WO2018203520A1 - 飛行機能付加装置およびロータユニット - Google Patents

飛行機能付加装置およびロータユニット Download PDF

Info

Publication number
WO2018203520A1
WO2018203520A1 PCT/JP2018/017166 JP2018017166W WO2018203520A1 WO 2018203520 A1 WO2018203520 A1 WO 2018203520A1 JP 2018017166 W JP2018017166 W JP 2018017166W WO 2018203520 A1 WO2018203520 A1 WO 2018203520A1
Authority
WO
WIPO (PCT)
Prior art keywords
unit
rotor
master unit
units
flight function
Prior art date
Application number
PCT/JP2018/017166
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
紀代一 菅木
和雄 市原
河野　雅一
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
Publication of WO2018203520A1 publication Critical patent/WO2018203520A1/ja

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
    • B64C13/20—Initiating means actuated automatically, e.g. responsive to gust detectors using radiated signals
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography

Definitions

  • the present invention relates to unmanned aircraft technology.
  • the multicopter For example, consider transporting heavy or large items using the multicopter. If it is not possible to lift it with a single multicopter, it is necessary to use a large multicopter with a higher power rotor or multiple multicopters.
  • the latter method has an advantage that the lift can be flexibly adjusted according to the weight and size of the transported object by appropriately changing the number of multicopters. On the other hand, simply increasing the number of multicopters will not allow them to fly together.
  • the problem to be solved by the present invention is to attach a plurality of rotor units to a transported object, and to connect a flight function adding device that enables the transported object to fly by linking the operations of these rotor units, and the rotor unit. It is to provide.
  • the flight function adding device of the present invention includes a plurality of rotor units, and each rotor unit includes a rotor having a driving source and a propeller connected to the driving source, and the rotor unit.
  • the master unit includes an inertial measurement device, configuration acquisition means for specifying a direction in which the thrust of each rotor unit changes the posture of the mounting target, and cooperative driving means for controlling the motor rotation speed of each slave unit. It is characterized by having.
  • a plurality of rotor units are attached to the mounting target, and the direction in which the thrust of each rotor unit changes the posture of the mounting target is specified by the configuration acquisition means of the master unit. And the motor rotation speed of these rotor units is managed centrally by the cooperative drive means which a master unit has. That is, according to the flight function adding device of the present invention, it is possible to configure a multicopter having the mounting target as a body frame. Furthermore, the flight function addition device of the present invention can flexibly adjust its lift by appropriately changing the number of slave units according to the weight and size of the mounting target.
  • the position of the center of gravity of the mounting target and the arrangement configuration of the rotor unit also change.
  • the position of the center of gravity of the mounting target and the arrangement configuration of the rotor unit also change.
  • this is automatically specified by the configuration acquisition means of the master unit, it is not necessary to manually adjust the parameters of the flight software for each mounting target, and the flight function is efficiently added to various mounting targets. It becomes possible to do.
  • each slave unit has an inertial measurement device, and the master unit can acquire a detection value of the inertial measurement device of each slave unit or a processing value of the detection value.
  • the master unit can more accurately grasp the change in the position and orientation of each slave unit. Thereby, the flight accuracy of the mounting target by the flight function adding device can be increased.
  • the configuration acquisition unit may change the orientation of the mounting target for each rotor unit including the master unit and / or a combination of the rotor units.
  • the direction in which the thrust of each rotor unit changes the posture of the mounting target can be specified.
  • the position of the center of gravity of the mounting target and the arrangement configuration of the rotor unit also change.
  • the mounting target is a hard article
  • a change in the position or posture of any one of the rotor units also appears as a change in the position or posture of another rotor unit via the mounting target. Therefore, prior to the flight of the mounting target, each rotor unit and a combination thereof are sequentially tested and detected, and the change in the posture of the mounting target at that time is detected, so that the thrust of each rotor unit changes the posture of the mounting target.
  • the direction can be specified. This also makes it possible to estimate the approximate arrangement direction of each slave unit around the position of the main rotor and the position of the center of gravity of the mounting target.
