WO2019079930A1 - 一种可垂直起降的海陆空潜四栖倾转三旋翼无人机 - Google Patents

一种可垂直起降的海陆空潜四栖倾转三旋翼无人机

Info

Publication number
WO2019079930A1
WO2019079930A1 PCT/CN2017/107292 CN2017107292W WO2019079930A1 WO 2019079930 A1 WO2019079930 A1 WO 2019079930A1 CN 2017107292 W CN2017107292 W CN 2017107292W WO 2019079930 A1 WO2019079930 A1 WO 2019079930A1
Authority
WO
WIPO (PCT)
Prior art keywords
airbag
drone
tilting
rotor
air
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2017/107292
Other languages
English (en)
French (fr)
Inventor
张硕
吕宗阳
孙涛
吴玉虎
孙希明
吴振宇
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dalian University of Technology
Original Assignee
Dalian University of Technology
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 Dalian University of Technology filed Critical Dalian University of Technology
Priority to PCT/CN2017/107292 priority Critical patent/WO2019079930A1/zh
Priority to US16/341,402 priority patent/US11305873B2/en
Publication of WO2019079930A1 publication Critical patent/WO2019079930A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; VEHICLES CAPABLE OF TRAVELLING IN OR ON DIFFERENT MEDIA, e.g. AMPHIBIOUS VEHICLES
    • B60F5/00—Other vehicles capable of travelling in or on different media
    • B60F5/02—Other vehicles capable of travelling in or on different media convertible into aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • B64C35/001—Flying-boats; Seaplanes with means for increasing stability on the water
    • B64C35/002—Flying-boats; Seaplanes with means for increasing stability on the water using adjustable auxiliary floats
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B35/00—Vessels or similar floating structures specially adapted for specific purposes and not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B7/00—Collapsible, foldable, inflatable or like vessels
    • B63B7/06—Collapsible, foldable, inflatable or like vessels having parts of non-rigid material
    • B63B7/08—Inflatable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
    • 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 
    • B64C25/54—Floats
    • B64C25/56—Floats inflatable
    • 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
    • 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
    • B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • 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
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B35/00—Vessels or similar floating structures specially adapted for specific purposes and not otherwise provided for
    • B63B2035/006—Unmanned surface vessels, e.g. remotely controlled
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B2207/00—Buoyancy or ballast means
    • B63B2207/04—Pressure equalising or adjusting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
    • B63G2008/002—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations unmanned
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C2009/005—Ailerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2201/00—Airbags mounted in aircraft for any use

Definitions

  • the invention belongs to the technical field of an unmanned aerial vehicle and an unmanned submersible, and particularly relates to an ocean, land and air submersible tilting trirotal unmanned aerial vehicle capable of vertically taking off and landing.
  • the object of the present invention is to provide a sea-land-air submersible tilting three-rotor UAV that can vertically take off and land, and realize the drone in vertical by controlling the submersible device and the tilting three-rotor device.
  • Switching between down mode, fixed wing mode, surface navigation mode and underwater stealth mode gives it the advantages of four drones, enhancing the applicability, maneuverability and efficiency of the drone.
  • a sea-land-air submersible tilting tri-rotor UAV capable of vertically taking off and landing, comprising a fuselage 1, a main wing 2, two ailerons 3, two vertical tails 4, two forward tilting shafts 5, 2 forward tilting seats 6, 2 front motor rotors 7, rear tilting seats 8, rear motor rotors 9, rear tilting shafts 10, propellers 11, two tail rudders 12, right rear airbags 13, airbag controllers 14, Left rear air bag 15, gas cylinder 16, front air bag 17 and control board;
  • the main wing 2 is a wing structure symmetric with respect to the central axis, and is integrally formed with the fuselage 1;
  • the two ailerons 3 are rectangular structures, and are respectively fixedly connected to the tail portions of the wings of the main wing 2, respectively.
