WO2017221387A1 - Aéronef sans pilote et son procédé de stockage - Google Patents

Aéronef sans pilote et son procédé de stockage Download PDF

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Publication number
WO2017221387A1
WO2017221387A1 PCT/JP2016/068733 JP2016068733W WO2017221387A1 WO 2017221387 A1 WO2017221387 A1 WO 2017221387A1 JP 2016068733 W JP2016068733 W JP 2016068733W WO 2017221387 A1 WO2017221387 A1 WO 2017221387A1
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WO
WIPO (PCT)
Prior art keywords
rotor
blade
counterweight
rotors
aerial vehicle
Prior art date
Application number
PCT/JP2016/068733
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English (en)
Japanese (ja)
Inventor
紀代一 菅木
Original Assignee
株式会社プロドローン
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 株式会社プロドローン filed Critical 株式会社プロドローン
Priority to JP2018523241A priority Critical patent/JP6398145B2/ja
Priority to PCT/JP2016/068733 priority patent/WO2017221387A1/fr
Publication of WO2017221387A1 publication Critical patent/WO2017221387A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • 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
    • B64U30/21—Rotary wings

Definitions

  • the present invention relates to an unmanned aerial vehicle and a storage method thereof.
  • Such a multicopter generally uses a rotor in which a plurality of blades are arranged at equal intervals in the circumferential direction.
  • a rotor having a plurality of blades has a problem in that the output efficiency of the rotor is likely to decrease because each blade passes through turbulent air flow generated by the blade in the front in the rotation direction.
  • the multicopter has a characteristic that the rotor tends to vibrate due to the mechanism of controlling the attitude and flight operation of the aircraft while continuously changing the rotational speed of each rotor.
  • the rotating surface of the blade may tilt and the rotor may precess. Such vibrations cause disturbance in the flight operation of the aircraft and noise.
  • such a multi-copter rotor is generally arranged at the tip of an arm that extends radially from the center of the fuselage. Therefore, when the rotor has a plurality of blades, the whole blade or a part thereof always protrudes outward from the arm regardless of the angular position of the blade. The protruding blades hinder the transportation of the airframe, and reduce the space efficiency of the airframe storage location.
  • the problem to be solved by the present invention is to provide an unmanned aerial vehicle that suppresses flight disturbance and noise caused by rotor vibration and has high space efficiency during storage.
  • an unmanned aerial vehicle is an unmanned aerial vehicle that includes a plurality of rotors and controls the attitude and flight operation of the fuselage by adjusting the rotation speed of each of the rotors.
  • At least one of the above is a single rotor having a single blade, a blade composed of only one blade, and a counterweight of the blade.
  • the first rotor of the present invention is composed of only one blade, unlike a general rotor having a plurality of blades, the output by passing through the turbulence generated by other blades. There is no need to consider a decrease in efficiency. Furthermore, the first rotor has a feature that acceleration / deceleration is quicker than the general rotor. Therefore, the stability and operability of the fuselage can be improved by adopting this first rotor in an unmanned aerial vehicle that controls the attitude and flight motion of the fuselage while continuously changing the rotational speed of each rotor. .
  • the single rotor of the present invention has a counterweight which is a dedicated weight member for suppressing vibration accompanying the rotation of the blade.
  • a counterweight which is a dedicated weight member for suppressing vibration accompanying the rotation of the blade.
  • the first rotor has a feature that it is less likely to cause precession than a general rotor having a plurality of blades, and a synergistic effect on the vibration suppression of the rotor is expected.
  • the unmanned aerial vehicle according to the present invention includes the first rotor so that it is possible to suppress flight disturbance and noise caused by the vibration of the rotor.
  • the rotors of the unmanned aerial vehicle of the present invention are all preferably one-gear rotors. However, even when only a part of the first-gear rotors are employed, the same effect is recognized although limited.
  • the single rotor of the present invention is composed of a single blade, the position of the blade of each single rotor is positioned along the extending direction of the arm on which the single rotor is supported. By arranging it toward the center of the space, it is possible to increase the space efficiency during storage of the aircraft.
  • the position of the center of gravity of the counterweight is preferably higher than the position of the base end of the blade when the first rotor is stationary.
  • the blades are corned according to the centrifugal force and lift force acting on the blades.
  • the center of gravity of the blade during rotation may move upward as compared to when the blade is stationary due to the blade load on the blade.
  • the center of gravity of the counterweight is positioned above the position of the blade when stationary, thereby improving the dynamic balance during unmanned aircraft flight. it can.