  • the master unit includes a photographing unit capable of photographing an image around the master unit, and an image recognizing unit that detects each slave unit from an image photographed by the photographing unit, and the configuration obtaining unit May be configured to specify the arrangement direction of these slave units centered on the position of the master unit from the position of each slave unit in the image.
  • the arrangement configuration of the rotor unit Prior to flight, by detecting each rotor unit from an image taken around the master unit, the arrangement configuration of the rotor unit can be specified. Thereby, the configuration acquisition means can identify or predict the direction in which the thrust of each rotor unit changes the posture of the mounting target. Based on the arrangement configuration, it becomes possible to conduct a more detailed test or to omit a part of the test.
  • the master unit preferably further includes an orientation sensor, an altitude sensor, and a GPS antenna.
  • the master unit When the master unit includes these sensors, it is possible to specify the position information of the master unit including the longitude and latitude and the azimuth angle of the nose based on an absolute index. Thereby, it becomes possible to fly the mounting target autonomously.
  • the plurality of rotor units include a CW unit in which the propeller rotates clockwise in a plan view and a CCW unit in which the propeller rotates counterclockwise in a plan view.
  • the CW unit and the CCW unit are The configuration may be such that the mounting target is alternately arranged along the circumferential direction of the mounting target.
  • the rotation direction of the propellers of these rotor units needs to be specified. Further, in order to stably perform this while canceling the counter torque of the propeller during the operation of the aileron and elevator to be mounted, it is convenient that the CW units and the CCW units are alternately arranged in the circumferential direction. By alternately arranging the CW units and CCW units constituting the flight function adding device in advance along the circumferential direction of the mounting target, it becomes possible to fly the mounting target in the same control method as a general multicopter. .
  • each rotor unit may be a counter-rotating rotor in which a pair of propellers rotating in opposite directions are arranged in the axial direction.
  • each rotor unit By making the rotor of each rotor unit a counter-rotating rotor capable of canceling the counter-torque independently, even in a configuration using an odd number of rotor units such as a tricopter, a special for processing the counter-torque There is no need to implement a separate mechanism. As a result, the lift of the flight function adding device can be adjusted in units of one rotor unit, and the lift can be adjusted more flexibly according to the weight and size of the mounting target.
  • the rotor unit of the present invention is a master unit of the flight function adding device, and the master unit can also operate as the slave unit.
  • a flight function addition device can be configured with a single type of rotor unit. Thereby, it is not necessary to be aware of the master / slave model when the rotor unit is mounted, and the master unit can be freely changed after the rotor unit is mounted.
  • the flight function adding device and the rotor unit of the present invention it is possible to link the operations of a plurality of rotor units to fly the mounting target.
  • FIG. 6 is a schematic plan view showing the rotation direction of each rotor unit R of the flight function addition device F.
  • 3 is a block diagram schematically showing a functional configuration of a master unit 10.
  • FIG. 3 is a block diagram schematically illustrating a functional configuration of a slave unit 50.
  • FIG. It is a plane schematic diagram which shows the mode of the test drive of the rotor unit R by the structure acquisition program CA.
  • FIG. 6 is a perspective view showing a state in which a flight function adding device F is attached to a chair 93. It is a perspective view which shows the external appearance of rotor unit Rb concerning 2nd Embodiment. It is a perspective view which shows a mode that the flight function addition apparatus Fb which consists of three rotor units Rb was attached to the desk 92 which is the mounting object of 2nd Embodiment. It is a perspective view which shows the external appearance of rotor unit Rc (master unit 10c) concerning 3rd Embodiment. It is a block diagram showing typically the functional composition of master unit 10c.
  • FIG. 1 is a perspective view showing an appearance of a rotor unit R according to the first embodiment.
  • FIG. 2 is a perspective view showing a state in which a flight function adding device F including four rotor units R is attached to a table 91 that is a mounting target of this example.
  • the rotor unit R is provided at a substantially spindle-shaped main body portion 11, a rod-shaped arm portion 12 that extends from the outer surface of the main body portion 11 to the outside in the radial direction of the main body portion 11, and the tip of the arm portion 12.