  • the two vertical fins 4 are respectively axially fixed on the upper end surface of the main wing 2 and located between the two ailerons 3;
  • the front motor rotor 7 is fixed on the forward tilting base 6, and the forward tilting base 6 is connected to the front portion of the fuselage 1 through the forward tilting shaft 5, and the left and right portions are symmetric with the central axis of the fuselage 1;
  • the independent tilt angle of the front motor rotor 7 ranges from 0° to 100°;
  • the rear motor rotor 9 is fixed on the rear tilting seat 8, and the rear tilting base 8 is connected to the tail of the fuselage 1 through the rear tilting shaft 10, and the tilt angle of the rear motor rotor 9 is -30° ⁇ 30°; independent control of the rotational speed of the two front motor rotors 7 and the rear motor rotors 9 to achieve vertical takeoff and landing and fixed wing modes;
  • the propeller 11 and the two rudders 12 pass through the tail of the fuselage 1 and are connected to the control panel inside the fuselage 1.
  • the two rudders 12 are symmetric with respect to the fuselage 1 and the propeller 11 is located at 2
  • the symmetry axis of the tail rudder 12; the control panel controls the rotation of the two tail rudders 12 to change the direction of navigation, and changes the speed of navigation in the water by controlling the rotation speed of the propeller 11;
  • the right rear air bag 13, the air bag controller 14, the left rear air bag 15, the gas bottle 16 and the front air bag 17 are fixed on the lower surface of the body 1 and the main wing 2, wherein the right rear air bag 13 and the left rear air bag 15 and the front airbag 1 7 are in an isosceles triangle layout, the center of the sea, land and air submarine tilting trirotal drone is on the symmetry line of the isosceles triangle; the right rear airbag 13, the left rear airbag 15 and the front airbag 17 respectively Connected to the cylinder 16 and controlled by the airbag controller 14;
  • the power system of the present invention has high efficiency, and the flying distance is obviously improved compared with the conventional multi-rotor UAV due to the fixed wing mode; Work on flat, mountain, water, and underwater to complete specified tasks such as aerial, ground, surface, and underwater photography, mapping, and concealment.
  • FIG. 1 is a top plan view of the present invention.
  • FIG. 2 is a side elevational view of the present invention.
  • 3 is a bottom plan view of the present invention.
  • 4(a) is a schematic diagram of control in the vertical take-off and landing mode of the present invention.
  • 4(b) is a schematic diagram of the roll control in the vertical take-off and landing mode of the present invention.
  • 4(c) is a schematic diagram of yaw control in the vertical take-off and landing mode of the present invention.
  • FIG. 5 is a schematic diagram of control in a fixed wing mode of the present invention.
  • (6a) is a schematic diagram of pitch control in the underwater mode.
  • (6b) is a schematic diagram of the roll control in the underwater mode.
  • a sea-land-air submersible tilting tri-rotor UAV capable of vertically taking off and landing, including a fuselage 1, a main wing 2, two ailerons 3, and two vertical tails 4, 2 a forward tilting shaft 5, two forward tilting seats 6, two front motor rotors 7, a rear tilting base 8, a rear motor rotor 9, a rear tilting shaft 10, a propeller 11, two tail rudders 12, and a right rear airbag 13
  • the airbag controller 14 the left rear airbag 15, the gas cylinder 16, the front airbag 17, and the control panel.
  • the main wing 2 is a wing-shaped structure that is symmetric with respect to the central axis and is fixed on the upper surface of the fuselage 1; the two ailerons 3 are rectangular structures and are respectively fixed to the tail portions of the wings of the main wing 2; The vertical tails 4 are respectively fixed on the upper surface of the tail end of the main wing 2 with the central axis of the main wing 2 as an axis.
  • the front motor rotor 7 is fixed on the forward tilting base 6, and the forward tilting base 6 is connected to the front part of the fuselage 1 through the forward tilting shaft 5, and the left and right parts are symmetric with the central axis of the fuselage 1;
  • the front motor rotor 7 has an independent tilting angle ranging from 0° to 100°;
  • the rear motor rotor 9 is fixed to the rear tilting seat 8, and the rear tilting base 8 is connected to the tail of the fuselage 1 through the rear tilting shaft 10, and the rear motor rotor 9 tilting angle range is -30 ° ⁇ 30 °.
  • the three-rotor speed is independently controlled to achieve vertical take-off and landing and fixed-wing modes.
  • the propeller 11 and the two rudders 12 pass through the tail of the fuselage 1 and are connected to the control panel inside the fuselage 1.
  • the two rudders 12 are symmetric with respect to the fuselage 1 and the propeller 11 is located at 2 On the axis of symmetry of the rudder 12; the control panel controls the rotation of the two rudders 12 to change the direction of navigation, and changes the speed of the propeller 11 to change the water The speed of navigation.