  • the optimum position of the counterweight above the blade can be adjusted by rotating the first rotor at the actual number of revolutions, or by using a dynamic balancer or the like.
  • the first rotor further has a spinner that covers a base end portion of the blade, and the counterweight is accommodated in the spinner.
  • the counterweight may be fixed to the inner peripheral surface of the spinner.
  • the air resistance of the counter weight can be suppressed, and since the counter weight does not protrude outside the spinner, the space efficiency during storage of the aircraft can be further increased. .
  • the position of the center of gravity of the counterweight can be finely adjusted after the first rotor is mounted on the unmanned aircraft.
  • each of the rotors may have an outer rotor type motor as a driving source, and the blade and the counterweight may be integrated with a motor case of the outer rotor type motor.
  • the blade and counterweight are integrated into the motor case of the outer rotor type motor, the number of rotor parts and assembly errors can be reduced. Thereby, it can suppress that the balance of a braid
  • the storage method for an unmanned aerial vehicle including a plurality of rotors is such that each rotor has a single blade and a counterweight of the blade.
  • Each of the rotors is supported by a plurality of arms extending radially from the center of the unmanned aircraft body, and the position of the blade of each rotor is determined by the extension of the arm on which the rotor is supported. It includes a step of arranging the airframe toward the center side of the airframe along the outgoing direction.
  • the blades of each rotor are composed of a single piece, the position of the blades of each rotor is directed toward the center of the fuselage along the extending direction of the arm on which the rotor is supported.
  • the space efficiency during storage of the aircraft can be improved.
  • the unmanned aerial vehicle and the unmanned aircraft storage method according to the present invention it is possible to suppress the flight disturbance and noise caused by the vibration of the rotor, and to improve the space efficiency during the storage. .
  • This embodiment is an example of a multicopter 10 (quad copter) that is an unmanned aerial vehicle in which four rotors R are mounted at equal intervals in the circumferential direction of the airframe.
  • the “rotor” in the present invention means a rotor having a vertical rotating shaft and a horizontal rotating surface, and does not include a rotor having a horizontal rotating shaft such as an airplane propeller.
  • “upper” for the rotor R means the intake side of the rotor R, that is, the rising direction of the multicopter 10
  • “lower” means the exhaust side of the rotor R, that is, the lowering direction of the multicopter 10. I mean.
  • FIG. 1 is a block diagram showing a functional configuration of the multicopter 10.
  • the aircraft of the multicopter 10 includes a flight controller 20, four rotors R, an ESC 43 (Electric Speed Controller) that controls rotation of the rotors R, a wireless transceiver 33 that performs wireless communication with an operator's control terminal 60, and A battery 51 as a power supply source is mounted.
  • ESC 43 Electronic Speed Controller
  • Each rotor R has a motor 41 which is an outer rotor type motor, a blade 42b connected to the output shaft thereof, and a counterweight 42w of the blade 42b.
  • the ESC 43 is connected to the motor 41 of the rotor R and is a device that rotates the motor 41 at a speed instructed by the flight controller FC.
  • the multicopter 11 in this embodiment is a quadcopter on which four rotors R are mounted.
  • the number of rotors R is not limited to four, and required flight stability, allowable cost, etc. It can be appropriately changed depending on the situation.
  • the flight controller FC includes a control device 20 that is a microcontroller.
  • the control device 20 includes a CPU 21 that is a central processing unit, a memory 22 that is a storage device such as a ROM and a RAM, and a PWM controller 23 that controls the rotation speed and rotation speed of each motor 41 via the ESC 43.
  • the flight controller FC further includes a flight control sensor group 31 and a GPS receiver 32 (hereinafter collectively referred to as “sensors”), which are connected to the control device 20.
  • the flight control sensor group 31 of the multicopter 10 in this embodiment includes an acceleration sensor, an angular velocity sensor, an atmospheric pressure sensor (altitude sensor), a geomagnetic sensor (orientation sensor), and the like.
  • the control device 20 can acquire position information of the own aircraft including the latitude and longitude of the flight, the flight altitude, and the azimuth angle of the nose, in addition to the tilt and rotation of the aircraft, using these sensors and the like.
  • the memory 22 of the control device 20 stores a flight control program FCP, which is a program in which a flight control algorithm for controlling the attitude and basic flight operation of the multicopter 10 during flight is installed.
  • the flight control program FCP adjusts the number of rotations of each rotor R based on the current position acquired from a sensor or the like according to an instruction from the operator (control terminal 60), and corrects the attitude and position disturbance of the fuselage.
  • the operation of the multicopter 10 can be performed by the operator from the control terminal 60.
