WO2017198082A1 - 飞行器 - Google Patents

飞行器 Download PDF

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Publication number
WO2017198082A1
WO2017198082A1 PCT/CN2017/083456 CN2017083456W WO2017198082A1 WO 2017198082 A1 WO2017198082 A1 WO 2017198082A1 CN 2017083456 W CN2017083456 W CN 2017083456W WO 2017198082 A1 WO2017198082 A1 WO 2017198082A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
arm
propeller
aircraft body
tail
Prior art date
Application number
PCT/CN2017/083456
Other languages
English (en)
French (fr)
Inventor
胡华智
潘旭
靳洪胜
Original Assignee
亿航智能设备（广州）有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 亿航智能设备（广州）有限公司 filed Critical 亿航智能设备（广州）有限公司
Publication of WO2017198082A1 publication Critical patent/WO2017198082A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/52—Tilting of rotor bodily relative to fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/296—Rotors with variable spatial positions relative to the UAV body
    • B64U30/297—Tilting rotors

Definitions

  • the present application relates to the field of aircraft technology, and in particular, to an aircraft.
  • the present application is to overcome the deficiencies of the prior art, and to provide an aircraft that reduces the propeller load, extends the flight space of the aircraft, and has a simple structure.
  • An aircraft includes an aircraft body, a boom assembly disposed on the aircraft body, and a power unit disposed on the arm assembly, the power unit including a driving member and a connection with the driving member
  • the propeller has a machine head at one end and a tail at the other end, and the propeller is disposed obliquely with respect to the aircraft body.
  • the aircraft is horizontally placed, the inclination angle of the rotating surface of the propeller and the horizontal plane is ⁇ , and ⁇ is greater than 0 degrees and less than 90 degrees.
  • the aircraft is placed horizontally, and the inclination angle ⁇ of the rotating surface of the propeller and the horizontal plane is ⁇ . It is 28.5 degrees.
  • a length of the top surface of the handpiece to the tail is greater than a length of the nose to the bottom surface of the tail.
  • the curvature of the top surface of the aircraft body is greater than the curvature of the bottom surface.
  • the arm assembly includes a first arm, a second arm, a third arm, and a fourth arm, and the first arm and the second arm are disposed on the aircraft The left and right sides of the head direction of the main body, and the first arm and the second arm respectively extend along the traveling direction of the aircraft, and the third arm and the fourth arm are disposed at the The third arm and the fourth arm extend in a vertical upward direction on a top surface of the aircraft body in the tail direction.
  • first arm, the second arm, the third arm and the fourth arm extend outwardly away from an axis of symmetry of the aircraft.
  • the aircraft body includes a left drag reducing portion disposed on a left side of the aircraft body and a right drag reducing portion disposed on a right side of the aircraft body, the left drag reducing portion and the right minus portion
  • the resistance parts are all curved
  • an air guiding portion is protruded upward from a central portion of the top surface of the aircraft body, and the air guiding portion extends from the handpiece to the tail.
  • the top surface of the aircraft body is further recessed with an air guiding portion, the air guiding portion is located between the air guiding portion and the drag reducing portion, and the air guiding portion is from the guiding portion
  • the wind portion smoothly extends downward and then smoothly extends upward toward the drag reducing portion.
  • a concave portion is symmetrically disposed between the front end of the handpiece and the first arm and the second arm.
  • the tail end is symmetrically provided with a recessed portion.
  • the present application also provides an aircraft, including an aircraft body, the front end of the aircraft is a nose, and the rear end is a tail;
  • a power device is disposed on the aircraft body, the power device is used to drive a propeller;
  • the aircraft has two states, a first state and a second state, respectively.
  • first state the rotating surface of the propeller has an inclined angle with the horizontal mask; in the second state, the rotation of the propeller The surface is parallel to the horizontal plane.
  • the plane of the bottom surface of the aircraft body is parallel to the horizontal plane.
  • the plane where the bottom surface of the aircraft is located has a tilt angle with the horizontal mask.
  • the present application also provides an aircraft, including an aircraft body, the front end of the aircraft is a nose, and the rear end is a tail;
  • a power device is disposed on the aircraft body, the power device is used to drive a propeller;
  • the plane of the bottom surface of the aircraft body has an oblique angle with the horizontal mask.
  • the aircraft is configured such that the rotating surface of the propeller is arranged obliquely with the aircraft body, and when the aircraft flies forward, the aircraft body is parallel to the horizontal plane, by passing the nose to the top of the tail
  • the length of the face is set to be larger than the length of the nose to the bottom surface of the tail, so that the airflow passes through the main body of the aircraft to generate a pressure difference on the upper and lower surfaces to generate a climbing force, thereby lifting the aircraft body Acting, thereby reducing the aircraft's reliance on the propeller, thereby reducing the load on the propeller, thereby greatly reducing motor power consumption to achieve longer cruising time in the same battery and powertrain configuration.
  • FIG. 1 is a schematic view of a forward state of an aircraft according to an embodiment of the present application.
  • FIG. 2 is a schematic structural view of an aircraft according to an embodiment of the present application.
  • FIG. 3 is a top plan view of an aircraft according to an embodiment of the present application.
  • FIG. 4 is a side view of the aircraft according to an embodiment of the present application;
  • FIG. 5 is a front elevational view of the aircraft according to an embodiment of the present application;
  • FIG. 6 is a rear view of the aircraft according to an embodiment of the present application.
  • an aircraft includes an aircraft main body 100, an arm assembly 200 disposed on the aircraft main body 100, and a power unit 300 fixed to the arm assembly 200.
  • the power unit 300 includes a driving member 320 and a propeller 340 connected to the driving member 320.
  • One end of the aircraft body 100 is a handpiece 160, and the other end is a tail 170;
  • the propeller 340 is disposed obliquely with respect to the aircraft body 100, wherein the propeller 340 is obliquely arranged along the traveling direction of the handpiece.
  • the arm assembly 200 disposed on the aircraft body 100 includes four arms, each of which is mounted with the driving member 320, and a propeller 340 fixed to the driving member 320, and the rotating surfaces of the four propellers 340 are arranged in an inclined manner with the traveling direction of the aircraft main body 100 on a whole structural arrangement, specifically the aircraft main body 100 Including the handpiece 1 60, the tilting directions of the four of the propellers 340 are deflected obliquely toward the nose of the aircraft body 100.