  • the airbag controller 14, the gas cylinder 16 and the front airbag 17 are sequentially fixed from the rear to the front on the control panel of the body 1, the right rear airbag 13, the left rear airbag 15, the gas cylinder 16 and the front airbag 17
  • the airbag controller 14 is connected to the airbag controller 14 respectively, wherein the right rear airbag 13 and the left rear airbag 15 are symmetrically fixed to the lower end of the wing tail of the main wing 2, respectively, and the air cylinder 16 passes through the airbag controller 14 to the right rear airbag 13, the left rear airbag 15, Front air bag 17.
  • the present invention has four modes of operation:
  • Pitch control When the two front motor rotors 7 of the drone are vertically aligned with the rear motor rotor 9, the pitch angle can be changed by adjusting the difference in the tension between the front rotor 7 and the rear rotor 9. Simultaneously reducing the speed of the front rotor 7 or increasing the speed of the rear rotor 9 can cause the drone to pitch.
  • Rolling control When the two front motor rotors 7 of the drone and the rear motor rotor 9 are vertically slanted upward, the roll angle can be controlled by adjusting the tension difference between the two rotors 7 in front of the drone. Increase the speed of the front right rotor 7 and reduce the speed of the front left rotor 7 to make the drone roll.
  • Yaw control When the two front motor rotors 7 of the drone and the rear motor rotor 9 are vertically slanted upward, the yaw angle can be controlled by adjusting the tilting angle of the rear tilting seat 8, and then Tilting seat 8 tilts a certain angle
  • the two front motor rotors 7 are tilted to the horizontal position ⁇ , and the rear motor rotor 9 is stopped, and the drone is completely controlled by the ailerons 3 and the vertical tails 4.
  • Fixed-wing flight can be achieved by controlling the thrust of the two forward rotors 7 and the aileron 3 steering surface angle.
