WO2021039502A1 - Dispositif de confirmation de fonctionnement pour aéronef à décollage/ atterrissage vertical électrique - Google Patents

Dispositif de confirmation de fonctionnement pour aéronef à décollage/ atterrissage vertical électrique Download PDF

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Publication number
WO2021039502A1
WO2021039502A1 PCT/JP2020/031147 JP2020031147W WO2021039502A1 WO 2021039502 A1 WO2021039502 A1 WO 2021039502A1 JP 2020031147 W JP2020031147 W JP 2020031147W WO 2021039502 A1 WO2021039502 A1 WO 2021039502A1
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WIPO (PCT)
Prior art keywords
thrust
operation confirmation
unit
eds
confirmation device
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PCT/JP2020/031147
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English (en)
Japanese (ja)
Inventor
真梨子 橋本
輝 岩川
俊 杉田
優一 竹村
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株式会社デンソー
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Publication of WO2021039502A1 publication Critical patent/WO2021039502A1/fr

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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This disclosure relates to an operation confirmation device for an electric vertical takeoff and landing aircraft.
  • eVTOL electric vertical take-off and landing aircraft
  • the electric vertical take-off and landing aircraft is equipped with a plurality of electric drive systems (EDS: Electric Drive System) having motors, and a plurality of rotor blades are rotationally driven by a plurality of motors to obtain lift and thrust of the airframe.
  • EDS Electric Drive System
  • Patent Document 1 discloses a method for analyzing the function of a gas turbine engine. Similar to gas turbine engines, electric drive systems for electric vertical take-off and landing aircraft are also required to undergo functional tests at the time of replacement or periodic inspections.
  • the electric vertical takeoff and landing aircraft can take off and land even in a narrow space compared to fixed-wing aircraft equipped with a gas turbine engine, it is expected to be operated in various places.
  • the functional test of the electric drive system requires special equipment such as a jig for fixing the electric drive system to the ground when the rotor blades are rotationally driven, so that it is similar to an airplane having a gas turbine engine. , It is expected that it will be carried out at inspection sites equipped with dedicated equipment. From these facts, the inventors of the present application considered that it is inefficient to move the electric vertical take-off and landing aircraft from the operation site to the inspection site or the like in order to carry out the functional test. For this reason, a technology capable of performing a functional test of an electric drive system at an operating location of an electric vertical take-off and landing aircraft is desired.
  • an operation confirmation device is provided.
  • This operation confirmation device is an operation confirmation device of an electric drive system mounted on an electric vertical takeoff and landing aircraft, and the electric drive system includes a motor for driving a rotary blade of the electric vertical takeoff and landing aircraft.
  • the operation confirmation device includes a fixing portion with the ground and a connecting portion for directly connecting to the electric drive system or indirectly via the body of the electric vertical take-off and landing aircraft.
  • the operation confirmation device of this form of electric vertical take-off and landing aircraft a fixed portion with the ground and a connecting portion for directly or indirectly connecting with the electric drive system via the airframe of the electric vertical take-off and landing aircraft. Therefore, it is possible to prevent the place for carrying out the functional test from being limited to the inspection site or the like. Therefore, the functional test of the system under test can be performed at the operation site of the electric vertical take-off and landing aircraft.
  • This disclosure can also be realized in various forms.
  • it can be realized in the form of an electric vertical take-off and landing machine provided with an operation check device, an operation check method of the electric vertical take-off and landing machine, and the like.
  • FIG. 1 is a top view schematically showing the configuration of an electric vertical take-off and landing aircraft equipped with a control device.
  • FIG. 2 is a side view schematically showing the configuration of the electric vertical take-off and landing aircraft.
  • FIG. 3 is a block diagram showing the configuration of an electric vertical take-off and landing aircraft.
  • FIG. 4 is a perspective view schematically showing an operation confirmation device mounted on the system under test.
  • FIG. 5 is a flowchart showing the test processing procedure.
  • FIG. 6 is a graph showing an example of the test results.
  • FIG. 7 is a sequence diagram showing the communication procedure of the test.
  • eVTOL electric Vertical Take-Off and Landing aircraft
  • the eVTOL100 is configured as a manned aircraft that is electrically driven and can take off and land in the vertical direction.
  • the eVTOL 100 includes an airframe 20, a plurality of rotor blades 30, and a plurality of electric drive systems 10 (hereinafter, also referred to as "EDS (Electric Drive System) 10"), and a battery 40 shown in FIG. , The converter 42, the distributor 44, the airframe communication unit 64, and the notification unit 66.
  • the eVTOL 100 of the present embodiment has eight rotor blades 30 and eight EDS 10s, respectively. In FIG. 3, for convenience of illustration, two rotor blades 30 and EDS 10 among the eight rotor blades 30 and EDS 10 included in the eVTOL 100 are shown as representatives.
  • the airframe 20 corresponds to the portion of the eVTOL 100 excluding the eight rotors 30 and the EDS 10.
  • the airframe 20 includes an airframe main body 21, a strut 22, six first support 23, six second support 24, a main wing 25, and a tail 28.
  • the body portion 21 constitutes the body portion of the eVTOL 100.
  • the machine body 21 has a symmetrical structure with the body axis AX as the axis of symmetry.
  • the "airframe axis AX” means an axis that passes through the center of gravity CM of the airframe and is along the front-rear direction of the eVTOL 100.
  • the "machine weight center position CM” means the position of the center of gravity of the eVTOL 100 when the occupant is not on board and the weight is empty.