  • the top surface area of the aircraft body 100 is larger than the bottom surface area of the aircraft body 100 such that the aircraft body 100 is substantially arched, and further, the handpiece 160 to the tail 170
  • the length of the top surface is greater than the length of the head 160 to the bottom surface of the tail 170
  • the curvature of the top surface of the aircraft body 100 is greater than the curvature of the bottom surface such that the aircraft flies forward, and the airflow passes through the aircraft body 100.
  • the crucible creates a pressure difference on the upper and lower surfaces to generate a creeping force, thereby exerting a lifting action on the aircraft body 100, thereby reducing the dependence on the propeller 340 and reducing the negative of the propeller 340. Load, thereby greatly reducing the power consumption of the motor to achieve the purpose of the aircraft with longer battery life in the same battery and power system configuration.
  • the rotating faces of the four said propellers 340 are parallel to each other
  • An air guiding portion 140 is protruded upward from a central portion of the top surface of the aircraft main body 100, and the air guiding portion 140 extends from the handpiece 160 to the tail 170.
  • the aircraft body is parallel to the horizontal plane, so that the airflow can cause a pressure difference between the air guiding portion 170 and the bottom surface through the aircraft body 100, thereby generating a climbing force, thereby reducing the propeller
  • the load of 340 allows more power to be used for normal flight of the aircraft, so that the aircraft has a longer cruising time.
  • the arm assembly 200 is provided with a mounting base 220.
  • the driving member 320 is disposed in the mounting base 220.
  • the driving member 320 includes a transmission member 322, and the propeller 340 It is connected to the transmission member 32.
  • the mounting base 220 is corresponding to the number of the arm, that is, each arm is provided with one of the mounting bases 220, and the mounting base 220 is specifically mounted on the end of the arm, and the mounting seat 220 is a machine
  • the arms are integrally formed to provide sufficient overall structural strength.
  • the mounting base 220 is a frame type structure provided with a mounting cavity, and the frame type structure is preferably a cylinder.
  • the driving component 320 is a motor, and the motor is installed in the mounting cavity, and then the propeller 340 is assembled. Therefore, the assembly structure of the whole machine can be made more compact and stable, and the installation and connection manner is simple.
  • the mounting seat 220 is disposed at the end of the arm assembly 200, which can effectively reduce the torque generated by the motor, minimize the weight of the end of the arm assembly 200, and effectively reduce the weight of the whole machine. , thus extending the flight time.
  • the mount 220 can also be disposed at other locations on the arm assembly 200 depending on the actual application.
  • the mounting seat 220 has a mounting cavity on the upper and lower sides thereof, a motor is fixed in the upper and lower mounting cavities, and a propeller is mounted on each of the motors, thereby forming a single mounting double The structure of the propeller, so that the aircraft can get more flight power and get longer flight time.
  • the aircraft is horizontally placed, the inclination angle of the rotating surface of the propeller 340 and the horizontal plane is ⁇ , and ⁇ is greater than 0 degrees and less than 90 degrees.
  • the reliable propeller can select the appropriate propeller within the above-mentioned inclination angle ⁇ by reliable theoretical calculation and simulation analysis without changing the battery capacity and the power of the driving member 320.
  • the inclination angle ⁇ of the propeller 340 may also be other values, preferably acute angles, which are also within the scope of protection of the present application.
  • the inclination angle ⁇ of the rotating surface of the propeller 340 and the horizontal plane is 28.5 degrees.
  • the data can be obtained by scaling.
  • the inclination angle of the rotating surface of the propeller 340 and the horizontal plane is arranged to be ⁇ 28.5 degrees ⁇ , and the propeller 340
  • the auxiliary lift provided is the highest, and thus the degree of dependence on the reduction and reduction of the propeller 340 is most apparent, so that the aircraft has a longer cruising time under the same load.
  • the arm assembly 200 includes a first arm 230, a second arm 240, a third arm 250, and a fourth arm 260, and the third arm 250 and the fourth arm
  • the height of the end of the arm 260 is higher than the height of the ends of the first arm 230 and the second arm 240, and the first arm 230 and the second arm 240 are disposed on the machine with the aircraft body 100.
  • the left and right sides of the head direction, and the first arm 230 and the second arm 240 respectively extend along the traveling direction of the aircraft, and the distance from the first arm 230 to the air guiding portion 140 It is equal to the distance of the second arm 240 to the air guiding portion 140.
  • the third arm 250 and the fourth arm 260 are disposed on a top surface of the aircraft body 100 in a tail direction, and the third arm and the fourth arm respectively extend in a vertical upward direction.
  • the distance from the third arm 250 to the air guiding portion 140 is equal to the distance from the fourth arm 260 to the air guiding portion 140.
  • the first arm 230, the second arm 240, the third arm 250, and the fourth arm 260 are connected to the aircraft body 100.
  • the cross-sectional dimension at the junction is greater than the cross-sectional dimension at the junction with the mount 220.
  • the first arm 230, the second arm 240, the third arm 250, and the fourth The cross-sectional dimension of the arm 260 tends to gradually decrease from the connection of the arm to the aircraft body 100 to the direction of the mount 200, so that not only the connection between the arm and the aircraft body 100 can be ensured.
  • connection area is large, so that it has higher connection strength, and the same weight can also reduce the overall weight of the arm, thereby reducing the weight of the whole machine, reducing the load of the propeller, and prolonging the flight time.
  • the rear end of the first arm 230 is provided with a fixing portion connected to the aircraft body 100.
  • the fixing portion extends forwardly by a cantilever, and the thickness of the fixing portion is greater than the thickness of the cantilever.
  • the first arm 230 and the second arm 240 are preferably cylinders whose outer surface is a continuous curved surface, and can be maximized under the premise of ensuring high connection strength.
