WO2019085148A1 - 一种无人飞行器及其升降起落架 - Google Patents

一种无人飞行器及其升降起落架 Download PDF

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Publication number
WO2019085148A1
WO2019085148A1 PCT/CN2017/114992 CN2017114992W WO2019085148A1 WO 2019085148 A1 WO2019085148 A1 WO 2019085148A1 CN 2017114992 W CN2017114992 W CN 2017114992W WO 2019085148 A1 WO2019085148 A1 WO 2019085148A1
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Prior art keywords
landing gear
lifting
leg
wing
aircraft
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PCT/CN2017/114992
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English (en)
French (fr)
Inventor
陈晨
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深圳市大疆创新科技有限公司
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Priority to CN201780065063.7A priority Critical patent/CN110418753A/zh
Publication of WO2019085148A1 publication Critical patent/WO2019085148A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
    • 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 
    • B64C25/66—Convertible alighting gear; Combinations of different kinds of ground or like engaging elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings

Definitions

  • the invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a lifting and landing gear for an unmanned aerial vehicle.
  • the lift and drag characteristics of the fixed wing are the most efficient in the current unmanned aerial vehicle.
  • the lift generated by the airfoil can reach several times or even dozens of times under the optimal cruising state.
  • the typical lift-to-resistance ratio of the small fixed-wing aircraft can reach 7-20; Therefore, for the current multi-rotor or other VTOL (vertical take-off and landing) unmanned aerial vehicles, one of the most effective means of improving cruise economy is to increase the fixed wing.
  • the present invention provides a lifting and landing gear for an unmanned aerial vehicle, including a wing panel and a landing gear for contacting the ground. a leg having one end connected to the landing gear leg and the other end connected to the aircraft body, the wing being used as a fixed wing for increasing the lift of the aircraft when the lifting gear is raised.
  • one end of the wing is directly connected to the landing gear leg.
  • the other end of the wing is provided with a rotating connection for rotational connection to the aircraft body.
  • the lifting and landing gear further comprises a landing gear leg, one end of the landing gear leg is directly connected to the landing gear leg, and the wing plate is disposed on the landing gear leg.
  • the other end of the landing gear leg is provided with a rotating connection for rotating connection On the aircraft body.
  • the landing gear legs are carbon fiber rods.
  • the landing gear feet are rods disposed parallel to the longitudinal direction of the aircraft body.
  • the plane of the chord of the wing has a predetermined angle with the axis of the landing gear leg.
  • the landing gear leg is fixedly connected to the landing gear leg; or the landing gear leg is foldably connected to the landing gear leg, and the landing gear leg can be folded to and when the aircraft is stored The position where the landing gear legs are parallel.
  • the flap is made of carbon fiber.
  • a lift tab rotatably disposed on the flap is further included.
  • the inside of the wing is a hollow structure.
  • the present invention also provides an unmanned aerial vehicle comprising: an aircraft body and at least one pair of lifting and landing gears disposed on the aircraft body, the lifting and landing gear being the lifting and landing gear disclosed in any of the above, When the lifting and landing gear is in the raised state, the wing is in an operating state; when the lifting and landing gear is in a falling state, the wing is in a recovered state.
  • the UAV is a multi-rotor aircraft.
  • the landing gear and the lifting wing are combined into one, and the landing gear not only has the routine for the aircraft to take off and land. Function, and when the aircraft is cruising, the landing gear also has the function of increasing the wing.
  • the UAV can now provide part or all of the lift by the more efficient wing, thereby improving the aircraft cruise economy;
  • On the aircraft landing gear it is possible to save the structure in which the raising wing is separately installed and the lifting force is transmitted to the fuselage in the conventional design, so that the inventive scheme not only makes the conventional way of providing the lifting wing directly on the aircraft body, The entire UAV is compact and keeps the weight of the entire UAV at a low level.
  • the unmanned aerial vehicle disclosed in the present invention adopts the above-mentioned lifting and landing gear, so that the lifting and landing gear of the unmanned aerial vehicle not only has the conventional function for the aircraft to take off and land, but also when the unmanned aerial vehicle is cruising, the landing gear also has
  • the UAV can now provide some or all of the lift from the more efficient wing, thereby improving the aircraft cruise economy.
  • the entire UAV is compact and the weight is kept at a low level.
  • FIG. 1 is a schematic structural view of an aircraft disclosed in an embodiment of the present invention when landing;
  • FIG. 2 is a schematic structural view of an aircraft disclosed in an embodiment of the present invention during flight.
