WO2021053786A1 - 飛行体 - Google Patents

飛行体 Download PDF

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Publication number
WO2021053786A1
WO2021053786A1 PCT/JP2019/036728 JP2019036728W WO2021053786A1 WO 2021053786 A1 WO2021053786 A1 WO 2021053786A1 JP 2019036728 W JP2019036728 W JP 2019036728W WO 2021053786 A1 WO2021053786 A1 WO 2021053786A1
Authority
WO
WIPO (PCT)
Prior art keywords
unit
wing
flight
attack
airframe
Prior art date
Application number
PCT/JP2019/036728
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
鈴木陽一
Original Assignee
株式会社エアロネクスト
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 株式会社エアロネクスト filed Critical 株式会社エアロネクスト
Priority to JP2019552634A priority Critical patent/JPWO2021053786A1/ja
Priority to PCT/JP2019/036728 priority patent/WO2021053786A1/ja
Priority to CN201980100835.5A priority patent/CN114502464A/zh
Publication of WO2021053786A1 publication Critical patent/WO2021053786A1/ja

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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
    • B64C27/08—Helicopters with two or more 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
    • B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded

Definitions

  • the present invention relates to an air vehicle, and more particularly to a thrust portion and a wing portion that are displaceably connected to each other.
  • tilt rotor system Two types of aircraft, the so-called tilt rotor system and the tilt wing system, are known as aircraft equipped with a rotor (rotor wing) and a main wing.
  • Patent Document 1 discloses an aircraft in which the main wing is fixed to the main body and the entire rotor including the motor is displaceable in the vertical direction and the flight direction (tilt rotor method).
  • Patent Document 2 discloses an aircraft in which the main wing and the main body are displaceable in the vertical direction and the flight direction, and the entire motor and rotor are fixed to the main wing (tilt wing). method).
  • the flight efficiency of the main wing is poor because the main wing enters a wide range of the wake of the propeller when ascending.
  • the present invention has been made in view of the above circumstances, and provides an air vehicle that enables an efficient and safe transition from hovering to level flight.
  • a flight unit having a wing portion and a rotary wing provided on the wing portion, Equipped with the airframe
  • the wing It is configured to be able to maintain a negative angle of attack, at least in the direction of travel.
  • An air vehicle is obtained.
  • the illustrated flying object is the state at the time of landing. It is the figure which looked at the flying body from the top. It is a figure explaining the flying object which concerns on embodiment of this invention.
  • the illustrated flying object is in the ascending state. It is a figure explaining the flying object which concerns on embodiment of this invention.
  • the illustrated flying object is a flight state in the direction of travel. It is a graph which showed the lift and resistance characteristics of an airfoil. It is a functional block diagram of the flying object of this invention.
  • the invention according to the present embodiment includes the following configurations.
  • [Item 1] A flight unit having a wing portion and a rotary wing provided on the wing portion, Equipped with the airframe The wing It is configured to be able to maintain a negative angle of attack, at least in the direction of travel. Aircraft.
  • [Item 2] The flying object according to item 1.
  • the wing It is configured to be able to maintain a negative angle of attack with respect to the rotation center axis of the rotor at least during hovering.
  • Aircraft. [Item 3] The flying object according to item 1 or item 2.
  • a boarding section that can be displaced independently of the fuselage section is provided.
  • [Item 4] The flying object according to item 3.
  • the fuselage extends horizontally and perpendicularly to the flight direction.
  • the boarding portion is provided substantially in the center of the aircraft portion in a side view. Aircraft.
  • the airframe 1 roughly includes a flight unit 10, an airframe unit 20, and a boarding unit 30.
  • the flight unit 10 includes a wing unit 100, a motor 102, and a propeller (rotor blade) 104.
  • the wing portion 100 is configured to be able to maintain a negative angle of attack with respect to the rotation center axis of the propeller 104 at least during hovering, and is fixed to the airframe portion 20.
  • various known methods can be adopted.
  • the airframe unit 20 (and the flight unit 10 fixed to the airframe unit 20) and the boarding unit 30 are configured to be displaceable independently.
  • the flying object 1 has an H-shape when viewed from above. That is, the flight body 1 includes two flight sections 10 provided in the front-rear direction and a body section 20 (and a boarding section 30) connecting them.
  • the flight unit 10 includes a wing unit 100, a motor 102, and a propeller 104.
  • the correspondence between the X-axis, the Y-axis and the Z-axis in the figure and the direction corresponds as follows.
  • X-axis 1st horizontal direction (+ X direction: left, -X direction: right)
  • Y-axis 2nd horizontal direction (+ Y direction: front, -Y direction: rear)
  • Z axis vertical direction (+ Z direction: up, -Z direction: down)
  • the wing portion 100 extends in the X direction and is a portion where lift is generated by the motor 102. In the initial state (the state shown in FIG. 1), the front edge faces upward and the trailing edge faces downward.
  • the wing portion 100 is composed of a front wing portion 100 and a rear wing portion 100.
  • the thrust generating unit 10 generates a propulsive force forward from the thrust generating unit 10 by rotating the propeller (thrust generating unit) 104.
  • the motor 102 can be replaced by an engine or the like.
  • the propeller 104 is driveable by the motor 102 and rotates clockwise and / or counterclockwise around the axis of rotation of the motor 102 (eg, the major axis of the motor).
  • the motor 102 can rotate the propellers 104 in the same direction, or can rotate the propellers 104 independently. Some of the propellers 104 rotate in one direction and the other propellers 104 rotate in the other direction.
  • the blades constituting the propeller 104 can all rotate at the same rotation speed, and can also rotate at different rotation speeds. The number of rotations can be automatically or manually determined based on the dimensions (for example, size, weight) and control state (speed, moving direction, etc.) of the moving body.
  • the propeller 104 rotates in response to the output from the motor 102.
  • the rotation of the propeller 104 generates a propulsive force for taking off the flying object 1 from the ground G, moving it horizontally, and landing it at the destination.
  • the propeller 104 can rotate to the right, stop, and rotate to the left.
  • the blade has an elongated shape. Any number of blades (rotors) (eg, 1, 2, 3, 4, or more blades) may be used. Further, the shape of the blade can be any shape such as a flat shape, a bent shape, a twisted shape, a tapered shape, or a combination thereof.
  • the shape of the blade can be changed (for example, expansion / contraction, folding, folding, etc.).