  • the clamp part 13 is provided.
  • the main body portion 11 of this example includes a case 11a that is a hollow container body and a spinner cap 11b disposed above the main body portion 11a.
  • the clamp portion 13 is a coupling portion that fixes the rotor unit R to the table 91.
  • the clamp part 13 of this example has a structure that can suitably tighten the circular pipe part or flat plate part to be mounted, the coupling part of the present invention is not limited to the form of the clamp part 13. As long as the rotor unit can be firmly fixed to the mounting target, the shape, structure, and coupling means for the mounting target are not limited.
  • the rotor unit R includes a rotor 27 including a motor 271 as a driving source and a fixed pitch propeller 272 (hereinafter simply referred to as “propeller 272”) attached to an output shaft of the motor 271.
  • the motor 271 is accommodated in the case body 11a. Further, a spinner cap 11 a is put on the blade root portion of the propeller 272.
  • the flight function addition device F of this example includes four rotor units R.
  • the rotor unit R of the flight function adding device F is roughly divided into a master unit 10 and a slave unit 50.
  • the master unit 10 is one of the plurality of rotor units R.
  • the master unit 10 is a unit that controls the motor rotation speed (throttle) of these rotor units R in a unified manner and operates the flight function adding device F as a unit.
  • the slave unit 50 is a rotor unit R other than the master unit 10.
  • the slave unit 50 is a unit that rotates the rotor 27 at a speed instructed by the master unit 10.
  • the master unit 10 in this example is linked to each slave unit 50 so as to be capable of wireless communication.
  • “link” means pairing of the rotor unit R that designates a communication partner, and means that the master unit 10 and each slave unit 50 are connected by a wireless virtual cable.
  • the communication method between the master unit 10 and the slave unit 50 is not limited to wireless communication, and these may be wired with a communication cable.
  • FIG. 3 is a schematic plan view showing the rotation direction of each rotor unit R of the flight function adding device F.
  • the rotor unit R of the flight function adding device F includes a CW unit (the master unit 10 and the slave unit 50 at the upper left in FIG. 3) in which the propeller 272 rotates in a plan view and a propeller 272 in a counterclockwise view in a plan view.
  • CCW units upper right and lower left slave units 50 in FIG. 3). These CW units and CCW units are alternately arranged along the circumferential direction of the table 91.
  • the rotation direction of the propeller 272 of each rotor unit R needs to be specified. Further, in order to stably perform this while canceling the counter torque of the propeller 272 during the aileron and elevator operations of the table 91, it is convenient that the CW units and the CCW units are alternately arranged in the circumferential direction. . In this example, the CW unit and the CCW unit constituting the flight function adding device F are alternately arranged in advance along the circumferential direction of the table 91, so that the table 91 is controlled by the same control method as a general multicopter. It is possible to fly.
  • FIG. 4 is a block diagram schematically illustrating the functional configuration of the master unit 10.
  • the master unit 10 mainly includes a flight controller FC that is a control unit of the flight function adding device F, a receiver 32 that receives a control signal from an operator (control terminal 31), a rotor 27, and an ESC 26 that is a drive circuit of the rotor 27. (Electric Speed Controller) and a battery 29 for supplying power to them.
  • FC flight controller
  • FC receives a control signal from an operator (control terminal 31)
  • a rotor 27 that is a drive circuit of the rotor 27.
  • Electric Speed Controller Electric Speed Controller
  • the rotor 27 includes a motor 271 that is a drive source and a propeller 272 attached to the motor 271.
  • the ESC 26 is connected to the motor 271 and controls the rotation speed of the motor 271 at a speed instructed from the flight controller FC.
  • 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 flash memory, and a PWM (Pulse Width Modulation) controller 25 that sends a PWM signal to the ESC 26.
  • 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 flash memory
  • PWM Pulse Width Modulation
  • the flight controller FC further includes a flight control sensor group 23 and a GPS antenna 24 (hereinafter collectively referred to as “sensors”), which are connected to the control device 20.
  • the GPS antenna 24 is precisely a navigation satellite system (NSS) receiver.
  • the GPS antenna 24 acquires current longitude and latitude values and time information from a global navigation satellite system (GNSS) or a regional navigation satellite system (RNSS).
  • GNSS global navigation satellite system
  • RNSS regional navigation satellite system
