear is usually subjected to a large impact energy. Especially in the case of unconventional landing, the quality of the landing gear plays a vital role in the protection of the aircraft.
  • An existing landing gear that can be used in a helicopter can be adapted for multi-terrain, which has four legs. When landing, there are only four legs on the force surface of the aircraft and the ground. The force surface is small, the impact strength is large, and when it is abnormally landed or landed, it may cause damage to the aircraft and damage on the aircraft.
  • an object of the present invention is to provide a landing gear for a vertical take-off and landing aircraft that has a large contact area with the ground.
  • the present invention provides a vertical landing gear comprising: a top connecting plate for connecting with a vertical take-off and landing aircraft, and a bottom connecting plate disposed opposite the top connecting plate, wherein the top connecting plate Connected to the bottom connecting plate by a plurality of equiangularly distributed main body struts, the main body strut includes a horizontally disposed first shank segment, and a second shank segment extending from the first shank segment and extending the second shank segment Forming an angle with the first rod segment.
  • the central axis of the top web coincides with the central axis of the bottom web
  • the landing gear comprising a suspension structure, the opposite ends of the suspension structure being respectively connected to the top web and the bottom web.
  • the suspension structure comprises a sleeve disposed in a central axis direction of the top connecting plate and an elastic member housed in the sleeve, one end of the sleeve being mounted on the upper surface of the bottom connecting plate, the elastic member
  • the telescopic movement is possible with respect to the sleeve in the direction of the central axis of the top web.
  • the lower surface of the top connecting plate is provided with a cylindrical portion, and opposite ends of the elastic member are respectively pressed against the inner bottom surface of the sleeve and the lower surface of the cylindrical portion, and the cylindrical portion at least partially protrudes Inside the sleeve.
  • the number of main body struts is four, four main struts are arranged equiangularly around the central axis of the top connecting plate, and the projection of the four main struts on the horizontal surface is a cross-shaped structure .
  • a transition section is formed between the first pole section and the second pole section, the transition section being an angled rounded corner.
  • the body strut further comprises a connecting section extending horizontally from the second pole section, the connecting section being fixedly connected to the top connecting plate, the connecting section being parallel to the first pole section.
  • the side wall of the top connecting plate is recessed inwardly with a plurality of first card slots, and the plurality of connecting segments are respectively inserted into the plurality of first card slots, and are connected to the top connecting plate by the first bolts.
  • the side wall of the bottom connecting plate is recessed inwardly with a plurality of second card slots, and the free ends of the plurality of first rod segments are respectively inserted into the plurality of second card slots, and are passed through the second bolt
  • the bottom connection plate is connected.
  • the bottom surface of the first rod segment and the bottom connecting plate are respectively provided with a first buffer pad and a second buffer pad, and the bottom planes of the first buffer pad and the second buffer pad are at the same horizontal plane.
  • the invention relates to a landing gear for a vertical take-off and landing aircraft, wherein the main body support for supporting the aircraft comprises a first pole section coplanar with the bottom connecting plate, so that the bottom connecting plate and the first pole section are in contact with the ground , increasing the contact area between the landing gear and the ground when landing, reducing the impact strength on the fuselage and the load on the aircraft when landing; and, because the second pole of the main pole is inclined away from the main pole, the first pole
  • the segment can have a longer length, further increasing the contact area of the landing gear with the ground when the aircraft is landing, effectively absorbing the impact energy at the time of landing, thereby ensuring a safe and stable landing of the aircraft.
  • Figure 1 is a perspective view of a landing gear in accordance with one embodiment of the present invention.
  • Figure 2 is a cross-sectional view of the landing gear in accordance with one embodiment of the present invention.
  • Figure 3 is a plan view of the landing gear in accordance with one embodiment of the present invention.
  • FIG. 4 is a schematic illustration of a landing gear during an abnormal landing, in accordance with one embodiment of the present invention.
  • the present invention provides a landing gear for a vertical take-off and landing aircraft, comprising: a top connecting plate 1 for connecting with a vertical take-off and landing aircraft, and a bottom opposite to the top connecting plate. Connecting plate 5.