  • the two front motor rotors 7 and the rear motor rotors 9 of the drone are stopped, and the air cylinder 16 is filled with air to the right rear air bag 13, the left rear air bag 15, and the front air bag 17 through the air bag controller 14 to float the drone.
  • the tail rudder 12 rotates to control the heading of the drone, and the propeller 11 controls the forward and reverse speed of the drone.
  • Pitch control The airbag controller 14 controls the difference between the airbags of the right rear airbag 13 and the left rear airbag 15 and the front airbag 17 to control the underwater pitch angle of the drone. Increasing the air volume of the right rear airbag 13 and the air volume of the left rear airbag 15 reduce the air volume of the front airbag 17, which can cause the drone to pitch.
  • Rolling control The difference between the air storage amount of the right rear airbag 13 and the left rear airbag 15 is controlled by the airbag controller 14 to control the underwater rolling angle of the drone. Increasing the air volume of the right rear air bag 13 and reducing the air storage capacity of the left rear air bag 15 can cause the drone to roll.
  • the rudder 12 rotates to control the heading of the drone, and the propeller 11 controls the forward and reverse speed of the drone.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Ocean & Marine Engineering (AREA)
  • Transportation (AREA)
  • Toys (AREA)

Abstract

一种可垂直起降的海陆空潜四栖倾转三旋翼无人机，在三旋翼无人机的基础上增设右后方气囊（13）、气囊控制器（14）、左后方气囊（15）、气瓶（16）和前方气囊（17）；所述的右后方气囊（13）、气囊控制器（14）、左后方气囊（15）、气瓶（16）和前方气囊（17）均固定在机身（1）和主翼（2）下表面，其中，右后方气囊（13）、左后方气囊（15）和前方气囊（17）三者呈等腰三角形布局，海陆空潜四栖倾转三旋翼无人机重心在等腰三角形的对称线上；右后方气囊（13）、左后方气囊（15）和前方气囊（17）分别与气瓶（16）相连，并通过气囊控制器（14）控制。通过控制潜浮装置和倾转三旋翼装置的方法，实现无人机在垂直起降模式、固定翼模式、水面航行模式和水下潜行模式间切换，从而使其拥有四种无人机的优点，增强无人机的适用性能、可操控性和效率。

Description

一种可垂直起降的海陆空潜四栖倾转三旋翼无人机 技术领域
[0001] 本发明属于无人飞行器和无人潜水器技术领域， 具体涉及一种可垂直起降的海 陆空潜四栖倾转三旋翼无人机。
背景技术
[0002] 目前无人机应用场合越来越多， 对无人机的性能要求工作场合要求越来越高， 如航拍、 侦査、 娱乐、 运输等。 由于无人机工作场景多样， 如平地、 山地、 水 下、 水面、 天上等。 垂直起降无人机对起降条件要求不高， 但是续航吋间载荷 较小。 固定翼无人机续航吋间载荷较大， 但是起降要求高。 无人船能够于水面 工作， 拍摄水面环境， 但是无法飞行， 续航不足。 无人潜水器能够于水下工作 ， 拍摄水下环境， 进行水下隐藏， 但是续航不足。 以上四种无人机各自优缺点 明显， 适用范围、 效率等有一定限制。
技术问题