  • Limiting the wind resistance of the flying raft; the third arm 250 and the fourth arm 260 are both identical in structure, and the third arm has a windward side and a side on the left and right sides, the side The width of the side surface is larger than the width of the windward surface, and the area of the side surface is larger than the area of the windward surface, so that the third arm is triangular.
  • An obtuse angle is formed between the windward surface and the horizontal plane, thereby reducing the contact area between the third arm 250 and the fourth arm 260 and the wind, thereby further reducing the wind resistance and improving the endurance of the aircraft.
  • a reinforcing rod is further connected between the third arm 250 and the fourth arm 260, and the reinforcing rod may be integrally formed or assembled, so that the third can be further improved. The structural strength of the arm 250 and the fourth arm 260 is prevented from being broken due to excessive force, which affects the service life of the aircraft.
  • the first arm 230, the second arm 240, the third arm 250, and the fourth arm 260 are all in a direction away from the symmetry axis of the aircraft. Extend outwards. Specifically, the first arm 230 and the second arm 240 are extended outwardly along the left and right sides of the head.
  • the third arm 250 and the fourth arm 260 extend vertically upward and obliquely away from the aircraft body 100, and extend outward along the left and right sides of the tail, thereby not only
  • the propellers on the adjacent first and second arms 230 and 240, the third arm 250, and the fourth arm 260 have sufficient and safe rotational space to avoid
  • the arm distance is too close, collision interference occurs, affecting the service life; the same can also make the arrangement of the four propellers 340 more balanced, and the weight of the aircraft body 100 is more balanced, so that the flight of the aircraft in the air is more stable.
  • the flight attitude is more stable.
  • the aircraft body 100 includes a left drag reducing portion 120 disposed on the left side of the aircraft body 100 and a right drag reducing portion 130 disposed on the right side of the aircraft body, and the left drag reducing portion 120 And the right drag reducing portion 130 is provided with a curved surface.
  • the left drag reducing portion 120 and the right drag reducing portion 130 are respectively a left side wall and a right side wall of the aircraft main body 100, and the curved surfaces are surfaces of the left side wall and the right side wall.
  • the arc surface extends along a top surface to a bottom surface of the aircraft body 100, that is, the left side wall and the right side wall are approximately cylindrical, thereby reducing the left and right directions of the aircraft in flight Side wind resistance
  • the lateral wind during the low-altitude aircraft makes the aircraft's navigation route deviate, reducing the propeller load and prolonging the flight time.
  • a central portion of the top surface of the aircraft body 100 protrudes upwardly from a wind guiding portion 140, and the air guiding portion 140 extends from the handpiece 160 to the Referring to the tail 170, further, along the direction of the nose 160 from the tail 170, the air guiding portion 140 firstly extends upwardly from the handpiece 160 to the tail 170 and then from the The handpiece 160 extends smoothly downwardly toward the tail 170.
  • the air guiding portion 140 coincides with an axis of symmetry of the aircraft, and is an elongated protrusion extending along a direction from the hand piece 160 to the tail 170, and a top surface of the air guiding portion 140
  • the arc surface has a certain width, thereby playing a good guiding effect on the flight of the aircraft.
  • the aircraft body 100 has a cavity therein for mounting a control circuit board, a battery, etc., which can be closed by a mating cover.
  • a portion of the air guiding portion 140 located at the head 160 is raised to a certain height, and the height of the air guiding portion 140 is gradually decreasing toward the tail 170.
  • the head is The thickness is greater than the thickness of the tail.
  • This structure can not only provide the aircraft body with as large a mounting cavity as possible on the basis of satisfying excellent flight performance, so as to facilitate installation and accommodation of various devices or components, including a battery assembly and a chip assembly, the aircraft body
  • the top surface is provided with an upper cover, and the upper cover has a snoring state and a closed state with respect to the aircraft body.
  • the air guiding portion 140 can make the aircraft have better aerodynamic performance, better flight performance and longer life during the cruising time.
  • the bottom of the aircraft body 100 is provided with a landing gear. The installation of the landing gear at the bottom of the aircraft body 100 ensures that the aircraft is safer and more stable when landing on the ground.
  • a wind guiding portion 150 is further recessed on a top surface of the aircraft main body 100, and the air guiding portion 150 is located at the air guiding portion 140 and the left drag reducing portion 120 and the right drag reducing portion.
  • the air guiding portion 150 is formed by smoothly extending downward from the air guiding portion 140 and extending upward to the left drag reducing portion 120 and/or the right drag reducing portion 130.
  • the thickness of the main body of the aircraft is used to reduce the weight and ensure excellent endurance performance.
  • a concave portion is symmetrically disposed between the first arm 230, the second arm 240, and the handpiece 160, and a surface of the concave portion is a curved surface, thereby reducing the weight of the aircraft body. , reduce the wind resistance of the flying raft .
  • the end of the tail 170 is symmetrically provided with a recess, thereby further reducing the weight of the aircraft body 100
  • the aircraft has two states, a first state and a second state, respectively, and the first state is a state in which the aircraft is horizontally flying forward or stationary on the bottom surface, at the first state.
  • the rotating surface of the propeller 340 and the horizontal plane have the inclination angle ⁇ , and the plane of the bottom surface of the aircraft body 100 is parallel to the horizontal plane; the inclination angle ⁇ of the rotating surface of the propeller 340 and the horizontal plane is greater than 0 degrees.
  • the inclination angle ⁇ of the rotating surface of the propeller 340 and the horizontal plane is 28.5 degrees.
  • the rotating surface of the propeller 340 is inclined with respect to the horizontal plane, thereby generating a component force that overcomes the gravity of the aircraft itself, reducing the load of the propeller 340, improving the sailing time, and a horizontal component, the horizontal direction.
  • the direction of force is the direction of travel of the aircraft.
  • the second state is a state in which the aircraft is vertically flying upward or hovering in the air. In the second state, the rotating surface of the propeller 340 is parallel to the horizontal plane, and the plane of the aircraft bottom surface and the horizontal plane have the Tilt angle ⁇ .