  • the top connecting plate 1 and the bottom connecting plate 5 are connected by a plurality of equiangularly distributed main body struts 2, and the main body struts 2 comprise a horizontally disposed first shank segment and a bent portion extending from the first shank segment
  • the second rod segment forms an angle with the first rod segment.
  • the main body strut 2 is a composite material of metal material or carbon fiber, and an angle formed between the first rod segment and the second rod segment has a resilience between the first rod segment and the second rod segment, thereby having a certain buffering function.
  • the main body strut 2 for supporting the aircraft includes a first pole section coplanar with the bottom connecting plate 5, that is, the bottom connecting plate 5 and the first pole The segments are on the same level.
  • the bottom connecting plate 5 and the first rod segment are in contact with the ground, which increases the contact area between the landing gear and the ground when landing, and reduces the impact strength on the fuselage and the onboard load when landing; and, due to the main body branch
  • the first rod segment of the rod 2 is inclined away from the main body rod 2, so that the first rod portion can have a longer length, further increasing the contact area of the landing gear with the ground when the aircraft is landing, effectively absorbing the impact energy at the time of landing, thereby Ensure the safe and smooth landing of the aircraft.
  • the second rod segment of the main body strut 2 extends obliquely from the plane of the top connecting plate 1 to the plane of the bottom connecting plate 5, so as to increase the contact area of the bottom connecting plate 5 and the first rod segment, and ensure the smoothness of the aircraft. Landing.
  • the vertical take-off and landing aircraft in the above embodiments may include, but is not limited to, a small and medium-sized drone and a manned aircraft.
  • the central axis of the top connecting plate 1 coincides with the central axis of the bottom connecting plate 5, and in other words, the top connecting plate 1 and the bottom connecting plate 5 are disposed opposite to each other and parallel to each other, so that the overall structure of the landing gear is further improved. stable.
  • the landing gear includes a suspension structure 6, and opposite ends of the suspension structure 6 are respectively connected to the top connecting plate 1 and the bottom connecting plate 5. In this way, when the aircraft is landing, the suspension structure 6 can effectively absorb the impact energy at the time of landing, thereby ensuring a safe and stable landing of the aircraft.
  • the suspension structure 6 includes a sleeve disposed in a central axis direction of the top connecting plate 1 and an elastic member housed in the sleeve, and one end of the sleeve is mounted on the upper surface of the bottom connecting plate 5.
  • the elastic member is telescopically movable relative to the sleeve in the direction of the central axis of the top connecting plate 1.
  • the elastic member may be an elastic functional element such as a spring or a rubber.
  • the lower surface of the top connecting plate 1 is extended downwardly with a cylindrical portion, and opposite ends of the elastic member are respectively pressed against the inner bottom surface of the sleeve and the lower surface of the cylindrical portion, and the cylindrical portion At least partially protrudes into the sleeve for pressing the elastic member to avoid deformation of the elastic member and causing buffer failure.
  • the suspension structure 6 may also include a telescoping rod in the middle and a spring disposed around or around the telescoping rod.
  • a hydraulic telescopic rod is used as the suspension structure 6.
  • the suspension structure 6 may include other structures having a shock absorbing function depending on the specific use, and the present invention is not limited thereto.
  • the number of the main body stays 2 is four, and the four main body stays 2 are equiangularly disposed around the central axis of the top connecting plate 1, and four
  • the projection of the main body strut 2 on the horizontal surface has a cross-shaped configuration.
  • the cross-shaped structure not only cushions when the aircraft is landing, but also helps the overall body to stabilize its center of gravity.
  • the body struts 2 may also be arranged asymmetrically.
  • the landing gear may include five equally spaced body struts.
  • the body strut 2 comprises a metal or alloy or composite material.
  • a transition section is formed between the first mast segment and the second mast segment, the transition segment being an angled round. Therefore, the main body strut 2 can generate a certain deformation when the aircraft is landing, and absorb part of the impact energy.