  • the flight control sensor group 23 of the master unit 10 in this example includes an IMU (Inertial Measurement Unit) 231 having a triaxial acceleration sensor and a triaxial angular velocity sensor, an atmospheric pressure sensor (altitude sensor), a triaxial geomagnetic sensor ( Orientation sensor).
  • the control device 20 can acquire position information including the latitude and longitude of the master unit 10, the altitude, and the azimuth angle of the nose, in addition to the tilt and rotation of the master unit 10, using these sensors and the like.
  • cooperation is a program that controls the attitude and basic flight operation of the table 91 (hereinafter also simply referred to as “table 91”) on which the flight function addition device F is mounted.
  • a drive program CD is stored.
  • the cooperative driving program CD adjusts the motor rotation speed of each rotor unit R based on the information acquired from the sensor or the like according to the control signal of the operator (control terminal 31), and corrects the attitude of the table 91 and the disturbance of the flight position.
  • the table 91 is allowed to fly.
  • the cooperative driving program CD inputs a PWM signal to the rotor 27 of the master unit 10 and drives the rotor 27 of each slave unit 50 based on the configuration of each rotor unit R specified by the configuration acquisition program CA described later.
  • These signals are transmitted from the communication device 35 to each slave unit 50. Thereby, the drive of each rotor unit R is linked and the flight operation
  • the flight function adding device F is manually operated by the operator using the control terminal 31 and the flight plan FP including the flight path and speed of the master unit 10, altitude parameters, and commands of the prescribed operation in the autonomous flight program AP. And the flight function adding device F can be allowed to fly autonomously (hereinafter, such autonomous flight is referred to as “autopilot”).
  • the master unit 10 in this embodiment has an advanced flight control function.
  • the master unit in the present invention is not limited to the form of the master unit 10, and a part of the sensor is omitted from the sensor or the like, for example, as a requirement that it has a function corresponding to the IMU 231 and the cooperative driving program CD. It is also possible to use one that does not have an autopilot function and can fly only by manual operation.
  • FIG. 5 is a block diagram schematically illustrating the functional configuration of the slave unit 50.
  • the same components as those of the master unit 10 are denoted by the same reference numerals as those of the master unit 10, and detailed description thereof is omitted.
  • the appearance of the slave unit 10 is the same as that of the master unit 10 (see FIG. 1).
  • the slave unit 50 mainly includes a communication device 36 that receives a control signal from the master unit 10, an ESC 26 that is a drive circuit for the rotor 27, and a battery 29 that supplies power to these.
  • the rotor 27 of the slave unit 50 includes a motor 271 as a drive source and a propeller 272 attached to the motor 271.
  • the ESC 26 is connected to the motor 271 and controls the rotation speed of the motor 271 in accordance with a control signal input from the communication device 36.
  • the slave unit 50 of this example includes an IMU 231.
  • the displacement amount of the slave unit 50 detected by the IMU 231 is fed back to the master unit 10 via the communication device 36.
  • the master unit 10 and the slave unit 50 are configured as different models.
  • the master unit 10 includes the slave unit 50. It has all the functions that. Therefore, the master unit 10 can also operate as the slave unit 50. Therefore, all the rotor units R of the flight function adding device F are configured by the model of the master unit 10, and by selecting the rotor unit R to be the master unit 10 from among the settings, the rotor unit R of a single model can be selected.
  • the flight function addition device F can be configured. This eliminates the need to be aware of the master / slave model when the rotor unit R is mounted, and the master unit 10 can be freely changed after the rotor unit R is mounted.
  • FIG. 6 is a schematic plan view showing a state of test drive of the rotor unit R by the configuration acquisition program CA.
  • the thrust of each rotor unit R In order to maintain the attitude of the table 91 during flight and to perform the elevator, aileron, and ladder operation of the table 91 (hereinafter, such operations are collectively referred to as “steering control”), the thrust of each rotor unit R
  • the direction in which the posture of the table 91 is changed needs to be specified. That is, it is necessary to specify the balance of the motor rotation speed of each rotor unit R when steering control of the table 91 (hereinafter, such balance is referred to as “throttle balance”).
  • the present invention if the shape or size of the mounting target changes, the position of the center of gravity of the mounting target and the mounting position of the rotor unit R also change.
  • the master unit 10 of this example automatically specifies the throttle balance at the time of steering control of the table 91 by the configuration acquisition program CA.