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  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
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  • Details Of Aerials (AREA)

Abstract

本申请公开了一种飞行器，包括飞行器主体、设置于所述飞行器主体上的机臂组件、及设置于所述机臂组件上的动力装置，所述动力装置包括驱动件、及与所述驱动件连接的螺旋桨，所述螺旋桨的旋转面沿所述机头的行进方向偏转、并与所述飞行器主体倾斜布置。当飞行器前行时，飞行器主体与水平面平行，通过将飞行器主体上表面设计为弧面，下表面设计为平面，使气流经过飞行器主体时在上、下表面产生压力差从而产生爬升力，由此为所述飞行器主体起到托举作用，由此来降低对所述螺旋桨的依赖，降低所述螺旋桨的负载，从而大大降低电机功耗以达到在同样的电池和动力系统配置下飞行器能够具备更长的续航时间。

Description

飞行器 技术领域
[0001] 本申请涉及飞行器技术领域， 尤其是涉及一种飞行器。
背景技术
[0002] 近几年来， 不断兴起的多旋翼飞行器因其具有的成本低、 易操作、 具有高度灵 活性和可以超低空飞行等特点越来越受到各行各业的广泛使用， 现有的大多数 飞行器主要应用于科学研究、 地理探测、 农业浇灌及视频拍摄等领域。 目前， 由于电池和动力系统等的效率问题， 导致飞行器飞行吋间较短， 基本维持在 10-3 0分钟的水平， 其主要原因是因为多旋翼飞行器的螺旋桨几乎承担了全部飞行器 重量， 从而导致飞行器需要较大的功率， 然而因为飞行器的飞行器主体尺寸不 宜过大， 所以限制了电池容量。 因此， 上述技术问题是多旋翼飞行器一技术瓶 颈， 短期内难以突破。
技术问题
问题的解决方案
技术解决方案
[0003] 基于此， 本申请在于克服现有技术的缺陷， 提供一种降低螺旋桨负载、 延长飞 行器飞行吋间且结构简单的飞行器。
[0004] 本申请的目的是这样实现的：
[0005] 一种飞行器， 包括飞行器主体、 设置于所述飞行器主体上的机臂组件、 设置于 所述机臂组件上的动力装置， 所述动力装置包括驱动件、 及与所述驱动件连接 的螺旋桨， 所述飞行器主体一端为机头， 另一端为机尾， 所述螺旋桨相对于所 述飞行器主体倾斜设置。
[0006] 下面对技术方案作进一步的说明：
[0007] 进一步地， 所述飞行器水平放置吋， 所述螺旋桨的旋转面与水平面的倾斜角为 δ， 且 δ大于 0度小于 90度。
[0008] 进一步地， 所述飞行器水平放置吋， 所述螺旋桨的旋转面与水平面的倾斜角 δ 为 28.5度。
[0009] 进一步地， 所述机头到所述机尾的顶面的长度大于所述机头到所述机尾底面的 长度。
[0010] 进一步地， 所述飞行器主体的顶面的曲率大于底面的曲率。
[0011] 进一步地， 所述机臂组件包括第一机臂、 第二机臂、 第三机臂和第四机臂， 所 述第一机臂和所述第二机臂布置于所述飞行器主体的机头方向的左右两侧， 并 且所述第一机臂和所述第二机臂分别沿所述飞行器行进方向延伸设置， 所述第 三机臂和所述第四机臂设置于所述飞行器主体的机尾方向的顶面上， 所述第三 机臂和所述第四机臂沿垂直向上方向延伸设置。
[0012] 进一步地， 所述第一机臂、 所述第二机臂、 所述第三机臂和所述第四机臂均沿 远离所述飞行器的对称轴方向向外延伸设置。
[0013] 进一步地， 所述飞行器主体包括设置在所述飞行器主体左侧的左减阻部和设置 在所述飞行器主体右侧的右减阻部， 所述左减阻部和所述右减阻部均设有弧面
[0014] 进一步地， 所述飞行器主体的顶面中部向上凸设一导风部， 所述导风部自所述 机头延伸至述机尾。
[0015] 进一步地， 所述飞行器主体的顶面还凹设有引风部， 所述引风部位于所述导风 部与所述减阻部之间， 所述引风部自所述导风部向下平滑延伸再向所述减阻部 向上平滑延伸形成。
[0016] 进一步地， 所述机头前端与所述第一机臂、 第二机臂之间对称设有凹入部。
[0017] 进一步地， 所述机尾末端对称设有凹陷部。
[0018] 本申请还提供一种飞行器， 包括一飞行器主体， 所述飞行器前端为一机头， 后 端为一机尾；
[0019] 一动力装置设于所述飞行器主体上， 所述动力装置用于驱动一螺旋桨；
[0020] 所述飞行器具有两种状态分别为第一状态及第二状态， 在第一状态吋， 所述螺 旋桨的旋转面与水平面具有一倾斜角； 在第二状态吋， 所述螺旋桨的旋转面与 水平面平行。
[0021] 进一步地， 在第一状态吋， 所述飞行器主体底面所在的平面与水平面平行。 [0022] 进一步地， 在第二状态吋， 所述飞行器底面所在的平面与水平面具有一倾斜角
[0023] 本申请还提供一种飞行器， 包括一飞行器主体， 所述飞行器前端为一机头， 后 端为一机尾；
[0024] 一动力装置设于所述飞行器主体上， 所述动力装置用于驱动一螺旋桨；
[0025] 当所述飞行器水平向前飞行或者静止在地面上吋， 所述飞行器主体底面所在的 平面与所述水平面平行；