  • the second pole segment further comprises a horizontally extending connecting section, the connecting section is connected and fixed to the top connecting plate 1, and the connecting section is parallel to the first pole section, so that the two ends of the main body strut 2 are parallel
  • the top connecting plate 1 and the bottom connecting plate 5 are fixedly connected.
  • the sidewall of the top connecting plate 1 is recessed inwardly with a plurality of first card slots, and the plurality of connecting segments are respectively inserted into the plurality of first card slots, and pass through the first bolt 4 and the top connecting plate. 1 connection.
  • the number of the first bolts 4 and the main body struts 2 can be adjusted as the case may be.
  • the main body strut 2 and the top web 1 can also be connected by other means such as a connector.
  • the top connecting plate is provided with a plurality of first threaded holes, the central axis of the first threaded hole is parallel to the central axis of the connecting plate, and the free end of the connecting portion is provided with a second threaded hole, the first thread The hole is arranged to coincide with the central axis of the second threaded hole, so that the first bolt is screwed in to form a fastening connection.
  • the side wall of the bottom connecting plate 5 is recessed inwardly with a plurality of second card slots, and the free ends of the plurality of first rod segments are respectively inserted into the plurality of second card slots and passed through the second bolts. 7 is connected to the bottom connecting plate 5.
  • the bottom surface of the first rod segment and the bottom connecting plate 5 are respectively provided with a first buffer pad 8 and a second buffer pad 9, the bottom of the first buffer pad 8 and the second buffer pad 9
  • the planes are in the same horizontal plane, so that the entire bottom plane of the landing gear is in the same plane to facilitate smooth landing.
  • the first rod segment and the second rod segment are in the same plane in the vertical direction, and the two are bent in a vertical plane to form an elastic buffer space.
  • an embodiment of the present invention relates to a landing gear suitable for a vertical take-off and landing aircraft (including but not limited to a small and medium-sized unmanned aerial vehicle and a manned aircraft type), which is composed of a cross-shaped main body frame and a fourth It is composed of a connecting plate (top connecting plate 1), a five-way connecting plate (bottom connecting plate 5), a strong spring (which can also be a shock absorber), a rubber gasket and a number of screws.
  • the main body frame comprises four main body struts 2.
  • the top connecting plate 1 is an upper four-way connecting plate and includes four card slots.
  • the bottom part contains a telescopic rod, and the spring is squeezed when landing to achieve the purpose of buffering.
  • the weight of the telescopic rod can help the overall body to stabilize the center of gravity.
  • the main frame structure of the landing gear can be made of alloy or composite material and has certain toughness, and includes a total of four main body rods 2.
  • Each of the main body struts 2 is formed in an integrally formed C-like structure.
  • the main body rod 2 can be rounded or square.
  • the upper four-way connecting plate is connected to the four main body rods 2 through the first bolts 4, and the specific connection manner can be flexibly adjusted according to the type of the aircraft.
  • the top connecting plate 1 further includes a screw mounting hole 3 through which the landing gear can be fixedly coupled to the aircraft body.
  • the lower five-way connecting plate shown in FIG. 1 is connected to the four main body stays 2 via a second bolt 7.
  • the number of specific screw holes can be adjusted according to the strength.
  • the suspension structure 6 is a spring. Depending on the size and type of the aircraft, springs of different strengths or shock absorbers can be used directly.
  • a first buffer pad 8 and a second buffer pad 9 are respectively connected to the bottom of the main body strut 2 and the bottom of the five-way connecting plate, and the rubber pad can be connected to the landing gear by means of bonding, wrapping or the like.
  • the first buffer pad 8 and the second buffer pad 9 first contact the ground to provide buffer protection for the first layer. Due to the inertia, the main body of the aircraft connected to the landing gear still maintains a downward trend, and the spring or shock absorber will be pressed through the four-way connecting plate to serve as a buffer protection for the second layer. At the same time, the main body strut 2 with certain toughness will also produce a certain deformation, absorb part of the impact energy, and play the buffer protection role of the third layer.