  • 1 is the main body of the aircraft
  • 21 is the landing gear leg
  • 22 is the landing gear leg
  • 3 is the wing
  • 4 is the arm
  • 5 is the motor.
  • One of the cores of the present invention is to provide a landing gear for an unmanned aerial vehicle to effectively improve the cruise economy of the aircraft without significantly increasing the size and weight of the aircraft.
  • Another core of the present invention is to provide an unmanned aerial vehicle employing the above-described lifting and lowering gear.
  • the lifting and landing gear of the unmanned aerial vehicle disclosed in the embodiment of the present invention comprises a wing plate 3 and a landing gear leg 22, wherein the landing gear foot 22 functions to contact the ground and stably support the aircraft, and one end of the wing plate 3 and the landing gear The legs 22 are connected, and the other end is connected to the aircraft body 1.
  • the landing gear has a raised state and a falling state. When the landing gear is in the raised state, the unmanned aerial vehicle is in the normal flight process, and the landing gear is in the landing state. The aircraft is about to land or has finished landing.
  • the lifting and landing gear is raised, the wing 3 is used as a fixed wing for increasing the lift of the aircraft.
  • the landing gear is combined with the lifting wing 3, the landing gear not only has the conventional function for the aircraft to take off and land, but also the landing gear when the UAV is cruising.
  • the UAV can provide partial or full lift by the more efficient wing 3 at this time, thereby improving the cruise economy of the UAV; and setting the wing 3 on the aircraft landing gear, not only can While maintaining the vertical take-off and landing functions of the aircraft, and saving the structure of separately installing the lifting wings and transferring the lift to the fuselage in the conventional design, the conventional manner of providing the lifting wings directly on the aircraft main body 1 is compared.
  • the solution of the present invention not only makes the entire UAV compact, but also keeps the weight of the entire UAV at a low level.
  • the landing gear includes a landing gear leg 21 in addition to the wing 3 and the landing gear leg 22.
  • One end of the landing gear leg 21 is directly associated with the landing gear.
  • the legs 22 are connected, and the flaps 3 are disposed on the landing gear legs 21.
  • the flaps 3 in this embodiment are indirectly connected to the landing gear legs 22 by the landing gear legs 21, and the landing gear legs 21 are located on the wing panels. 3
  • the landing gear leg 21 drives the wing plate 3 to operate, thereby realizing the opening and recovery of the wing plate 3.
  • connection between the landing gear leg 21 and the landing gear leg 22 is not limited to one type.
  • the movable connection or the fixed connection may be adopted between the landing gear leg 21 and the landing gear leg 22, and the movable connection may be connected by bolting or It can be realized by means of hinges, etc., and the fixed connection can be realized by means including welding and bonding.
  • the landing gear foot 22 can be further configured in a foldable manner.
  • the landing gear foot 22 can be rotated to the landing gear.
  • the legs 21 are parallel to each other, thereby effectively reducing the size of the entire aircraft, facilitating storage or transportation; when the unmanned aerial vehicle needs to work, only the landing gear legs 22 need to be rotated to the working position, more preferably
  • the manner is that a position locking mechanism is provided between the landing gear leg 21 and the landing gear leg 22, and the position locking mechanism can be a locking pin disposed on either of the landing gear leg 21 and the landing gear leg 22. And a locking hole provided on the other one.
  • the end of the landing gear leg 21 for connecting with the aircraft body 1 is provided with a rotating connection portion, which may be a rotating shaft, and correspondingly, the aircraft body 1 is provided with a shaft hole adapted to the rotating shaft;
  • the rotary connecting portion may also be a shaft hole.
  • the aircraft body 1 is provided with a rotating shaft corresponding to the shaft hole.
  • the landing gear legs 21 in this embodiment are carbon fiber rods, of course, the landing gear feet. 22 and wing 3 can also be considered to be made of carbon fiber material.
  • the flap 3 can also adopt a hollow structure, which can further reduce the weight of the landing gear.
  • the landing gear legs 22 are specifically rod members disposed longitudinally parallel to the aircraft body 1, with a predetermined angle between the plane of the chord of the wing 3 and the axis of the landing gear legs 22, It is ensured that the flap 3 can reach an optimum angle when the lifting gear is raised.
  • the preset angle can be adaptively designed according to the specific size of the unmanned aerial vehicle and the state after the lifting and landing gear is deployed. According to the actual situation, the actual angle of the preset angle is not unique.