  • the above-described cooperative drive program CD adjusts the motor rotation speed of each rotor unit R based on the throttle balance specified by the configuration acquisition program CA, and maintains the attitude of the table 91 in units of the entire flight function adding device F. Steering control is performed.
  • the “posture of the table 91” refers to the inclination of the table 91 and the direction in the circumferential direction.
  • the circumferential direction of the table 91 appears as the nose direction (heading) of the flight function adding device F, but the direction as the nose can be arbitrarily set.
  • the flight function adding device F may be defined as a quad plus configuration, and the opposite side of the extension direction of the arm 12 of the master unit 10 (the direction indicated by the arrow H in FIG. 6) may be set as the nose direction manually. -It may be automatically set in another direction.
  • the configuration acquisition program CA of this example test-drives each rotor unit R including the master unit 10 and a combination thereof at a motor rotational speed at which the posture of the table 91 changes, Whether or not the steering control of the table 91 is possible and its control method are specified from the change in the posture of 91.
  • the table 91 in this example is a hard article, and the change in the position or posture of any one of the rotor units R also appears as a change in the position or posture of another rotor unit R via the table 91. Therefore, each rotor unit R or a combination of these is automatically and sequentially tested, and the change in the attitude of the table 91 at that time (inclination of the IMU 231 of the master unit 10) is detected, so that the throttle balance of each rotor unit R is detected. Can be specified. This also makes it possible to specify the approximate arrangement direction of each slave unit 50 around the position of the main rotor 10 and the position of the center of gravity of the table 91.
  • each slave unit 50 is a unit B, C, or D clockwise from the unit A. Further, it is assumed that the center of gravity g of the table 91 is in the center of the table 91.
  • the configuration acquisition program CA of this example increases the throttle (motor rotational speed) of each unit one by one clockwise from the unit A until the posture of the table 91 changes, and from the detected value of the IMU 231 of the unit A
  • the inclination direction of unit A at that time is acquired.
  • the top of the unit A is inclined in the a direction.
  • the unit B is test-driven, the top of the unit A is tilted in the b direction
  • the unit C is test-driven, it is tilted in the c direction
  • the unit D is test-driven, it is tilted in the d direction.
  • the center of gravity g of the table 91 is at the center of the table 91, and each rotor unit R is arranged line-symmetrically and point-symmetrically so as to pass through the center of gravity g. Further, the rotation direction of each rotor unit R is also known in advance. Therefore, even with the above-described test drive alone, the aircraft is ready for flight. On the other hand, when the position of the center of gravity of the mounting target is biased or the arrangement of each rotor unit R is irregular, not only each rotor unit is tested and driven, but also a combination of these rotor units is tested. By driving, it is possible to specify whether or not the steering control of the mounting target is possible and the control method thereof.
  • the four rotor units R are attached to the table 91, and the throttle balance at the time of steering control of the table 91 is specified by the configuration acquisition program CA included in the master unit 10. .
  • the operations of the rotor units R are centrally managed by the cooperative drive program CD that the master unit 10 has.
  • the flight function addition device F constitutes a multicopter having the table 91 as a body frame.
  • the flight function addition apparatus F of this example can adjust a lift flexibly by changing suitably the number of the slave units 50 according to the weight and size of mounting
  • the slave unit 50 of this example has the IMU 231, and the master unit 10 can acquire the detection value of the IMU 231 of the slave unit 50. Thereby, the master unit 10 can grasp
  • FIG. 7 is a perspective view showing a state in which the flight function adding device F of this example is attached to a chair 93 that is a mounting target of the present invention.
  • the master unit 10 of the present example performs a test drive of each rotor unit R, thereby specifying the throttle balance during steering control. Therefore, for example, as in the chair 93 in FIG. 7, even when the rotor unit R is a special mounting target that is arranged at different heights, the posture is maintained and the throttle balance for performing the steering control is specified. be able to.
  • FIG. 8 is a perspective view showing an appearance of the rotor unit Rb according to the second embodiment.
  • FIG. 9 is a perspective view showing a state in which a flight function adding device Fb including three rotor units Rb is attached to a desk 92 that is a mounting target of this example.