  • the aircraft when the aircraft first landed at a certain angle or a certain angle of the landing gear, the weight and position of the four-way connecting plate and the five-way connecting plate and the suspension structure 6 connected therebetween are Similar to the stabilizing center of gravity of the tumbler, the aircraft automatically corrects the landing attitude to ensure the safe landing of the aircraft and protect the body and the load on the aircraft from damage.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
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Abstract

公开了一种用于垂直起降飞行器的起落架，其包括：用于与垂直起降飞行器连接的顶部连接板（1），以及与顶部连接板（1）相对设置的底部连接板（5），其中，顶部连接板（1）与底部连接板（5）之间通过多个等角度分布的主体支杆（2）连接，主体支杆（2）包括水平设置的第一杆段，及自第一杆段弯折延伸形成的第二杆段，第二杆段与第一杆段形成夹角。该起落架与地面接触面积较大。

Description

用于垂直起降飞行器的起落架 技术领域
本发明涉及飞行器技术领域，更具体而言，涉及一种用于垂直起降飞行器的起落架。
 背景技术
对于垂直起降的飞行器，当它带着载荷一起降落时，起落架通常要承受较大的冲击能量。尤其在非常规降落时，起落架的好坏对飞行器的保护起着至关重要的作用。
 技术问题
一种现有的可用于直升式无人机的起落架可适用于多地形，该起落架含四个支腿。降落时，飞行器与地面的受力面只有四个支腿，受力面小，冲击强度大，并且在非正常降落或带载降落时，可能造成飞行器的震伤及机上带载的损伤。
 技术解决方案
针对相关技术中存在的问题，本发明的目的在于提供一种与地面接触面积较大的用于垂直起降飞行器的起落架。
为实现上述目的，本发明提供了一种用于垂直起降飞行器，包括：用于与垂直起降飞行器连接的顶部连接板，以及与顶部连接板相对设置的底部连接板，其中，顶部连接板与底部连接板之间通过多个等角度分布的主体支杆连接，主体支杆包括水平设置的第一杆段，及自第一杆段弯折延伸形成的第二杆段，第二杆段与第一杆段形成夹角。
根据本发明的实施例，顶部连接板的中心轴线与底部连接板的中心轴线重合，起落架包括避震结构，避震结构的相对两端分别与顶部连接板和底部连接板连接。
根据本发明的实施例，避震结构包括在顶部连接板的中心轴线方向上设置的套筒及收容在套筒内的弹性元件，套筒的一端装设在底部连接板的上表面，弹性元件可在顶部连接板的中心轴线方向上相对于套筒作伸缩运动。
根据本发明的实施例，顶部连接板的下表面设有柱形部，弹性元件的相对两端分别抵压于套筒的内底面和柱形部的下表面，并且柱形部至少部分伸入套筒内。
根据本发明的实施例，主体支杆设置的数量为四根，四根主体支杆等角度地绕顶部连接板的中心轴线而设置，并且四根主体支杆在水平面上的投影呈十字形构造。
根据本发明的实施例，第一杆段与第二杆段之间形成过渡段，过渡段为夹角的倒圆角。