[0003] 本发明的目的在于提供一种可垂直起降的海陆空潜四栖倾转三旋翼无人机， 通 过控制潜浮装置和倾转三旋翼装置的方法， 实现无人机在垂直起降模式、 固定 翼模式、 水面航行模式和水下潜行模式间切换， 从而使其拥有四种无人机的优 点， 增强无人机的适用性能、 可操控性和效率。
问题的解决方案
技术解决方案
[0004] 本发明的技术方案：
[0005] 一种可垂直起降的海陆空潜四栖倾转三旋翼无人机， 包括机身 1、 主翼 2、 2个 副翼 3、 2个垂直尾翼 4、 2个前倾转轴 5、 2个前倾转座 6、 2个前电机旋翼 7、 后倾 转座 8、 后电机旋翼 9、 后倾转轴 10、 螺旋桨 11、 2个尾舵 12、 右后方气囊 13、 气 囊控制器 14、 左后方气囊 15、 气瓶 16、 前方气囊 17与控制板；
[0006] 所述的主翼 2是以中轴线对称的翼状结构， 与机身 1一体结构； 所述的 2个副翼 3 为长方形结构， 分别固定连接在主翼 2的两侧机翼尾部， 可绕其固定端向机身 1 方向展幵； 2个垂直尾翼 4分别以主翼 2的中轴线为轴， 对称垂直固定在主翼 2尾 端上表面， 位于两个副翼 3间；
[0007] 所述的前电机旋翼 7固定在前倾转座 6上， 前倾转座 6通过前倾转轴 5与机身 1的 前部相连， 左右两部分以机身 1的中轴线对称； 前电机旋翼 7的独立倾转角度范 围为 0°~100°；
[0008] 所述的后电机旋翼 9固定在后倾转座 8上， 后倾转座 8通过后倾转轴 10与机身 1的 尾部连接， 后电机旋翼 9倾转角度范围为 -30°~30°； 两前电机旋翼 7和后电机旋翼 9转速独立控制， 实现垂直起降和固定翼模式；
[0009] 所述的螺旋桨 11和 2个尾舵 12穿过机身 1尾部下方， 连接在机身 1内部的控制板 上， 2个尾舵 12以机身 1对称轴对称， 螺旋桨 11位于 2个尾舵 12的对称轴上； 控制 板控制 2个尾舵 12转动进而改变航行方向， 通过控制螺旋桨 11转速进而改变在水 中航行速度；
[0010] 所述的右后方气囊 13、 气囊控制器 14、 左后方气囊 15、 气瓶 16和前方气囊 17均 固定在机身 1和主翼 2下表面， 其中， 右后方气囊 13、 左后方气囊 15和前方气囊 1 7三者呈等腰三角形布局， 海陆空潜四栖倾转三旋翼无人机重心在等腰三角形的 对称线上； 右后方气囊 13、 左后方气囊 15和前方气囊 17分别与气瓶 16相连， 并 通过气囊控制器 14控制；
发明的有益效果
有益效果
[0011] 本发明的有益效果： 本发明的动力系统效率高， 相对于传统多旋翼无人机， 由 于多了固定翼模式， 续航吋间， 飞行距离都会有明显提升； 适用场景多， 可在 平地、 山地、 水面、 水下进行工作， 从而完成空中、 地面、 水面和水下拍摄、 测绘和隐蔽等指定任务。
对附图的简要说明
附图说明
[0012] 图 1是本发明的俯视示意图。
[0013] 图 2是本发明的侧视示意图。
[0014] 图 3是本发明的仰视示意图。 [0015] 图 4(a)是本发明的垂直起降模式下控制示意图。
[0016] 图 4(b)是本发明的垂直起降模式下的滚转控制示意图。
[0017] 图 4(c)是本发明的垂直起降模式下的偏航控制示意图。
[0018] 图 5为本发明固定翼模式下控制示意图。
[0019] 图 (6a)为水下模式下的俯仰控制示意图。
[0020] 图 (6b)为水下模式下的滚转控制示意图。
[0021] 图中： 1机身； 2主翼； 3副翼 x2; 4垂直尾翼 x2; 5倾转轴 x2;
[0022] 6倾转座 x2; 7电机旋翼 x2; 8后倾转座； 9后电机旋翼； 10后倾转轴；
[0023] 11螺旋桨； 12尾舵 x2; 13右后方气囊； 14气囊控制器； 15左后方气囊；
[0024] 16气瓶； 17前方气囊。
本发明的实施方式
[0025] 以下结合技术方案和附图详细叙述本发明的具体实施方式。
[0026] 结合图 l~6b， 一种可垂直起降的海陆空潜四栖倾转三旋翼无人机， 包括机身 1 、 主翼 2、 2个副翼 3、 2个垂直尾翼 4、 2个前倾转轴 5、 2个前倾转座 6、 2个前电 机旋翼 7、 后倾转座 8、 后电机旋翼 9、 后倾转轴 10、 螺旋桨 11、 2个尾舵 12、 右 后方气囊 13、 气囊控制器 14、 左后方气囊 15、 气瓶 16、 前方气囊 17与控制板。
[0027] 所述的主翼 2是以中轴线对称的翼状结构并固定在机身 1上表面； 所述的 2个副 翼 3为长方形结构， 分别固定在主翼 2的两侧机翼尾部； 2个垂直尾翼 4分别以主 翼 2的中轴线为轴， 对称垂直固定在主翼 2尾端上表面。
[0028] 所述的前电机旋翼 7固定在前倾转座 6上， 前倾转座 6通过前倾转轴 5与机身 1的 前部相连， 左右两部分以机身 1中轴线对称； 左右前电机旋翼 7独立倾转角度范 围为 0°~100°； 后电机旋翼 9固定在后倾转座 8上， 后倾转座 8通过后倾转轴 10与机 身 1的尾部连接， 后电机旋翼 9倾转角度范围为 -30°~30°。 三旋翼转速独立控制， 实现垂直起降和固定翼模式。