  • the same components as those of the previous embodiment are denoted by the same reference numerals as those of the previous embodiment, and detailed description thereof is omitted.
  • the rotor unit Rb of this example includes a substantially spindle-shaped main body portion 11, a rod-shaped arm portion 12 that extends from the outer surface of the main body portion 11 to the radially outer side of the main body portion 11, and the arm portion 12. It has the clamp part 13 provided in the front-end
  • the rotor unit Rb includes two rotors 27 including a motor 271 as a drive source and a propeller 272 attached to the motor 271. These two rotors 27 are counter-rotating rotors in which a pair of propellers 272 rotating in opposite directions are arranged in the axial direction.
  • each rotor unit Rb is a counter-rotating rotor capable of canceling the counter-torque alone, an odd number of rotor units Rb are used as in the flight function adding device Fb shown in FIG. There is no need to implement a special mechanism for handling anti-torque. As a result, the lift of the flight function adding device Fb can be adjusted in units of the rotor unit Rb, and more flexible adjustment of the lift according to the weight and size of the mounting target is possible.
  • the basic functions of the master unit 10b and the slave unit 50b constituting the flight function adding device Fb are the master unit 10 and the slave unit 50 of the flight function adding device F, except that the rotor 27 is a counter-rotating propeller. It is the same.
  • FIG. 10 is a perspective view showing an appearance of a rotor unit Rc (master unit 10c) according to the third embodiment.
  • Rc master unit 10c
  • the rotor unit Rc of this example includes a substantially spindle-shaped main body portion 11, a rod-shaped arm portion 12 extending from the outer surface of the main body portion 11 to the radially outer side of the main body portion 11, and the arm portion 12. It has the clamp part 13 provided in the front-end
  • the rotor unit Rc includes a rotor 27 including a motor 271 that is a drive source and a propeller 272 attached to the motor 271.
  • rotor units Rc of this example are mounted in line symmetry and point symmetry along the circumferential direction of the table 91, and the rotation direction thereof is also the first embodiment. It is the same as the rotor unit R of the embodiment.
  • the main unit 11 of the master unit 10c has a movable camera that is a photographing unit capable of changing the photographing direction in the circumferential direction of the master unit 10c and a predetermined angular range in the vertical direction with the motor 41 as a drive source. 40 is provided.
  • FIG. 11 is a block diagram schematically illustrating the functional configuration of the master unit 10c. Since the function regarding the flight control of the master unit 10c is the same as that of the master unit 10 of the first embodiment, the description thereof is omitted. The difference between the master unit 10c and the master unit 10 is that the master unit 10c includes the movable camera 40 and that the configuration acquisition program CA has an image recognition program IR.
  • the image recognition program IR is a program for detecting the rotor unit Rc from an image photographed by the movable camera 40.
  • the master unit 10c Prior to the flight, the master unit 10c images the entire circumference of the master unit 10c with the movable camera 40, and detects each rotor unit Rc from the image. Thereby, the arrangement direction of each slave unit (rotor unit Rc other than the master unit 10c) around the position of the master unit 10c can be specified.
  • each rotor unit Rc can be detected more accurately and easily. It is also possible to specify the distance between the master unit 10c and each slave unit from the size. Further, the distance between the master unit 10c and each slave unit can also be specified by using a stereo camera as the movable camera 40. In addition, for example, a receiver compatible with a short-range wireless communication protocol capable of estimating a distance from a radio wave source from the attenuation of radio wave intensity due to propagation loss is mounted on the master unit 10c, and each slave unit supports the same protocol. By mounting the transmitter, it is possible to estimate the distance between the master unit 10c and each slave unit from the radio wave intensity detected by the receiver of the master unit 10c.
  • each rotor unit Rc By performing this test drive, it becomes possible to specify a more accurate throttle balance. Further, it is considered that the preparation for flight may be completed by specifying the positional relationship of each rotor unit Rc by limiting the shape of the mounting target, the position of its center of gravity, and the arrangement of each rotor unit Rc.
  • a motor is used as a propeller drive source, but this may be an engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
PCT/JP2018/017166 2017-05-02 2018-04-27 飛行機能付加装置およびロータユニット WO2018203520A1 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2017-091912 2017-05-02
JP2017091912A JP6579523B2 (ja) 2017-05-02 2017-05-02 飛行機能付加装置およびロータユニット