根据本发明的实施例，主体支杆进一步包括自第二杆段水平延伸的连接段，连接段连接固定于顶部连接板，连接段与第一杆段相互平行。
根据本发明的实施例，顶部连接板的侧壁向内凹设有多个第一卡槽，多个连接段分别对应插入多个第一卡槽，并通过第一螺栓与顶部连接板连接。
根据本发明的实施例，底部连接板的侧壁向内凹设有多个第二卡槽，多个第一杆段的自由端分别对应插入多个第二卡槽，并通过第二螺栓与底部连接板连接。
根据本发明的实施例，第一杆段和底部连接板的底面分别设置有第一缓冲垫片和第二缓冲垫片，第一缓冲垫片和第二缓冲垫片的底平面处于同一水平面。
 有益效果
本发明的有益技术效果在于：
本发明涉及的用于垂直起降飞行器的起落架，用于支撑飞行器的主体支杆包括与底部连接板共面的第一杆段，这样，通过底部连接板与第一杆段共同与地面接触，增大了降落时起落架与地面的接触面积，降低在降落时对机身和机上带载的冲击强度；并且，由于主体支杆的第二杆段背离主体支杆倾斜，使得第一杆段可以具有较长的长度，进一步增加飞行器着陆时起落架与地面的接触面积，有效地吸收了降落时的冲击能量，从而保障飞行器的安全平稳降落。
 附图说明
图1是根据本发明一个实施例起落架的立体视图；
图2是根据本发明一个实施例起落架的剖视图；
图3是根据本发明一个实施例起落架的俯视图；
图4是根据本发明一个实施例非正常降落时起落架的示意图。
 本发明的实施方式
以下将结合附图，对本发明的实施例进行详细描述。
如图1至图4所示，本发明提供了一种用于垂直起降飞行器的起落架，包括：用于与垂直起降飞行器连接的顶部连接板1，以及与顶部连接板相对设置的底部连接板5。其中，顶部连接板1与底部连接板5之间通过多个等角度分布的主体支杆2连接，主体支杆2包括水平设置的第一杆段，及自第一杆段弯折延伸形成的第二杆段，第二杆段与第一杆段形成夹角。主体支杆2为金属材质或碳纤维等复合材料，第一杆段与第二杆段之间形成夹角使第一杆段与第二杆段之间具有回弹力，进而具有一定的缓冲功能。
上述实施例中涉及的用于垂直起降飞行器的起落架，用于支撑飞行器的主体支杆2包括与底部连接板5共面的第一杆段，也就是说底部连接板5与第一杆段位于同一个水平面上。这样，通过底部连接板5与第一杆段共同与地面接触，增大了降落时起落架与地面的接触面积，降低在降落时对机身和机上带载的冲击强度；并且，由于主体支杆2的第一杆段背离主体支杆2倾斜，使得第一杆段可以具有较长的长度，进一步增加飞行器着陆时起落架与地面的接触面积，有效地吸收了降落时的冲击能量，从而保障飞行器的安全平稳降落。
也就是说，主体支杆2的第二杆段从顶部连接板1所在平面向底部连接板5所在平面倾斜延伸，以增大底部连接板5与第一杆段的触地面积，保证飞行器平稳着陆。
另外，上述实施例中的垂直起降飞行器可以包含但不限于中小型无人机和载人机型。
根据本发明的实施例，顶部连接板1的中心轴线与底部连接板5的中心轴线重合，换个角度讲，顶部连接板1与底部连接板5相对设置且相互平行，使起落架的整体结构更稳定。起落架包括避震结构6，避震结构6的相对两端分别与顶部连接板1和底部连接板5连接。这样，当飞行器降落时，避震结构6可以有效地吸收降落时的冲击能量，从而保障飞行器的安全平稳降落。
根据本发明的实施例，避震结构6包括在顶部连接板1的中心轴线方向上设置的套筒及收容在套筒内的弹性元件，套筒的一端装设在底部连接板5的上表面，弹性元件可在顶部连接板1的中心轴线方向上相对于套筒作伸缩运动。当飞行器着陆时，地面与底部连接板5接触，进而挤压避震结构6以压缩弹性元件，从而达到缓冲的目的。弹性元件可为弹簧、橡胶等具有弹性功能的元件。