  • parameters such as the flight path, speed, and altitude are registered in advance in the flight control program FCP, and autonomously reach the destination. It is also possible to fly (hereinafter referred to as “autopilot”).
  • the multicopter 10 in this embodiment has an advanced flight control function.
  • the unmanned aerial vehicle according to the present invention may be any aircraft that includes a plurality of rotors R and controls the attitude and flight operation of the aircraft by adjusting the rotational speed of each of the rotors R. It may be an airframe in which sensors are omitted, or an airframe that does not have an autopilot function and can fly only by manual operation.
  • FIG. 2 is a partial perspective view showing the configuration of the rotor R of the multicopter 10.
  • the multicopter 10 includes four rotors R, and all the rotors R have the same configuration as that in FIG.
  • the rotor R includes a motor 41 that is an outer rotor type motor, a single blade 42 b that is connected to the output shaft of the motor 41, and a dome-shaped spinner 46 that covers a connecting portion between the motor 41 and the blade 42 b.
  • a counter-rotor composed of a counterweight 42w fixed to the inner peripheral surface of the spinner 46.
  • the counterweight 42w is a dedicated weight member for suppressing vibration accompanying the rotation of the blade 42b.
  • the position of the center of gravity of the counterweight 42w of the present embodiment is disposed slightly above the position of the center of gravity when the blade 42b is stationary.
  • the blade 42b is corned by the centrifugal force and the lift force acting on the blade 42b. Since the center of gravity of the counterweight 42w is disposed above the position of the center of gravity when the blade 42b is stationary, the dynamic balance in this state can be improved.
  • the specific position, shape, and weight of the counterweight 42w are optimized in advance by rotating the rotor R at an actual rotational speed or using a dynamic balancer or the like.
  • the rotor R of the present embodiment determines the position of the center of gravity of the counterweight 42w based on the actual shape, hardness, rotational speed, etc. of the blade 42b in consideration of dynamic balance. etc. If not strictly, as the rotor R 2 in FIG. 5 to be described later, it is also conceivable to match the vertical center of gravity of the blade 42b and the counterweight 42w stationary.
  • the counterweight 42w of this embodiment uses lead as its material, and when adjusting the balance between the counterweight 42w and the blade 42b, the shape and weight of the counterweight 42w can be easily finely adjusted. It is possible.
  • the material of the counterweight of the present invention is not particularly limited, and materials other than lead can be used. However, in order to suppress the size of the counterweight 42w and prevent the counterweight 42w from protruding long in the radial direction of the rotor R, It is preferable to use a material having a large specific gravity.
  • the counterweight 42 w of the present embodiment is a separate member from the blade 42 b and is fixed to the inner peripheral surface of the spinner 46.
  • Counterweight 42w for example, as the rotor R 2 in FIG. 5 to be described later, may be formed integrally continuous from the blade 42b, furthermore, a hub integral not shown connecting the motor 41 and the blade 42b It may be made.
  • the counterweight 42w of the present embodiment is stuck to the inner peripheral surface of the spinner 46 and fixed at one place.
  • the positional relationship between the blade 42b and the counterweight 42w is preferably adjusted before the rotor R is mounted on the multicopter 10, but the balance adjusted by the rotor R alone and the multicopter 10 are actually mounted. It is also conceivable that an error occurs in the balance when flying.
  • the relative position and arrangement angle of the counterweight 42w with respect to the blade 42b can be finely adjusted later by the fixing position of the screw or the like for fixing the counterweight 42w and the degree of tightening or loosening thereof. By doing so, it is possible to flexibly eliminate the error between the theoretical balance and the actual balance.
  • the rotor R is configured by one blade 42b, the reduction in output efficiency due to the blade 42b passing through the turbulence generated by the other blade is considered. There is no need. Furthermore, the first rotor has a feature that acceleration / deceleration is quicker than a general rotor having a plurality of blades. By adopting this rotor R in the multicopter 10 that controls the attitude and flight motion of the aircraft while continuously changing the rotational speed of each rotor, the stability and operation of the aircraft during the flight of the multicopter 10 are achieved. Sex has been improved.
  • the counterweight 42w is accommodated inside the spinner 46.
  • the counterweight 42w is accommodated inside the spinner 46.
  • the counterweight 42w is accommodated inside the spinner 46, the reduction in output efficiency due to such air resistance is prevented. This feature also contributes to improving the stability and operability of the aircraft during the flight of the multicopter 10.
  • the counterweight 42 w of the present embodiment is fixed to the inner peripheral surface of the spinner 46.
  • the vibration generated by the blade 42b can be canceled by the counterweight 42w that is a weight member optimized for suppressing the vibration of the blade 42b.