  • one end of the flap 3 is directly connected to the landing gear leg 22.
  • the flap 3 also serves as a leg for lifting the landing gear, in order to make the wing 3 is rotatably connected to the aircraft body 1, and the end of the wing 3 for connecting with the UAV is further provided with a rotating connection.
  • the rotating connection may be a rotating shaft, and correspondingly, the aircraft body 1 is disposed.
  • the rotating connecting portion may also be a shaft hole, and correspondingly, the aircraft body 1 is provided with a rotating shaft corresponding to the shaft hole.
  • the flap 3 is further provided with a lift tab, and the lift tab is rotatably disposed on the flap 3 to assist in adjusting the lift and pitch moment of the flap 3.
  • an unmanned aerial vehicle is further disclosed in the embodiment of the present invention, and the unmanned aerial vehicle includes an aircraft main body_1 and at least one pair of lifting and landing gears disposed on the aircraft main body 1, and the lifting and landing gear is any one of the above
  • the lifting and landing gear of the unmanned aerial vehicle disclosed in the embodiment the lifting and landing gear is driven by a steering gear or other driving device, and when the lifting and landing gear is in the raised state, the wing plate 3 is in a working state as a fixed wing, and the lifting and lowering When the landing gear is in a landing state, the flap 3 is in a retracted state.
  • the unmanned aerial vehicle includes, but is not limited to, a multi-rotor aircraft.
  • the unmanned aerial vehicle shown in FIGS. 2 and 3 is a quadrotor aircraft, and the motor 5 for supplying power is mounted on the aircraft main body 1 through the arm 4.
  • the lifting and landing gear of the unmanned aerial vehicle not only has the conventional function for the aircraft to take off and land, but also has the lifting wing when the aircraft is cruising.
  • the function of the board 3, the UAV can now provide some or all of the lift by the more efficient wing 3, thereby improving the aircraft cruise economy; while the entire UAV is compact and the weight is kept low.