Publications (1)

Publication Number Publication Date
WO2018203520A1 true WO2018203520A1 (ja) 2018-11-08

Family

ID=64016187

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2018/017166 WO2018203520A1 (ja) 2017-05-02 2018-04-27 飛行機能付加装置およびロータユニット

Country Status (2)

Country Link
JP (1) JP6579523B2 (enrdf_load_stackoverflow)
WO (1) WO2018203520A1 (enrdf_load_stackoverflow)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7031733B2 (ja) * 2018-03-23 2022-03-08 日本電気株式会社 遠隔制御装置、遠隔制御システム、遠隔制御方法、および遠隔制御プログラム
JP2020157922A (ja) * 2019-03-26 2020-10-01 三菱日立パワーシステムズ株式会社 支持位置決定装置、支持位置決定方法、およびプログラム
JPWO2023203675A1 (enrdf_load_stackoverflow) * 2022-04-20 2023-10-26

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001039397A (ja) * 1999-08-02 2001-02-13 Komatsu Ltd 水平回転翼を有した飛翔体
JP2014039417A (ja) * 2012-08-17 2014-02-27 Ricoh Co Ltd モータ制御装置およびモータ制御方法、ならびに、画像形成装置
JP2016043927A (ja) * 2014-08-26 2016-04-04 パロット 投げスタートにおける回転翼の無人機を動的に制御する方法
WO2016059877A1 (ja) * 2014-10-17 2016-04-21 ソニー株式会社 制御装置、制御方法および飛行体デバイス
JP2016138854A (ja) * 2015-01-29 2016-08-04 株式会社ゼンリンデータコム ナビゲーションシステム、ナビゲーション装置、飛行体、ナビゲーション連携制御方法、ナビゲーション装置用連携制御プログラム及び飛行体用連携制御プログラム
WO2016134193A1 (en) * 2015-02-19 2016-08-25 Amazon Technologies, Inc. Collective unmanned aerial vehicle configurations
JP2016173739A (ja) * 2015-03-17 2016-09-29 セコム株式会社 飛行ロボット制御システム及び飛行ロボット
WO2016193884A1 (en) * 2015-05-29 2016-12-08 Verity Studios Ag An aerial vehicle
JP2016208255A (ja) * 2015-04-22 2016-12-08 みこらった株式会社 移動型プロジェクション装置
WO2017038809A1 (ja) * 2015-09-04 2017-03-09 株式会社プロドローン 滞空位置制御装置
US9605926B1 (en) * 2016-01-07 2017-03-28 DuckDrone, LLC Drone-target hunting/shooting system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3189025B2 (ja) * 1994-02-24 2001-07-16 ヤマハ発動機株式会社 飛行体の姿勢制御装置
JP3185081B2 (ja) * 1994-03-10 2001-07-09 ヤマハ発動機株式会社 無人ヘリコプタの姿勢制御装置