  • the blades may be symmetrical (having the same upper and lower surfaces) or asymmetric (having different shaped upper and lower surfaces).
  • the blade can be formed into an air wheel, wing, or geometric shape suitable for generating dynamic aerodynamic force (eg, lift, thrust) as the blade moves through the air.
  • the geometry of the blade can be appropriately selected to optimize the dynamic air properties of the blade, such as increasing lift and thrust and reducing drag.
  • the airframe portion 20 extends rearward from the center of the front wing portion 100 and is connected to the center of the rear wing portion 100.
  • the machine body portion 20 can be formed of a material appropriately selected from carbon, stainless steel, aluminum, magnesium and the like, alloys thereof, combinations and the like.
  • the body unit 20 has a substantially annular accommodating unit that includes the boarding unit 30.
  • the accommodating portion is provided in the vicinity of substantially the center of the airframe portion 20.
  • the boarding portion 30 has a substantially annular shape corresponding to the shape of the accommodating portion, and is located inside the accommodating portion.
  • the boarding section 30 and the accommodating section are configured to be independently displaceable in the circumferential direction of a substantially annular shape.
  • the propeller 104 is provided in front of the front edge of the wing portion 100.
  • the front edge of the wing portion 100 is directed upward, and the motor unit is oriented to generate at least an upward propulsive force.
  • the leg portion 202 and the rear side wing portion (and the motor 102) function as a portion that supports the flying object 1 at the time of landing.
  • the wing portion 100 has a negative angle of attack with respect to the rotation center axis of the propeller 104.
  • both the front propeller 104 and the rear propeller 104 have a negative angle of attack with respect to the rotation center axis of the propeller 104.
  • the wing portion 100 has a negative angle of attack with respect to the rotation center axis of the propeller 104 even during horizontal movement.
  • both the front propeller 104 and the rear propeller 104 have a negative angle of attack with respect to the rotation center axis of the propeller 104.
  • both the front propeller 104 and the rear propeller 104 have a negative angle of attack with respect to the rotation center axis of the propeller 104.
  • FIG. 5 is a graph showing the lift / resistance characteristics of the airfoil.
  • the horizontal axis of FIG. 5 indicates the angle of attack, and the vertical axis indicates the resistance coefficient and lift coefficient.
  • the negative angle of attack has a smaller drag coefficient than the positive angle of attack.
  • the airframe is manufactured with an angle of attack of -6 degrees, the lift of the main wing equivalent to that of an airframe with a zero angle of attack can be obtained.
  • the wing portion 100 has a negative angle of attack with respect to the rotation center axis of the propeller 104, it is possible to suppress an excessive angle of attack of the wing portion 100 while suppressing the drag force of the wake of the propeller.
  • the flying object of the present embodiment it is possible to safely shift from the hovering time to the horizontal flight transition.
  • FIG. 6 is a functional block diagram of the flying object of the present invention.
  • the above-mentioned flying object may have, for example, a configuration as shown in FIG.
  • the flight controller can have one or more processors such as a programmable processor (eg, central processing unit (CPU)).
  • processors such as a programmable processor (eg, central processing unit (CPU)).
  • the flight controller has a memory (not shown) and can access the memory.
  • the memory stores the logic, code, and / or program instructions that the flight controller can execute to perform one or more steps.
  • the memory may include, for example, a separable medium such as an SD card or random access memory (RAM) or an external storage device.
  • a separable medium such as an SD card or random access memory (RAM) or an external storage device.
  • the data acquired from the cameras and sensors may be directly transmitted and stored in the memory. For example, still image / moving image data taken by a camera or the like is recorded in an internal memory or an external memory.
  • the flight controller includes a control module configured to control the state of the aircraft.
  • the control module adjusts the spatial placement, velocity, and / or acceleration of an air vehicle with six degrees of freedom (translational motion x, y and z, and rotational motion ⁇ x , ⁇ y and ⁇ z).
  • the control module can control one or more of the states of the mounting unit and the sensors.
  • the flight controller is capable of communicating with a transmitter / receiver configured to transmit and / or receive data from one or more external devices (eg, terminals, display devices, or other remote controls).
  • the transmitter / receiver can use any suitable communication means such as wired communication or wireless communication.
  • the transmitter / receiver uses one or more of local area network (LAN), wide area network (WAN), infrared, wireless, WiFi, point-to-point (P2P) network, telecommunications network, cloud communication, and the like. be able to.
  • LAN local area network
  • WAN wide area network
  • infrared wireless
  • WiFi point-to-point
  • P2P point-to-point
  • telecommunications network cloud communication, and the like. be able to.
  • the transmitter / receiver can transmit and / or receive one or more of data acquired by sensors, processing results generated by a flight controller, predetermined control data, user commands from a terminal or a remote controller, and the like. ..
  • the sensors according to this embodiment may include an inertial sensor (accelerometer, gyro sensor), GPS sensor, proximity sensor (eg, rider), or vision / image sensor (eg, camera).
  • an inertial sensor accelerelerometer, gyro sensor
  • GPS sensor GPS sensor
  • proximity sensor eg, rider
  • vision / image sensor eg, camera
  • the air vehicle of the present invention can be expected to be used as an air vehicle dedicated to home delivery services over medium and long distances, and as an industrial air vehicle in wide area monitoring operations and reconnaissance / rescue operations in mountainous areas. Further, the air vehicle of the present invention can be used in airplane-related industries such as multicopter drones, and further, the air vehicle of the present invention is suitably used as an air vehicle equipped with a camera or the like and capable of performing aerial photography missions. In addition, it can be used in various industries such as security field, agriculture, and infrastructure monitoring.
  • the flying object of the present invention may be applied to an unmanned flying object.
  • the blade portion 100 is configured to be able to maintain a negative angle of attack with respect to the rotation center axis of the rotary blade at least during hovering.
  • the wing portion 100 may be configured so as to be able to maintain at least a negative angle of attack with respect to the traveling direction.
  • Air vehicle 10 Flight unit 100 Wing unit 102 Motor 104 Propeller (rotor blade) 20 Aircraft section 30 Boarding section