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

一种无人飞行器及其升降起落架，所述升降起落架包括翼板(3)和用于与地面接触的起落架支脚(22)，所述翼板(3)的一端与所述起落架支脚(22)相连，另一端用于与飞行器主体(1)相连，当所述升降起落架升起时，所述翼板(3)作为固定翼用于提高飞行器的升力。该无人飞行器起落架可以提升飞行器巡航经济性；同时还能够使得整个无人飞行器结构紧凑，重量保持在较低水平。

Description

一种无人飞行器及其升降起落架 技术领域
本发明涉及无人飞行器技术领域，特别涉及一种无人飞行器及无人飞行器的升降起落架。
背景技术
固定翼的升力和阻力特性是目前无人飞行器中效率最高的，最佳巡航状态下翼面产生的升力可达到阻力的几倍甚至数十倍，小型固定翼飞行器典型全机升阻比可以达到7～20；因此，对于目前的多旋翼或其他VTOL(vertical take-off and landing，垂直起降)无人飞行器而言，提高巡航经济性最为有效的手段之一就是增加固定机翼。
但是，直接在飞行器主体上增加固定机翼不仅会显著增大飞行器的整体尺寸，而且还会明显增加飞行器主体的整体重量，导致飞行器的载荷系数较小的问题出现。
发明内容
为了能够在不显著增大无人飞行器尺寸和重量的前提下有效提高飞行器的巡航经济性，本发明提供了一种无人飞行器的升降起落架，包括翼板和用于与地面接触的起落架支脚，所述翼板的一端与所述起落架支脚相连，另一端用于与飞行器主体相连，当所述升降起落架升起时，所述翼板作为固定翼用于提高飞行器的升力。
优选的，所述翼板的一端直接与所述起落架支脚相连。
优选的，所述翼板的另一端设置有转动连接部，用于转动连接于所述飞行器主体上。
优选的，所述升降起落架还包括起落架支腿，所述起落架支腿的一端直接与所述起落架支脚相连，且所述翼板设置于所述起落架支腿上。
优选的，所述起落架支腿的另一端设置有转动连接部，用于转动连接 于所述飞行器主体上。
优选的，所述起落架支腿为碳纤维杆件。
优选的，所述起落架支脚为平行于所述飞行器主体的纵向设置的杆件。
优选的，所述翼板的翼弦所在的平面与所述起落架支脚的轴线具有预设夹角。
优选的，所述起落架支脚与所述起落架支腿固定连接；或所述起落架支脚可折叠连接在所述起落架支腿上，在飞行器收纳时，所述起落架支脚可折叠至与所述起落架支腿平行的位置。
优选的，所述翼板为由碳纤维制成。
优选的，还包括可转动地设置在所述翼板上的升力调整片。
优选的，所述翼板的内部为空心结构。
本发明还提供了一种无人飞行器，包括飞行器主体和设置在所述飞行器主体上的至少一对升降起落架，该升降起落架为上述任意一项中所公开的升降起落架，在所述升降起落架处于升起状态时，所述翼板处于工作状态；在所述升降起落架处于降落状态时，所述翼板处于回收状态。
优选的，所述无人飞行器为多旋翼飞行器。
由以上技术方案可以看出，本发明所公开的无人飞行器的升降起落架中，将起落架与起增升作用的翼板合二为一进行设计，起落架不仅具有供飞行器进行起落的常规功能，而且在飞行器进行巡航时，起落架还具有增升翼板的功能，无人飞行器此时可以由效率更高的翼板提供部分或全部升力，从而提升飞行器巡航经济性；将翼板设置在飞行器起落架上，可以节省常规设计中单独安装增升翼以及将升力传递到机身的结构，因此相比于直接在飞行器主体上设置增升翼的传统方式而言，本发明方案不仅使得整个无人飞行器结构紧凑，而且还使整个无人飞行器的重量保持在较低水平。
本发明中所公开的无人飞行器，由于采用了上述升降起落架，因此该无人飞行器的升降起落架不仅具有供飞行器进行起落的常规功能，而且在无人飞行器进行巡航时，起落架还具有增升翼板的功能，无人飞行器此时可以由效率更高的翼板提供部分或全部升力，从而提升飞行器巡航经济 性；同时整个无人飞行器结构紧凑，重量保持在了较低水平。
附图说明
图1为本发明实施例中所公开的飞行器在着陆时的结构示意图；
图2为本发明实施例中所公开的飞行器在飞行时的结构示意图。
其中，1为飞行器主体，21为起落架支腿，22为起落架支脚，3为翼板，4为机臂，5为电机。
具体实施方式
本发明的核心之一是提供一种无人飞行器的升降起落架，以便在不显著增大飞行器尺寸和重量的前提下，有效提高飞行器的巡航经济性。
本发明的另一核心在于提供一种采用上述升降起落架的无人飞行器。
本发明实施例中所公开的无人飞行器的升降起落架，包括翼板3和起落架支脚22，其中起落架支脚22的作用在于与地面接触并稳定支撑飞行器，翼板3的一端与起落架支脚22相连，另一端用于与飞行器主体1相连，起落架具有升起状态和降落状态，起落架在升起状态时，无人飞行器处于正常飞行过程中，起落架在降落状态时，无人飞行器即将降落或者已经完成降落，在本实施例中，当升降起落架升起时，翼板3作为固定翼用于提高飞行器的升力。