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001039397A (ja) * 1999-08-02 2001-02-13 Komatsu Ltd 水平回転翼を有した飛翔体
JP2014039417A (ja) * 2012-08-17 2014-02-27 Ricoh Co Ltd モータ制御装置およびモータ制御方法、ならびに、画像形成装置
JP2016043927A (ja) * 2014-08-26 2016-04-04 パロット 投げスタートにおける回転翼の無人機を動的に制御する方法
WO2016059877A1 (ja) * 2014-10-17 2016-04-21 ソニー株式会社 制御装置、制御方法および飛行体デバイス
JP2016138854A (ja) * 2015-01-29 2016-08-04 株式会社ゼンリンデータコム ナビゲーションシステム、ナビゲーション装置、飛行体、ナビゲーション連携制御方法、ナビゲーション装置用連携制御プログラム及び飛行体用連携制御プログラム
WO2016134193A1 (en) * 2015-02-19 2016-08-25 Amazon Technologies, Inc. Collective unmanned aerial vehicle configurations
JP2016173739A (ja) * 2015-03-17 2016-09-29 セコム株式会社 飛行ロボット制御システム及び飛行ロボット
JP2016208255A (ja) * 2015-04-22 2016-12-08 みこらった株式会社 移動型プロジェクション装置
WO2016193884A1 (en) * 2015-05-29 2016-12-08 Verity Studios Ag An aerial vehicle
WO2017038809A1 (ja) * 2015-09-04 2017-03-09 株式会社プロドローン 滞空位置制御装置
US9605926B1 (en) * 2016-01-07 2017-03-28 DuckDrone, LLC Drone-target hunting/shooting system

Also Published As

Publication number Publication date
JP2018188011A (ja) 2018-11-29
JP6579523B2 (ja) 2019-09-25

Similar Documents

Publication Publication Date Title
US10281930B2 (en) Gimbaled universal drone controller
US20220137643A1 (en) Aircraft control method and aircraft
EP4250553B1 (en) Multi-rotor tonal noise control for uav
JP6239619B2 (ja) 位置決め及び相互動作用紐集合体を備えたフライングカメラ
US8953933B2 (en) Aerial photogrammetry and aerial photogrammetric system
JP6390013B2 (ja) 小型無人飛行機の制御方法
JP6671375B2 (ja) 無人機の飛行補助方法
US11447235B2 (en) Unmanned aerial vehicle
JP2017065467A (ja) 無人機およびその制御方法
JP5713231B2 (ja) 飛行体
US10882600B2 (en) Foldable unmanned aerial vehicle
WO2018203520A1 (ja) 飛行機能付加装置およびロータユニット
KR20120081500A (ko) 복수개의 회전익을 가진 비행장치 및 그 제어방법
WO2018214155A1 (zh) 用于设备姿态调整的方法、设备、系统和计算机可读存储介质
EP3269639B1 (en) Aircraft and roll method thereof
WO2020017486A1 (ja) 無人航空機
JP2019077207A (ja) 回転翼航空機
US20200249019A1 (en) Attachable-detachable unit and sensor calibrating method using the same
JP2019043394A (ja) 回転翼航空機
WO2018016514A1 (ja) 姿勢安定化装置およびこれを備える無人航空機
JP2009096369A (ja) 無人無線操縦ヘリコプタの操縦支援装置
WO2019044865A1 (ja) 無人移動体およびこれを用いた無人移動体システム
JP6547109B2 (ja) 飛行制御装置およびこれを備える無人航空機
JP2006282034A (ja) 水平速度方位計

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18795269

Country of ref document: EP

Kind code of ref document: A1

DPE2 Request for preliminary examination filed before expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18795269

Country of ref document: EP

Kind code of ref document: A1