[0029] 所述的螺旋桨 11和 2个尾舵 12穿过机身 1尾部下方， 连接在机身 1内部的控制板 上， 2个尾舵 12以机身 1对称轴对称， 螺旋桨 11位于 2个尾舵 12的对称轴上； 控制 板控制 2个尾舵 12转动进而改变航行方向， 通过控制螺旋桨 11转速进而改变在水 中航行速度。
[0030] 所述的气囊控制器 14、 气瓶 16与前方气囊 17依次从后向前固定在机身 1内控制 板上， 右后方气囊 13、 左后方气囊 15、 气瓶 16与前方气囊 17分别与气囊控制器 1 4相连， 其中右后方气囊 13与左后方气囊 15分别对称固定在主翼 2的机翼尾部下 端， 气瓶 16通过气囊控制器 14向右后方气囊 13、 左后方气囊 15、 前方气囊 17。
[0031] 本发明共有四种工作模式：
[0032] (1)垂直起降模式：
[0033] 在垂直起降模式下， 当无人机的 2个前电机旋翼 7与后电机旋翼 9垂直向上吋， 通过同吋控制 2个前电机旋翼 7与后电机旋翼 9的推力大小和方向， 实现无人机姿 态控制。
[0034] 俯仰控制： 当无人机的 2个前电机旋翼 7与后电机旋翼 9垂直向上吋， 通过调节 前方旋翼 7和后方旋翼 9的拉力差， 可实现俯仰角度的变化。 同吋减小前方旋翼 7 转速或增后方旋翼 9转速， 可使无人机产生俯仰。
[0035] 滚转控制： 当无人机的 2个前电机旋翼 7与后电机旋翼 9垂直向上吋， 通过调节 无人机前方两旋翼 7的拉力差， 可实现对滚转角的控制。 增大前方右侧旋翼 7转 速， 减小前方左侧旋翼 7转速， 可使无人机产生滚转。
[0036] 偏航控制： 当无人机的 2个前电机旋翼 7与后电机旋翼 9垂直向上吋， 通过调节 后倾转座 8的倾转角度， 可实现对偏航角度的控制， 将后倾转座 8倾转一定角度
， 可使无人机产生偏航。
[0037] (2)固定翼飞行模式：
[0038] 随着无人机水平速度的增大， 2个前电机旋翼 7倾转到水平位置吋， 后电机旋翼 9停止工作吋， 无人机完全由副翼 3和垂直尾翼 4进行控制。 通过控制 2个前转旋 翼 7的推力大小以及副翼 3舵面角度能够实现固定翼飞行。
[0039] (3)水面航行模式：
[0040] 无人机的 2个前电机旋翼 7与后电机旋翼 9停止工作， 气瓶 16通过气囊控制器 14 向右后方气囊 13、 左后方气囊 15、 前方气囊 17充满空气使无人机漂浮于水面， 尾舵 12左右转动控制无人机航向， 螺旋桨 11控制无人机前进后退速度。
[0041] (4)水下航行模式： [0042] 无人机的 2个前电机旋翼 7与后电机旋翼 9停止工作， 气瓶 16通过气囊控制器 14 向右后方气囊 13、 左后方气囊 15、 前方气囊 17充入适量空气保证无人机潜深。
[0043] 俯仰控制： 通过气囊控制器 14控制气囊右后方气囊 13和左后方气囊 15与前方气 囊 17储气量之差控制无人机水下俯仰角度。 增大右后方气囊 13储气量和左后方 气囊 15储气量， 减小前方气囊 17储气量， 可使无人机产生俯仰。
[0044] 滚转控制： 通过气囊控制器 14控制右后方气囊 13与左后方气囊 15储气量之差从 而控制无人机水下滚转角度。 增大右后方气囊 13储气量， 减小左后方气囊 15储 气量， 可使无人机产生滚转。 尾舵 12左右转动控制无人机航向， 螺旋桨 11控制 无人机前进后退速度。

Claims

权利要求书 [权利要求 1] 一种可垂直起降的海陆空潜四栖倾转三旋翼无人机， 其特征在于， 所 述的海陆空潜四栖倾转三旋翼无人机在三旋翼无人机的基础上， 增设 右后方气囊 (13)、 气囊控制器 (14)、 左后方气囊 (15)、 气瓶 (16)和前方 气囊 (17); 所述的右后方气囊 (13)、 气囊控制器 (14)、 左后方气囊 (15)、 气瓶 (16) 和前方气囊 (17)均固定在机身 (1)和主翼 (2)下表面， 其中， 右后方气囊 (13)、 左后方气囊 (15)和前方气囊 (17)三者呈等腰三角形布局， 海陆空 潜四栖倾转三旋翼无人机重心在等腰三角形的对称线上； 右后方气囊 (13)、 左后方气囊 (15)和前方气囊 (17)分别与气瓶 (16)相连， 并通过气 囊控制器 (14)控制。 [权利要求 2] 根据权利要求 1所述的可垂直起降的海陆空潜四栖倾转三旋翼无人机， 其特征在于， 所述的海陆空潜四栖倾转三旋翼无人机包括机身 (1) 、 主翼 (2)、 2个副翼 (3)、 2个垂直尾翼 (4)、 2个前倾转轴 (5)、 2个前倾 转座 (6)、 2个前电机旋翼 (7)、 后倾转座 (8)、 后电机旋翼 (9)、 后倾转 轴 (10)、 螺旋桨 (11)、 2个尾舵 (12)、 右后方气囊 (13)、 气囊控制器 (14) 、 左后方气囊 (15)、 气瓶 (16)、 前方气囊 (17)与控制板； 所述的主翼 (2)是以中轴线对称的翼状结构， 与机身 (1)一体结构； 所 述的 2个副翼 (3)为长方形结构， 分别固定连接在主翼 (2)的两侧机翼尾 部， 可绕其固定端向机身 (1)方向展幵； 2个垂直尾翼 (4)分别以主翼 (2) 的中轴线为轴， 对称垂直固定在主翼 (2)尾端上表面， 位于两个副翼 (3 )间； 所述的前电机旋翼 (7)固定在前倾转座 (6)上， 前倾转座 (6)通过前倾转 轴 (5)与机身 (1)的前部相连， 左右两部分以机身 (1)的中轴线对称； 前 电机旋翼 (7)的独立倾转角度范围为 0°~100°； 所述的后电机旋翼 (9)固定在后倾转座 (8)上， 后倾转座 (8)通过后倾转 轴 (10)与机身 (1)的尾部连接， 后电机旋翼 (9)倾转角度范围为 -30°~30° ； 两前电机旋翼 (7)和后电机旋翼 (9)转速独立控制， 实现垂直起降和 固定翼模式； 所述的螺旋桨 (11)和 2个尾舵 (12)穿过机身 (1)尾部下方， 连接在机身 (1 )内部的控制板上， 2个尾舵 (12)以机身 (1)对称轴对称， 螺旋桨 (11)位 于 2个尾舵 (12)的对称轴上； 控制板控制 2个尾舵 (12)转动进而改变航 行方向， 通过控制螺旋桨 (11)转速进而改变在水中航行速度； 所述的右后方气囊 (13)、 气囊控制器 (14)、 左后方气囊 (15)、 气瓶 (16) 和前方气囊 (17)均固定在机身 (1)和主翼 (2)下表面， 其中， 右后方气囊 (13)、 左后方气囊 (15)和前方气囊 (17)三者呈中心对称布局； 右后方气 囊 (13)、 左后方气囊 (15)和前方气囊 (17)分别与气瓶 (16)相连， 并通过 气囊控制器 (14)控制； 海陆空潜四栖倾转三旋翼无人机共有四种工作模式：
(1)垂直起降模式：
在垂直起降模式下， 当无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)垂 直向上吋， 通过同吋控制 2个前电机旋翼 (7)与后电机旋翼 (9)的推力大 小和方向， 实现无人机姿态控制；
俯仰控制： 当无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)垂直向上吋 ， 通过调节前方旋翼 (7)和后方旋翼 (9)的拉力差， 实现俯仰角度的变 化； 同吋减小前方旋翼 (7)转速或增后方旋翼 (9)转速， 使无人机产生 俯仰；
滚转控制： 当无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)垂直向上吋 ， 通过调节无人机前方两旋翼 (7)的拉力差， 实现对滚转角的控制； 增大前方右侧旋翼 (7)转速， 减小前方左侧旋翼 (7)转速， 使无人机产 生滚转；
偏航控制： 当无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)垂直向上吋 ， 通过调节后倾转座 (8)的倾转角度， 实现对偏航角度的控制， 将后 倾转座 (8)倾转一定角度， 使无人机产生偏航；
(2)固定翼飞行模式：
随着无人机水平速度的增大， 2个前电机旋翼 (7)倾转到水平位置吋， 后电机旋翼 (9)停止工作吋， 无人机完全由副翼 (3)和垂直尾翼 (4)进行 控制； 通过控制 2个前转旋翼 (7)的推力大小以及副翼 (3)舵面角度实现 固定翼飞行；
(3)水面航行模式：
无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)停止工作， 气瓶 (16)通过 气囊控制器 (14)向右后方气囊 (13)、 左后方气囊 (15)、 前方气囊 (17)充 满空气使无人机漂浮于水面， 尾舵 (12)左右转动控制无人机航向， 螺 旋桨 (11)控制无人机前进后退速度；
(4)水下航行模式：
无人机的 2个前电机旋翼 (7)与后电机旋翼 (9)停止工作， 气瓶 (16)通过 气囊控制器 (14)向右后方气囊 (13)、 左后方气囊 (15)、 前方气囊 (17)充 入空气保证无人机潜深；
俯仰控制： 通过气囊控制器 (14)控制气囊右后方气囊 (13)和左后方气 囊 (15)与前方气囊 (17)储气量之差控制无人机水下俯仰角度； 增大右 后方气囊 (13)储气量和左后方气囊 (15)储气量， 减小前方气囊 (17)储气 量， 使无人机产生俯仰；
滚转控制： 通过气囊控制器 (14)控制右后方气囊 (13)与左后方气囊 (15) 储气量之差从而控制无人机水下滚转角度； 增大右后方气囊 (13)储气 量， 减小左后方气囊 (15)储气量， 使无人机产生滚转； 尾舵 (12)左右 转动控制无人机航向， 螺旋桨 (11)控制无人机前进后退速度。
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