[0026] 当所述飞行器垂直向上飞行或者悬停在空中吋， 所述飞行器主体底面所在的平 面与所述水平面具有一倾斜角。
[0027] 进一步地， 当所述飞行器水平向前飞行或者静止在地面上吋， 所述螺旋桨的旋 转面与水平面具有一倾斜角。
[0028] 进一步地， 当所述飞行器垂直向上飞行或者悬停在空中吋， 所述螺旋桨的旋转 面与水平面平行。
发明的有益效果
有益效果
[0029] 上述飞行器通过将所述螺旋桨的旋转面与所述飞行器主体呈倾斜布置的结构， 当飞行器向前飞行吋， 飞行器主体与水平面平行， 通过将所述机头到所述机尾 的顶面的长度设置成大于所述机头到所述机尾底面的长度， 从而使得气流经过 飞行器主体吋在上、 下表面产生压力差从而产生爬升力， 由此对所述飞行器主 体起到托举作用， 由此来降低飞行器对所述螺旋桨的依赖， 从而降低所述螺旋 桨的负载， 从而大大降低电机功耗以达到在同样的电池和动力系统配置下飞行 器能够具备更长的续航吋间。
对附图的简要说明
附图说明
[0030] 图 1为本申请实施例所述的飞行器的前行状态示意图；
[0031] 图 2为本申请实施例所述的飞行器的结构示意图；
[0032] 图 3为本申请实施例所述的飞行器的俯视图；
[0033] 图 4为本申请实施例所述的飞行器的侧视图； [0034] 图 5为本申请实施例所述的飞行器的前视图；
[0035] 图 6为本申请实施例所述的飞行器的后视图。
[0036] 附图标记说明：
[0037] 100、 飞行器主体， 120、 左减阻部， 130、 右减阻部， 140、 导风部， 150、 引 风部， 160、 机头， 170、 机尾， 200、 机臂组件， 220、 安装座， 230、 第一机臂 ， 240、 第二机臂， 250、 第三机臂， 260、 第四机臂， 300、 动力装置， 320、 驱 动件， 322、 传动件， 340、 螺旋桨， 400、 起落架。
本发明的实施方式
[0038] 下面对本申请的实施例进行详细说明：
[0039] 如图 1至图 4所示， 一种飞行器， 包括飞行器主体 100、 设置于所述飞行器主体 1 00上的机臂组件 200、 及固定于所述机臂组件 200上的动力装置 300， 所述动力装 置 300包括驱动件 320、 及与所述驱动件 320连接的螺旋桨 340， 所述飞行器主体 1 00的一端为机头 160， 另一端为机尾 170;
[0040] 所述螺旋桨 340相对于所述飞行器主体 100倾斜布置， 其中， 所述螺旋桨 340沿 所述机头的行进方向倾斜布置。
[0041] 在本优选实施例的所述飞行器中， 所述飞行器主体 100上设置的所述机臂组件 2 00包括四个机臂， 每个机臂上均安装有所述驱动件 320， 以及固定于所述驱动件 320上的螺旋桨 340， 且在整机结构布置上将四个所述螺旋桨 340的旋转面与所述 飞行器主体 100的行进方向呈倾斜状布置， 具体的所述飞行器主体 100包括机头 1 60， 四个所述螺旋桨 340的倾斜方向为朝所述飞行器主体 100的所述机头 160的方 向偏转倾斜。
[0042] 基于此， 所述飞行器主体 100的顶面面积大于所述飞行器主体 100的底面面积使 得所述飞行器主体 100大致成拱型结构， 进一步地， 所述机头 160到所述机尾 170 的顶面的长度大于所述机头 160到所述机尾 170底面的长度， 且所述飞行器主体 1 00的顶面的曲率大于底面的曲率从而使得飞行器向前飞行吋， 气流经过飞行器 主体 100吋在上、 下表面产生压力差从而产生爬升力， 由此对所述飞行器主体 10 0起到托举作用， 由此来降低对所述螺旋桨 340的依赖， 降低所述螺旋桨 340的负 载， 从而大大降低电机功耗以达到在同样的电池和动力系统配置下飞行器能够 具备更长的续航吋间的目的。 优选的， 四个所述螺旋桨 340的旋转面均相互平行
[0043] 所述飞行器主体 100的顶面中部向上凸设一导风部 140， 所述导风部 140自所述 机头 160延伸到所述机尾 170。 当飞行器向前飞行吋， 飞行器主体与水平面平行 ， 可以使气流经过所述飞行器主体 100吋在所述导风部 170和底面之间产生压力 差， 从而产生爬升力， 因而可以减小所述螺旋桨 340的负载， 让更多的动力用于 飞行器的正常飞行， 以使得飞行器具备更长的续航吋间。
[0044] 在本实施例中， 所述机臂组件 200上设有安装座 220， 所述驱动件 320设置于所 述安装座 220内， 所述驱动件 320包括传动件 322， 所述螺旋桨 340与所述传动件 3 22连接。 其中， 所述安装座 220与机臂的数量对应， 即每个机臂均设有一个所述 安装座 220， 所述安装座 220具体安装于机臂的末端， 所述安装座 220为与机臂一 体成型， 以使其具备足够的整体结构强度。 此外， 所述安装座 220为设有安装腔 的框型结构， 该框型结构优选为圆柱体， 所述驱动件 320为电机， 将该电机安装 于上述安装腔内， 之后装配所述螺旋桨 340， 由此可以使整机的装配结构更加紧 凑、 稳固， 安装连接方式简单。