  • the first rotor has a feature that it is difficult to cause precession, and a synergistic effect on the suppression of vibration of the rotor R is expected. Thereby, the problem of the multicopter that the vibration is likely to occur is improved, and the flight disturbance and noise of the multicopter 10 due to the vibration of the rotor R are suppressed.
  • [Modification of rotor] 4 and 5 are views showing rotors R 1 and R 2 which are modifications of the rotor R.
  • FIG. 1 is a diagram showing rotors R 1 and R 2 which are modifications of the rotor R.
  • Rotor R 1 in FIG. 4 the motor case 41c of the motor 41 as a driving source, a rotor blade 42b and counterweight 42w are integrated.
  • 4 (a) is a side view of the rotor R 1
  • FIG. 4 (b) is a plan view showing a cross section taken along A-A position in FIGS. 4 (a).
  • the motor case 41c of the motor 41 is an outer rotor type motor, by which the blade 42b and the counterweight 42w are integrated, the number of parts and assembling errors of the rotor R 1 is reduced. This prevents the balance between the blade 42b and the counterweight 42w from being lost due to accumulated errors.
  • the rotor R 1 of the present modification a counterweight 42w by forming thicker than a portion of the thickness of the other portions in the circumferential direction of the motor case 42c. Therefore, a portion of the counterweight 42w, the amount of leakage flux to the outside of the motor case 42c and is suppressed, the output efficiency of the rotor R 1 is enhanced.
  • the blade 42b and the counterweight 42w are integrally formed with the motor case 42c.
  • the blade 42b and the counterweight 42w that are separate from the motor case 42c may be coupled to the motor case 42c. Good.
  • the rotor R 2 shown in FIG. 5 is an example of a simpler structure of the rotor R.
  • FIG. 5A is a side view of the rotor R 2
  • FIG. 5B is a plan view of the rotor R 2 .
  • Rotor R 2 of this modification is integrated counterweight 42w is the proximal end portion of the blade 42b, during a stationary state of the blade 42b, the center of gravity position are matched in the vertical direction of the blade 42b and the counterweight 42w .
  • Rotor R 2 is not provided with a spinner, counterweight 42w is exposed to the outside.
  • the disadvantages of the rotor R 2 when compared with the rotor R are as described above.
  • FIG. 3 is a diagram illustrating a storage method of the multicopter 10 at the storage location.
  • the multicopter 10 of the present embodiment four arms 11 extend radially from the center of the airframe, and the rotor R is disposed at the tip thereof.
  • the whole blade or a part thereof always protrudes outward from the arm regardless of the angular position of the blade.
  • the protruding blade hinders the transport of the aircraft, and, for example, as shown in FIG. 3 (a), it is necessary to secure a large occupied space D of the aircraft. It causes a decrease.
  • the rotor R is configured by a single blade 42b, the position of the blade 42b of each rotor R is set in the extending direction of the arm 11 on which the rotor R is supported.
  • the occupied space D of the multicopter 10 in the storage location can be made compact, and the space efficiency of the storage location can be improved (see FIG. 3B).
  • the counterweight 42w since the counterweight 42w is accommodated in the spinner 46, the counterweight 42w does not protrude from the rotor R in the radial direction, and the space saving effect is maximized. Yes.
  • the present invention is not limited to the above-described embodiments, and various modifications can be made without departing from the scope of the present invention.
  • the rotor R that is the first rotor of the present invention is used for all of the rotors, but even when the rotor R is used only for some of the rotors, there is a limitation.
  • the vibration suppression effect mentioned above and a space saving effect can be acquired.
  • the drive source of the rotor R is not limited to a motor.
  • an engine may be used for a large body.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un aéronef sans pilote ayant un rendement spatial élevé en stockage, de telle sorte que les perturbations et le bruit en vol provoqués par les vibrations des rotors soient minimisés. Pour ce faire, l'aéronef sans pilote comprend une pluralité de rotors qui, par réglage de leurs vitesses de rotation, commandent l'assiette du corps de l'aéronef et les opérations de vol. L'objet de l'invention est caractérisé en ce qu'au moins l'un parmi la pluralité de rotors est un rotor à pale unique qui possède une seule pale et un contrepoids de la pale. L'invention concerne en outre un procédé de stockage pour l'aéronef sans pilote qui est caractérisé en ce qu'il comprend une étape dans laquelle la position des pales de chaque rotor est arrangée de manière à ce qu'elles soient dirigées vers le centre du corps de l'aéronef le long de la direction d'extension des bras qui supportent les rotors.
PCT/JP2016/068733 2016-06-23 2016-06-23 Aéronef sans pilote et son procédé de stockage WO2017221387A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2018523241A JP6398145B2 (ja) 2016-06-23 2016-06-23 無人航空機およびその保管方法
PCT/JP2016/068733 WO2017221387A1 (fr) 2016-06-23 2016-06-23 Aéronef sans pilote et son procédé de stockage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2016/068733 WO2017221387A1 (fr) 2016-06-23 2016-06-23 Aéronef sans pilote et son procédé de stockage