根据本发明的实施例，顶部连接板1的下表面向下延伸设有柱形部，弹性元件的相对两端分别抵压于套筒的内底面和柱形部的下表面，并且柱形部至少部分伸入套筒内，用于抵压弹性元件，避免弹性元件变形而造成缓冲失效。
或者，在一个可选实施例中，避震结构6也可以包括位于中间的伸缩杆，以及包围或围绕伸缩杆设置的弹簧。或者使用液压伸缩杆来作为避震结构6，当然，根据具体使用情况，避震结构6也可以包括其他具有减震功能的结构，本发明不局限于此。
如图2至图3所示，根据本发明的实施例，主体支杆2设置的数量为四根，四根主体支杆2等角度地绕顶部连接板1的中心轴线而设置，并且四根主体支杆2在水平面上的投影呈十字形构造。十字形构造不但可以在飞行器着陆时起到缓冲作用，而且可以协助整体机身稳定重心。
当然，可以理解的是，在一个可选实施例中，主体支杆2也可以不对称设置，例如，起落架可以包括五根等间距设置的主体支杆。进一步地，在本发明的一个可选实施例中，主体支杆2包括金属或合金或复合材料。
再次参照图1和图2，根据本发明的实施例，第一杆段与第二杆段之间形成过渡段，过渡段为夹角的倒圆角。以便主体支杆2在飞行器着陆时能够产生一定形变，吸收部分冲击能量。
根据本发明的实施例，第二杆段进一步包括水平延伸的连接段，连接段连接固定于顶部连接板1，连接段与第一杆段相互平行，方便主体支杆2的两个末端与平行设置的顶部连接板1和底部连接板5固定连接。
根据本发明的实施例，顶部连接板1的侧壁向内凹设有多个第一卡槽，多个连接段分别对应插入多个第一卡槽，并通过第一螺栓4与顶部连接板1连接。当然，根据具体情况，第一螺栓4和主体支杆2的数量可以进行调整。并且，还应该理解的是，主体支杆2与顶部连接板1之间也可以通过诸如插接件的其他方式连接。
在上述实施例中，顶部连接板上设有多个第一螺纹孔，第一螺纹孔的中心轴线与连接板的中心轴线相互平行，连接段的自由端设置有第二螺纹孔，第一螺纹孔与第二螺纹孔的中心轴线重合设置，方便第一螺栓旋入形成紧固连接。
根据本发明的实施例，底部连接板5的侧壁向内凹设有多个第二卡槽，多个第一杆段的自由端分别对应插入多个第二卡槽，并通过第二螺栓7与底部连接板5连接。
根据本发明的实施例，第一杆段和底部连接板5的底面分别设置有第一缓冲垫片8和第二缓冲垫片9，第一缓冲垫片8和第二缓冲垫片9的底平面处于同一水平面，为了使起落架的整个底平面处于同一平面内，以利于平稳降落。
根据本发明的实施例，如图3所示，第一杆段与第二杆段在竖直方向上位于同一平面内，二者在竖直平面内弯折形成弹性缓冲空间。
如图1所示，本发明的一个实施例涉及一种适用于垂直起降飞行器（包含但不限于中小型无人机和载人机型）的起落架，由十字型的主体框架、一个四通连接板（顶部连接板1）、一个五通连接板（底部连接板5）、一根强力弹簧（也可以为减震器）、橡胶垫片和若干螺钉组成。其中，主体框架包括四条主体支杆2。
如图中所示，顶部连接板1为上部四通连接板，含四个卡槽。底部含一伸缩杆，降落时对弹簧进行挤压，从而达到缓冲的目的。另一方面，伸缩杆的重量可以协助整体机身稳定重心。
起落架的主体框架结构，可采用合金或复合材料，具备一定的韧性，总共含四根主体支杆2。每根主体支杆2均采用一体成型的类C型结构。主体支杆2可采用圆杆或方形。上部四通连接板通过第一螺栓4连接四根主体支杆2，具体的连接方式可根据飞行器类型进行灵活调节。
顶部连接板1还包括螺丝钉安装孔位3，起落架可通过这四个螺丝钉安装孔位3与飞行器主体进行固定连接。
图1所示的下部五通连接板，与四根主体支杆2间通过第二螺栓7相连。具体螺丝孔位的数量可根据强度需要进行调节。如图所示的避震结构6，采用的是弹簧，根据飞行器的大小和类型，可选择不同强度的弹簧或者直接采用避震器。