[0045] 另外， 将所述安装座 220布设于所述机臂组件 200的末端， 可以有效减少电机产 生的力矩， 使所述机臂组件 200末端的重量降至最低， 有效地减轻整机重量， 从 而延长飞行吋间。 当然， 根据实际应用需要所述安装座 220也可以设置于所述机 臂组件 200上的其他位置。 在另一个实施例中， 所述安装座 220的上下两侧均设 有安装腔， 上下两个安装腔内均固定电机， 并在每个电机上均安装一个螺旋桨 ， 由此形成单安装座双螺旋桨的结构， 如此可以使飞行器获得更大的飞行动力 ， 获得更长的飞行吋间。
[0046] 如图 4所示， 所述飞行器水平放置吋， 所述螺旋桨 340的旋转面与水平面的倾斜 角为 δ， 且 δ大于 0度小于 90度。 实际使用中， 根据飞行器的不同尺寸和重量情况 ， 在不改变电池容量和驱动件 320的功率情况下， 通过可靠的理论计算和仿真分 析， 可以在上述倾斜角 δ范围内选择合适的所述螺旋桨 340的旋转面和水平面的 实际倾斜角 δ的值， 从而使所述螺旋桨 340所提供的辅助升力足够， 从而减小所 述螺旋桨 340的负载负担， 进而可以显著地缓解电池容量不足及驱动件 320功率 受限的短板。 当然， 在其他实施例中， 所述螺旋桨 340的倾斜角 δ也可以是其它 数值， 优选为锐角， 也都在本申请的保护范围内。
[0047] 进一步的， 在本实施例中优选所述螺旋桨 340的旋转面与水平面的倾斜角 δ为 28 .5度。 根据理论计算和仿真分析得到的数据通过换算可以得出， 在电池容量和电 机功率一定的情况下， 将所述螺旋桨 340的旋转面与水平面的倾斜角布置 δ为 28.5 度吋， 所述螺旋桨 340提供的辅助升力最高， 进而对所述螺旋桨 340的减负和减 少依赖的程度最为明显， 从而使飞行器在相同载重情况下具有更长的续航吋间
[0048] 如图 2所示， 所述机臂组件 200包括第一机臂 230、 第二机臂 240、 第三机臂 250 和第四机臂 260， 所述第三机臂 250和第四机臂 260末端的高度高于所述第一机臂 230和第二机臂 240末端的高度， 所述第一机臂 230和所述第二机臂 240布置于与 所述飞行器主体 100的机头方向的左右两侧， 并且所述第一机臂 230和所述第二 机臂 240分别沿所述飞行器行进方向延伸设置， 所述第一机臂 230到所述导风部 1 40的距离等于所述第二机臂 240到所述导风部 140的距离。 所述第三机臂 250和所 述第四机臂 260设置于所述飞行器主体 100的机尾方向的顶面上， 所述第三机臂 和所述第四机臂分别沿垂直向上方向延伸设置， 所述第三机臂 250到所述导风部 140的距离等于所述第四机臂 260到所述导风部 140的距离。 通过上述布置结构不 仅满足载重要求的前提下， 还能使机体结构更加紧凑， 占用更小的空间， 同吋 提升飞行器的飞行性能。
[0049] 请参照图 5、 图 6， 在另一个实施例中， 所述第一机臂 230、 第二机臂 240、 第三 机臂 250和第四机臂 260与所述飞行器主体 100连接处的横截面尺寸大于与所述安 装座 220连接处的横截面尺寸， 进一步地， 所述第一机臂 230、 所述第二机臂 240 、 所述第三机臂 250和所述第四机臂 260的截面尺寸由机臂与所述飞行器主体 100 的连接处至所述安装座 200的方向均呈逐渐减小的趋势， 如此不仅可以确保机臂 与所述飞行器主体 100的连接处的连接面积大， 从而具备更高的连接强度， 同吋 也可以降低机臂的整体重量， 从而减轻整机重量， 减小螺旋桨的负载， 延长飞 行吋间。 所述第一机臂 230后端设有一固定部与所述飞行器主体 100相连， 自所 述固定部向前延伸一悬臂， 所述固定部的厚度大于所述悬臂的厚度。
[0050] 此外， 在另一个实施例中所述第一机臂 230和所述第二机臂 240优选为外表面为 连续曲面的柱体， 在保证较高连接强度的前提下还可以尽最大限度的降低飞行 吋的风阻； 所述第三机臂 250和所述第四机臂 260两者结构相同， 所述第三机臂 具有一迎风面及位于左右两侧的一侧面， 所述侧面的宽度大于所述迎风面的宽 度， 所述侧面的面积大于所述迎风面的面积， 使得所述第三机臂呈三角板状。 所述迎风面与水平面之间形成钝角， 由此可以减少飞行吋所述第三机臂 250和所 述第四机臂 260与风的接触面积， 从而进一步降低风阻， 提高飞行器的续航能力 。 进一步优选的， 所述第三机臂 250和所述第四机臂 260间还连接有加固杆， 该 加固杆可以是一体成型的， 也可以是装配上去的， 如此可以进一步提高所述第 三机臂 250和所述第四机臂 260的结构强度， 避免因受力过大而发生折断， 影响 飞行器的使用寿命。
[0051] 请参照图 6， 所述第一机臂 230、 所述第二机臂 240、 所述第三机臂 250及所述第 四机臂 260均沿远离所述飞行器的对称轴的方向向外延伸设置。 具体的是， 将所 述第一机臂 230和所述第二机臂 240沿机头的左、 右侧向外延伸扩展。 所述第三 机臂 250及所述第四机臂 260向远离所述飞行器主体 100的方向垂直向上伸展且倾 斜布置， 同吋沿机尾的左、 右侧向外延伸拓展， 由此不仅可以使得相邻的所述 第一机臂 230和所述第二机臂 240上的螺旋桨、 所述第三机臂 250和所述第四机臂 260上的螺旋桨具有足够且安全的转动空间， 避免机臂距离过近， 发生碰撞干涉 ， 影响使用寿命； 同吋还可以使四个所述螺旋桨 340的布置更加平衡， 分担所述 飞行器主体 100的重量更加均衡， 从而使飞行器在空中的飞行更加平稳， 飞行姿 态更加稳定。