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WO2017221387A1 true WO2017221387A1 (fr) 2017-12-28

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PCT/JP2016/068733 WO2017221387A1 (fr) 2016-06-23 2016-06-23 Aéronef sans pilote et son procédé de stockage

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7137885B1 (ja) 2022-03-30 2022-09-15 株式会社石川エナジーリサーチ 飛行装置の製造方法

Families Citing this family (1)

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Publication number Priority date Publication date Assignee Title
KR102263117B1 (ko) * 2020-12-23 2021-06-10 주식회사 클루 무인항공기용 싱글 프로펠러 조립체

Citations (3)

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Publication number Priority date Publication date Assignee Title
JP2011006041A (ja) * 2009-06-23 2011-01-13 Sakayuki Morita 回転翼航空機用の電動機内臓ハブ、並びにそれを用いた回転翼航空機、並びにその回転翼航空機用アンチ・トルク装置
JP2012071823A (ja) * 2010-08-06 2012-04-12 Ge Aviation Systems Ltd 航空機のプロペラ
US9334049B1 (en) * 2014-12-03 2016-05-10 Amazon Technologies, Inc. Single blade rotor system for use in a vertical takeoff and landing (VTOL) aircraft

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
JP2011006041A (ja) * 2009-06-23 2011-01-13 Sakayuki Morita 回転翼航空機用の電動機内臓ハブ、並びにそれを用いた回転翼航空機、並びにその回転翼航空機用アンチ・トルク装置
JP2012071823A (ja) * 2010-08-06 2012-04-12 Ge Aviation Systems Ltd 航空機のプロペラ
US9334049B1 (en) * 2014-12-03 2016-05-10 Amazon Technologies, Inc. Single blade rotor system for use in a vertical takeoff and landing (VTOL) aircraft

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Title
AMAZINGDIYPROJECTS: "Single blade propeller multirotor test 2", 2 October 2014 (2014-10-02), XP054979498, Retrieved from the Internet <URL:https://www.youtube.com/watch?v=CmhwROMBK8E> [retrieved on 20160815] *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7137885B1 (ja) 2022-03-30 2022-09-15 株式会社石川エナジーリサーチ 飛行装置の製造方法
JP2023148302A (ja) * 2022-03-30 2023-10-13 株式会社石川エナジーリサーチ 飛行装置の製造方法

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