主体支杆2底部和五通连接板底部分别连接有第一缓冲垫片8和第二缓冲垫片9，橡胶垫片可采用但不限于粘接、包裹等方式与起落架连接。
当飞行器正常降落时，第一缓冲垫片8和第二缓冲垫片9先接触地面，起到第一层的缓冲保护作用。由于惯性作用，与起落架相连的飞行器主体仍保持下降的趋势，将通过四通连接板挤压弹簧或避震器，起到第二层的缓冲保护作用。同时，具备一定韧性的主体支杆2也将产生一定的形变，吸收部分冲击能量，起到第三层的缓冲保护作用。
如图4所示，当飞行器以起落架的某个角或某两个角先着地时，由于四通连接板和五通连接板及两者间连接的避震结构6的重量及位置起到类似于不倒翁的稳定重心的作用，所以飞行器会自动地矫正着陆姿态，以保证飞行器的安全降落，保护机身主体及机上的带载不受到损伤。
以上所述仅为本发明的优选实施例而已，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。
 

Claims (10)

  1. 一种用于垂直起降飞行器的起落架，其特征在于，包括：用于与所述垂直起降飞行器连接的顶部连接板（1），以及与所述顶部连接板相对设置的底部连接板（5），
    其中，所述顶部连接板（1）与所述底部连接板（5）之间通过多个等角度分布的主体支杆（2）连接，所述主体支杆（2）包括水平设置的第一杆段，及自所述第一杆段弯折延伸形成的第二杆段，所述第二杆段与所述第一杆段形成夹角。
  2. 根据权利要求1所述的起落架，其特征在于，所述顶部连接板（1）的中心轴线与所述底部连接板（5）的中心轴线重合，所述起落架包括避震结构（6），所述避震结构（6）的相对两端分别与所述顶部连接板（1）和所述底部连接板（5）连接。
  3. 根据权利要求2所述的起落架，其特征在于，所述避震结构（6）包括在所述顶部连接板（1）的中心轴线方向上设置的套筒及收容在所述套筒内的弹性元件，所述套筒的一端装设在所述底部连接板（5）的上表面，所述弹性元件可在所述顶部连接板（1）的中心轴线方向上相对于所述套筒作伸缩运动。
  4. 根据权利要求3所述的起落架，其特征在于，所述顶部连接板（1）的下表面设有柱形部，所述弹性元件的相对两端分别抵压于所述套筒的内底面和所述柱形部的下表面，并且所述柱形部至少部分伸入所述套筒内。
  5. 根据权利要求1所述的起落架，其特征在于，所述主体支杆（2）设置的数量为四根，四根所述主体支杆（2）等角度地绕所述顶部连接板（1）的中心轴线而设置，并且所述四根主体支杆（2）在水平面上的投影呈十字形构造。
  6. 根据权利要求1所述的起落架，其特征在于，所述第一杆段与所述第二杆段之间形成过渡段，所述过渡段为所述夹角的倒圆角。
  7. 根据权利要求1所述的起落架，其特征在于，所述主体支杆（2）进一步包括自所述第二杆段水平延伸的连接段，所述连接段连接固定于所述顶部连接板（1），所述连接段与所述第一杆段相互平行。
  8. 根据权利要求7所述的起落架，其特征在于，所述顶部连接板（1）的侧壁向内凹设有多个第一卡槽，多个所述连接段分别对应插入多个所述第一卡槽，并通过第一螺栓（4）与所述顶部连接板（1）连接。
  9. 根据权利要求1所述的起落架，其特征在于，所述底部连接板（5）的侧壁向内凹设有多个第二卡槽，多个所述第一杆段的自由端分别对应插入多个所述第二卡槽，并通过第二螺栓（7）与所述底部连接板（5）连接。
  10. 根据权利要求9所述的起落架，其特征在于，所述第一杆段和所述底部连接板（5）的底面分别设置有第一缓冲垫片（8）和第二缓冲垫片（9），所述第一缓冲垫片（8）和所述第二缓冲垫片（9）的底平面处于同一水平面。
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