[0052] 进一步地， 所述飞行器主体 100包括设置在所述飞行器主体 100左侧的左减阻部 120和设置在所述飞行器主体右侧的右减阻部 130， 所述左减阻部 120和所述右减 阻部 130均设有弧面。 在本实施例中， 所述左减阻部 120和所述右减阻部 130分别 为所述飞行器主体 100的左侧壁和右侧壁， 该弧面为左侧壁和右侧壁的表面形状 ， 且该弧面沿所述飞行器主体 100的顶面至底面方向延伸设置， 即左侧壁和右侧 壁近似为圆柱体， 由此可以减小飞行中的飞行器左、 右两个方向的侧风阻， 降 低飞行器前行过程中侧向风使飞行器的航行路线产生偏离的影响， 降低螺旋桨 的负载， 从而延长飞行吋间。
[0053] 如图 3所示， 在一个优选的实施例中， 所述飞行器主体 100的顶面中部向上凸设 一导风部 140， 所述导风部 140自所述机头 160延伸至所述机尾 170， 进一步地， 沿着所述机头 160自所述机尾 170的方向， 所述导风部 140先自所述机头 160向所 述机尾 170向上平滑延伸再自所述机头 160向所述机尾 170平滑向下延伸。 所述导 风部 140与所述飞行器的对称轴重合， 且其为沿所述机头 160至所述机尾 170的方 向延伸布置的长条形凸起， 所述导风部 140的顶面具有一定宽度的弧面， 由此在 飞行器飞行吋起到良好的导流作用。 此外， 所述飞行器主体 100内部具有空腔， 用于安装控制电路板、 电池等， 该空腔可以通过匹配的盖体封闭。 该导风部 140 位于所述机头 160处的部分隆起一定高度， 且朝所述机尾 170的方向所述导风部 1 40的高度呈逐渐递减的趋势， 进一步地， 所述机头的厚度大于所述机尾的厚度 。 此结构不仅可以所述飞行器主体 100在满足优良的飞行性能的基础上使飞行器 主体具备尽量大的安装空腔， 以便于安装容纳各种装置或部件， 包括电池组件 及芯片组件， 所述飞行器主体顶面设有一上盖， 所述上盖相对于所述飞行器主 体具有打幵状态及闭合状态。 同吋所述导风部 140可以使飞行器具有更好的空气 动力学性能， 飞行性能更佳， 续航吋间更长。 此外， 所述飞行器主体 100的底部 设有起落架。 在所述飞行器主体 100的底部安装设置所述起落架， 可以确保飞行 器降落地面吋更加安全、 平稳。
[0054] 此外， 所述飞行器主体 100的顶面还凹设有引风部 150， 所述引风部 150位于所 述导风部 140与所述左减阻部 120、 所述右减阻部 130之间， 所述引风部 150是自 所述导风部 140向下平滑延伸再向所述左减阻部 120和 /或所述右减阻部 130向上平 滑延伸形成。 在本实施例中优选在所述导风部 140的两侧设置两个所述引风部 15 0， 该引风部 150过渡连接所述导风部 140与左、 右侧壁， 不仅可以减少飞行器主 体的厚度， 以降低重量， 保证优良的续航性能， 同吋可以减小迎风风阻， 空气 抬升效果会更好， 可以进一步减少所述螺旋桨 340的负载， 提高续航吋间。 另外 ， 所述第一机臂 230、 所述第二机臂 240与所述机头 160之间对称设有凹入部， 且 该凹入部的表面设为弧面， 由此可以减小飞行器主体重量， 降低飞行吋的风阻 。 所述机尾 170末端对称设有凹陷部， 由此可以进一步减小飞行器主体 100重量
[0055] 本实施例中， 所述飞行器具有两种状态分别为第一状态及第二状态， 第一状态 即为当所述飞行器水平向前飞行或者静止在底面上吋的状态， 在第一状态吋， 所述螺旋桨 340的旋转面与水平面具有所述倾斜角 δ， 所述飞行器主体 100底面所 在的平面与所述水平面平行； 所述螺旋桨 340的旋转面与水平面的倾斜角 δ大于 0 度小于 90度， 优选地， 所述螺旋桨 340的旋转面与水平面的倾斜角 δ为 28.5度。 所 述螺旋桨 340的旋转面与水平面倾斜， 由此产生一个克服所述飞行器自身重力的 分力， 减少所述螺旋桨 340的负载， 提高航行吋间， 以及一个水平方向的分力， 水平方向的分力方向为所述飞行器的行进方向。 第二状态即为当所述飞行器垂 直向上飞行或者悬停在空中吋的状态， 在第二状态吋， 所述螺旋桨 340的旋转面 与水平面平行， 所述飞行器底面所在的平面与水平面具有所述倾斜角 δ。
[0056] 以上所述实施例的各技术特征可以进行任意的组合， 为使描述简洁， 未对上述 实施例中的各个技术特征所有可能的组合都进行描述， 然而， 只要这些技术特 征的组合不存在矛盾， 都应当认为是本说明书记载的范围。
[0057] 以上所述实施例仅表达了本申请的几种实施方式， 其描述较为具体和详细， 但 并不能因此而理解为对本申请保护范围的限制。 应当指出的是， 对于本领域的 普通技术人员来说， 在不脱离本申请构思的前提下， 还可以做出若干变形和改 进， 这些都属于本申请的保护范围。 因此， 本申请专利的保护范围应以所附权 利要求为准。