可以发现，在上述实施例中，起落架与起增升作用的翼板3合二为一，起落架不仅具有供飞行器进行起落的常规功能，而且在无人飞行器进行巡航时，起落架还具有增升翼板3的功能，无人飞行器此时可以由效率更高的翼板3提供部分或全部升力，从而提升无人飞行器巡航经济性；将翼板3设置在飞行器起落架上，不仅可以在保持飞行器的垂直起降和悬停功能，而且可以节省常规设计中单独安装增升翼以及将升力传递到机身的结构，因此相比于直接在飞行器主体1上设置增升翼的传统方式而言，本发明方案不仅使得整个无人飞行器结构紧凑，而且还使整个无人飞行器的重量保持在较低水平。
为了使本技术领域的人员更好地理解本发明方案，下面结合附图和具体实施方式对本发明作进一步的详细说明。
请参考图2和图3，在本发明的一种实施例中，升降起落架除了翼板3和起落架支脚22外还包括起落架支腿21，起落架支腿21的一端直接与起落架支脚22相连，翼板3设置在起落架支腿21上，该实施例中的翼板3实质上是通过起落架支腿21间接连接在起落架支脚22上，起落架支腿21位于翼板3升降中心附近，升降起落架的状态发生改变时，起落架支腿21带动翼板3动作，从而实现翼板3的打开和回收，请参考图2，当升降起落架处于降落状态时，翼板3刚好处于回收状态，此时翼板3不在发挥增加升力的作用；请参考图3，当升降起落架处于升起状态时，此时无人飞行器处于正常飞行状态或者巡航状态，翼板3刚好处于打开状态，翼板3此时发挥增加飞行器升力的作用，固定翼的升力和阻力特性，使得采用该翼板3的飞行器的巡航经济性显著提高。
起落架支腿21与起落架支脚22之间的连接方式不限于一种，例如起落架支腿21与起落架支脚22之间可以采用活动连接或者固定连接的方式，活动连接可以通过螺栓连接或者铰接等方式实现，固定连接可以采用包括焊接和粘接在内的方式实现。
当起落架支腿21与起落架支脚22之间采用铰接方式相连时，起落架支脚22还可进一步设计为可折叠的方式，当无人飞行器收纳时，起落架支脚22可旋转至与起落架支腿21平行的位置上，从而有效降低整个飞行器的尺寸，为储存或运输提供便利；当无人飞行器需进行工作时，仅需将起落架支脚22旋转至工作位置即可，更为优选的方式是，起落架支腿21与起落架支脚22之间还设置有位置锁止机构，该位置锁止机构可以由设置在起落架支腿21和起落架支脚22任意一者上的锁止销，和设置在另外一者上的锁止孔构成。
起落架支腿21用于与飞行器主体1相连的一端设置有转动连接部，该转动连接部可以为转动轴，相应的，飞行器主体1上设置有与该转动轴适配的轴孔；当然，该转动连接部也可以为轴孔，相应的，飞行器主体1上设置有与该轴孔对应的转动轴。
为了提高无人飞行器的续航里程，需要在保证升降起落架强度的前提下有效降低升降起落架的重量，为此，本实施例中的起落架支腿21为碳纤维杆件，当然，起落架支脚22以及翼板3也可考虑采用碳纤维材料制 成，翼板3还可以采用空心结构，这可以进一步降低起落架的重量。
请参考图2和图3，起落架支脚22具体为平行于飞行器主体1纵向设置的杆件，翼板3的翼弦所在的平面与起落架支脚22的轴线之间具有预设夹角，以保证在升降起落架升起时，翼板3能够达到最佳角度。需要进行说明的是，预设夹角可根据无人飞行器的具体尺寸、升降起落架展开后的状态进行适应性设计，根据实际情况不同，预设夹角的实际角度并不唯一。
在本发明另一实施例中，翼板3的一端直接与起落架支脚22相连，翼板3除了作为提高飞行器升力的固定翼之外，还兼做升降起落架的支腿，为了使翼板3可转动地连接在飞行器主体1上，翼板3用于与无人飞行器相连的一端还设置有转动连接部，同理，该转动连接部可以为转动轴，相应的，飞行器主体1上设置有与该转动轴适配的轴孔；当然，该转动连接部也可以为轴孔，相应的，飞行器主体1上设置有与该轴孔对应的转动轴。
更进一步的，翼板3上还设置有升力调整片，升力调整片可转动的设置在翼板3上，以辅助对翼板3的升力和俯仰力矩进行调节。
除此之外，本发明实施例中还公开了一种无人飞行器，该无人飞行器包括飞行器主体_1和设置在飞行器主体1上的至少一对升降起落架，升降起落架为上述任意一实施例中所公开的无人飞行器的升降起落架，升降起落架通过舵机或其他驱动装置进行驱动，该升降起落架在处于升起状态时，翼板3作为固定翼处于工作状态，该升降起落架处于降落状态时，翼板3处于回收状态。该无人飞行器包括但不限于多旋翼飞行器，如图2和图3中所示的无人飞行器为四旋翼飞行器，用于提供动力的电机5通过机臂4安装在飞行器主体1上。