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
PCT/JP2019/036728 2019-09-19 2019-09-19 飛行体 WO2021053786A1 (ja)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP2019552634A JPWO2021053786A1 (zh) 2019-09-19 2019-09-19
PCT/JP2019/036728 WO2021053786A1 (ja) 2019-09-19 2019-09-19 飛行体
CN201980100835.5A CN114502464A (zh) 2019-09-19 2019-09-19 飞行体

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2019/036728 WO2021053786A1 (ja) 2019-09-19 2019-09-19 飛行体

Publications (1)

Publication Number Publication Date
WO2021053786A1 true WO2021053786A1 (ja) 2021-03-25

Family

ID=74884439

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2019/036728 WO2021053786A1 (ja) 2019-09-19 2019-09-19 飛行体

Country Status (3)

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JP (1) JPWO2021053786A1 (zh)
CN (1) CN114502464A (zh)
WO (1) WO2021053786A1 (zh)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4633628B1 (zh) * 1966-12-30 1971-10-01
US20180257761A1 (en) * 2016-07-01 2018-09-13 Bell Helicopter Textron Inc. Aircraft having Single-Axis Gimbal Mounted Propulsion Systems
WO2019145704A1 (en) * 2018-01-23 2019-08-01 Kamran Iqbal Airborne urban mobility vehicle

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2318273A4 (en) * 2008-09-02 2017-09-06 Urban Aeronautics Ltd. Vtol vehicle with coaxially tilted or tiltable rotors
JP6108077B2 (ja) * 2013-01-29 2017-04-05 株式会社Ihi 垂直離着陸機
GB2540169B (en) * 2015-07-08 2018-08-08 Ge Aviation Systems Llc Aircraft wing shaped to counter aerodynamic effects of propeller wake
US10513332B2 (en) * 2015-10-05 2019-12-24 Sikorsky Aircraft Corporation Tiltwing aircraft
US10513334B2 (en) * 2017-06-12 2019-12-24 Textron Innovations Inc. X-tiltwing aircraft
US11117657B2 (en) * 2018-01-19 2021-09-14 Aerhart, LLC Aeronautical apparatus

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4633628B1 (zh) * 1966-12-30 1971-10-01
US20180257761A1 (en) * 2016-07-01 2018-09-13 Bell Helicopter Textron Inc. Aircraft having Single-Axis Gimbal Mounted Propulsion Systems
WO2019145704A1 (en) * 2018-01-23 2019-08-01 Kamran Iqbal Airborne urban mobility vehicle

Also Published As

Publication number Publication date
JPWO2021053786A1 (zh) 2021-03-25
CN114502464A (zh) 2022-05-13

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