Claims

权利要求书
[权利要求 1] 一种飞行器， 其特征在于， 包括飞行器主体、 设置于所述飞行器主体 上的机臂组件、 设置于所述机臂组件上的动力装置， 所述动力装置包 括驱动件、 及与所述驱动件连接的螺旋桨， 所述飞行器主体一端为机 头， 另一端为机尾， 所述螺旋桨相对于所述飞行器主体倾斜设置。
[权利要求 2] 根据权利要求 1所述的飞行器， 其特征在于， 所述飞行器水平放置吋
， 所述螺旋桨的旋转面与水平面的倾斜角为 δ， 且 δ大于 0度小于 90度
[权利要求 3] 根据权利要求 1或 2所述的飞行器， 其特征在于， 所述飞行器水平放置 吋， 所述螺旋桨的旋转面与水平面的倾斜角 δ为 28.5度。
[权利要求 4] 根据权利要求 1所述的飞行器， 其特征在于， 所述机头到所述机尾的 顶面的长度大于所述机头到所述机尾底面的长度。
[权利要求 5] 根据权利要求 1所述的飞行器， 其特征在于， 所述飞行器主体的顶面 的曲率大于底面的曲率。
[权利要求 6] 根据权利要求 1所述的飞行器， 其特征在于， 所述机臂组件包括第一 机臂、 第二机臂、 第三机臂和第四机臂， 所述第一机臂和所述第二机 臂布置于所述飞行器主体的机头方向的左右两侧， 并且所述第一机臂 和所述第二机臂分别沿所述飞行器行进方向延伸设置， 所述第三机臂 和所述第四机臂设置于所述飞行器主体的机尾方向的顶面上， 所述第 三机臂和所述第四机臂沿垂直向上方向延伸设置。
[权利要求 7] 根据权利要求 6所述的飞行器， 其特征在于， 所述第一机臂、 所述第 二机臂、 所述第三机臂和所述第四机臂均沿远离所述飞行器的对称轴 方向向外延伸设置。
[权利要求 8] 根据权利要求 1所述的飞行器， 其特征在于， 所述飞行器主体包括设 置在所述飞行器主体左侧的左减阻部和设置在所述飞行器主体右侧的 右减阻部， 所述左减阻部和所述右减阻部均设有弧面。
[权利要求 9] 根据权利要求 1所述的飞行器， 其特征在于， 所述飞行器主体的顶面 中部向上凸设一导风部， 所述导风部自所述机头延伸至述机尾。 根据权利要求 9所述的飞行器， 其特征在于， 所述飞行器主体的顶面 还凹设有引风部， 所述引风部位于所述导风部与所述减阻部之间， 所 述弓 I风部自所述导风部向下平滑延伸再向所述减阻部向上平滑延伸形 成。
根据权利要求 1所述的飞行器， 其特征在于， 所述机头前端与所述第 一机臂、 所述第二机臂之间对称设有凹入部。
根据权利要求 1所述的飞行器， 其特征在于， 所述机尾末端对称设有 凹陷部。
一种飞行器， 其特征在于， 包括一飞行器主体， 所述飞行器前端为一 机头， 后端为一机尾；
一动力装置设于所述飞行器主体上， 所述动力装置用于驱动一螺旋桨 所述飞行器具有两种状态分别为第一状态及第二状态， 在第一状态吋 ， 所述螺旋桨的旋转面与水平面具有一倾斜角； 在第二状态吋， 所述 螺旋桨的旋转面与水平面平行。
根据权利要求 13所述的飞行器， 其特征在于， 在第一状态吋， 所述飞 行器主体底面所在的平面与水平面平行。
根据权利要求 13所述的飞行器， 其特征在于， 在第二状态吋， 所述飞 行器底面所在的平面与水平面具有一倾斜角。
一种飞行器， 其特征在于， 包括一飞行器主体， 所述飞行器前端为一 机头， 后端为一机尾；
一动力装置设于所述飞行器主体上， 所述动力装置用于驱动一螺旋桨 当所述飞行器水平向前飞行或者静止在地面上吋， 所述飞行器主体底 面所在的平面与所述水平面平行；
当所述飞行器垂直向上飞行或者悬停在空中吋， 所述飞行器主体底面 所在的平面与所述水平面具有一倾斜角。
根据权利要求 16所述的飞行器， 其特征在于， 当所述飞行器水平向前 飞行或者静止在地面上吋， 所述螺旋桨的旋转面与水平面具有一倾斜 角。
[权利要求 18] 根据权利要求 16所述的飞行器， 其特征在于， 当所述飞行器垂直向上 飞行或者悬停在空中吋， 所述螺旋桨的旋转面与水平面平行。
PCT/CN2017/083456 2016-05-17 2017-05-08 飞行器 WO2017198082A1 (zh)

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CN205916327U (zh) * 2016-05-17 2017-02-01 亿航智能设备（广州）有限公司 飞行器
CN105882953B (zh) * 2016-05-17 2018-10-02 亿航智能设备（广州）有限公司 飞行器

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7874513B1 (en) * 2005-10-18 2011-01-25 Smith Frick A Apparatus and method for vertical take-off and landing aircraft
CN204623835U (zh) * 2015-04-30 2015-09-09 何春旺 多轴飞行器
CN204642150U (zh) * 2015-04-30 2015-09-16 江苏数字鹰科技发展有限公司 变轴向多旋翼飞行器
CN204688409U (zh) * 2015-04-27 2015-10-07 广州快飞计算机科技有限公司 一种多旋翼和固定翼结合的无人飞行器
CN105882953A (zh) * 2016-05-17 2016-08-24 亿航智能设备（广州）有限公司 飞行器
CN205916327U (zh) * 2016-05-17 2017-02-01 亿航智能设备（广州）有限公司 飞行器

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7874513B1 (en) * 2005-10-18 2011-01-25 Smith Frick A Apparatus and method for vertical take-off and landing aircraft
CN204688409U (zh) * 2015-04-27 2015-10-07 广州快飞计算机科技有限公司 一种多旋翼和固定翼结合的无人飞行器
CN204623835U (zh) * 2015-04-30 2015-09-09 何春旺 多轴飞行器
CN204642150U (zh) * 2015-04-30 2015-09-16 江苏数字鹰科技发展有限公司 变轴向多旋翼飞行器
CN105882953A (zh) * 2016-05-17 2016-08-24 亿航智能设备（广州）有限公司 飞行器
CN205916327U (zh) * 2016-05-17 2017-02-01 亿航智能设备（广州）有限公司 飞行器

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