上述实施例中的无人飞行器，由于采用了上述升降起落架，因此该无人飞行器的升降起落架不仅具有供飞行器进行起落的常规功能，而且在飞行器进行巡航时，起落架还具有增升翼板3的功能，无人飞行器此时可以由效率更高的翼板3提供部分或全部升力，从而提升飞行器巡航经济性；同时整个无人飞行器结构紧凑，重量保持在了较低水平。
以上对本发明所提供的无人飞行器及无人飞行器的升降起落架进行 了详细介绍。本文中应用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想。应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理的前提下，还可以对本发明进行若干改进和修饰，这些改进和修饰也落入本发明权利要求的保护范围内。

Claims (25)

  1. 一种无人飞行器的升降起落架，其特征在于，包括翼板和用于与地面接触的起落架支脚，所述翼板的一端与所述起落架支脚相连，另一端用于与飞行器主体相连，当所述升降起落架升起时，所述翼板作为固定翼用于提高飞行器的升力。
  2. 根据权利要求1所述的升降起落架，其特征在于，所述翼板的一端直接与所述起落架支脚相连。
  3. 根据权利要求2所述的升降起落架，其特征在于，所述翼板的另一端设置有转动连接部，用于转动连接于所述飞行器主体上。
  4. 根据权利要求1所述的升降起落架，其特征在于，所述升降起落架还包括起落架支腿，所述起落架支腿的一端直接与所述起落架支脚相连，且所述翼板设置于所述起落架支腿上。
  5. 根据权利要求4所述的升降起落架，其特征在于，所述起落架支腿的另一端设置有转动连接部，用于转动连接于所述飞行器主体上。
  6. 根据权利要求4所述的升降起落架，其特征在于，所述起落架支腿为碳纤维杆件。
  7. 根据权利要求1所述的升降起落架，其特征在于，所述起落架支脚为平行于所述飞行器主体的纵向设置的杆件。
  8. 根据权利要求7所述的升降起落架，其特征在于，所述翼板的翼弦所在的平面与所述起落架支脚的轴线具有预设夹角。
  9. 根据权利要求7所述的升降起落架，其特征在于，所述起落架支脚与所述起落架支腿固定连接；或所述起落架支脚可折叠连接在所述起落架支腿上，在飞行器收纳时，所述起落架支脚可折叠至与所述起落架支腿平行的位置。
  10. 根据权利要求1所述的升降起落架，其特征在于，所述翼板为由碳纤维制成。
  11. 根据权利要求1-10任意一项所述的升降起落架，其特征在于，还包括可转动地设置在所述翼板上的升力调整片。
  12. 根据权利要求1-10任意一项所述的升降起落架，其特征在于， 所述翼板的内部为空心结构。
  13. 一种无人飞行器，包括飞行器主体和设置在所述飞行器主体上的至少一对升降起落架，其特征在于，
    所述升降起落架包括翼板和用于与地面接触的起落架支脚，所述翼板的一端与所述起落架支脚相连，另一端用于与飞行器主体相连，当所述升降起落架升起时，所述翼板作为固定翼用于提高飞行器的升力；
    在所述升降起落架处于升起状态时，所述翼板处于工作状态；在所述升降起落架处于降落状态时，所述翼板处于回收状态。
  14. 根据权利要求13所述的无人飞行器，其特征在于，所述翼板的一端直接与所述起落架支脚相连。
  15. 根据权利要求14所述的无人飞行器，其特征在于，所述翼板的另一端设置有转动连接部，用于转动连接于所述飞行器主体上。
  16. 根据权利要求13所述的无人飞行器，其特征在于，所述升降起落架还包括起落架支腿，所述起落架支腿的一端直接与所述起落架支脚相连，且所述翼板设置于所述起落架支腿上。
  17. 根据权利要求16所述的无人飞行器，其特征在于，所述起落架支腿的另一端设置有转动连接部，用于转动连接于所述飞行器主体上。
  18. 根据权利要求16所述的无人飞行器，其特征在于，所述起落架支腿为碳纤维杆件。
  19. 根据权利要求13所述的无人飞行器，其特征在于，所述起落架支脚为平行于所述飞行器主体的纵向设置的杆件。
  20. 根据权利要求19所述的无人飞行器，其特征在于，所述翼板的翼弦所在的平面与所述起落架支脚的轴线具有预设夹角。
  21. 根据权利要求19所述的无人飞行器，其特征在于，所述起落架支脚与所述起落架支腿固定连接；或所述起落架支脚可折叠连接在所述起落架支腿上，在飞行器收纳时，所述起落架支脚可折叠至与所述起落架支腿平行的位置。
  22. 根据权利要求13所述的无人飞行器，其特征在于，所述翼板为由碳纤维制成。
  23. 根据权利要求13-22任意一项所述的无人飞行器，其特征在于， 还包括可转动地设置在所述翼板上的升力调整片。
  24. 根据权利要求13-22任意一项所述的无人飞行器，其特征在于，所述翼板的内部为空心结构。
  25. 根据权利要求13-24任意一项所述的无人飞行器，其特征在于，所述无人飞行器为多旋翼飞行器。
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