  • a passenger compartment (not shown) is formed inside the machine body 21.
  • an acceleration sensor 29 is mounted on the machine body 21.
  • the acceleration sensor 29 is composed of a three-axis sensor and measures the acceleration of the eVTOL 100. The measurement result by the acceleration sensor 29 is output to the control device 50.
  • the strut portion 22 has a substantially columnar appearance shape extending in the vertical direction, and is fixed to the upper part of the machine body portion 21.
  • the support column portion 22 is arranged at a position overlapping the machine weight center position CM of the eVTOL 100 when viewed in the vertical direction.
  • One end of each of the six first support parts 23 is fixed to the upper end of the support part 22.
  • Each of the six first support portions 23 has a substantially rod-like appearance shape, and is arranged radially at equal angular intervals so as to extend along a plane perpendicular to the vertical direction.
  • Rotors 30 and EDS 10 are arranged at the other end of each first support portion 23, that is, at an end portion located away from the strut portion 22.
  • Each of the six second support portions 24 has a substantially rod-like appearance shape, and connects the other ends (ends on the side not connected to the strut portion 22) of the first support portions 23 adjacent to each other. ing.
  • the main wing 25 is composed of a right wing 26 and a left wing 27.
  • the right wing 26 is formed so as to extend to the right from the main body portion 21 of the airframe.
  • the left wing 27 is formed so as to extend to the left from the main body portion 21 of the airframe.
  • a rotary wing 30 and an EDS 10 are arranged on the right wing 26 and the left wing 27, respectively.
  • the tail wing 28 is formed at the rear end of the main body 21 of the airframe.
  • Six of the eight rotors 30 are arranged at the ends of the second support portions 24, and are mainly configured as lift rotors 31 for obtaining lift of the airframe 20.
  • Two of the eight rotors 30 are arranged on the right wing 26 and the left wing 27, respectively, and are mainly configured as cruise rotors 32 for obtaining the thrust of the airframe 20.
  • Each rotor 30 is rotationally driven independently of each other around its own rotation axis.
  • Each rotor 30 has three blades 33 arranged at equal intervals with each other.
  • the blade angle of each rotor 30 is variably configured. Specifically, the blade angle is adjusted by an actuator (not shown) according to the instruction from the control device 50. As shown in FIG.
  • each rotor 30 is provided with a rotation speed sensor 34 and a torque sensor 35, respectively.
  • the rotation speed sensor 34 measures the rotation speed of the rotary blade 30.
  • the torque sensor 35 measures the rotational torque of the rotary blade 30. The measurement results by the sensors 34 and 35 are output to the control device 50.
  • the eight EDS 10s shown in FIG. 1 are configured as an electric drive system for rotationally driving each rotary blade 30. Six of the eight EDS 10s drive the lift rotor 31 to rotate. Two of the eight EDS 10s rotate the cruise rotor 32, respectively.
  • each EDS 10 includes a drive unit 11, a drive motor 12, a gearbox 13, a rotation speed sensor 14, a current sensor 15, a voltage sensor 16, a torque sensor 17, and an EDS side. It has a storage unit 18.
  • the drive unit 11 is configured as an electronic device including an inverter circuit (not shown) and a controller (not shown) that controls the inverter circuit.
  • the inverter circuit is composed of power elements such as IGBT (Insulated Gate Bipolar Transistor) and MOSFET (Metal-Oxide-Semiconductor Field-Effect Transistor), and is connected to the drive motor 12 according to the duty ratio according to the control signal supplied from the controller. Supply the drive voltage.
  • the controller is electrically connected to the control device 50 and supplies a control signal to the inverter circuit in response to a command from the control device 50.
  • the drive motor 12 is composed of a brushless motor in the present embodiment, and outputs rotational motion according to the voltage and current supplied from the inverter circuit of the drive unit 11.
  • the brushless motor instead of the brushless motor, it may be composed of an arbitrary motor such as an induction motor or a reluctance motor.
  • the gearbox 13 physically connects the drive motor 12 and the rotary blade 30.
  • the gearbox 13 has a plurality of gears (not shown), and decelerates the rotation of the drive motor 12 and transmits the rotation to the rotary blade 30.
  • the gearbox 13 may be omitted and the rotation shaft of the rotary blade 30 may be directly connected to the drive motor 12.
  • the rotation speed sensor 14 and the torque sensor 17 are provided in the drive motor 12, respectively, and measure the rotation speed and the rotation torque of the drive motor 12, respectively.
  • the current sensor 15 and the voltage sensor 16 are provided between the drive unit 11 and the drive motor 12, respectively, and measure the drive current and the drive voltage, respectively.
  • the measurement results of the sensors 14 to 17 are output to the control device 50 via the drive unit 11.
  • the test program is stored in advance in the EDS side storage unit 18.
  • Input information such as the test date and time, latitude and longitude, aircraft number, and air temperature and pressure input from the control device 50 is stored in the EDS side storage unit 18. Further, the EDS side storage unit 18 stores the measurement data from each sensor.
  • the battery 40 is composed of a lithium ion battery and functions as one of the power supply sources in the eVTOL 100.
  • the battery 40 mainly supplies electric power to the drive unit 11 of each EDS 10 to drive each drive motor 12.
  • the lithium ion battery instead of the lithium ion battery, it may be composed of an arbitrary secondary battery such as a nickel hydrogen battery, and instead of the battery 40 or in addition to the battery 40, any electric power such as a fuel cell or a generator may be used.
  • a source may be installed.
  • the converter 42 is connected to the battery 40, lowers the voltage of the battery 40, and supplies the voltage to the auxiliary equipment and the control device 50 of the eVTOL 100 (not shown).
  • the distributor 44 distributes the voltage of the battery 40 to the drive unit 11 included in each EDS 10.
  • the control device 50 is a microcomputer including a storage unit 51 and a CPU (Central Processing Unit), and is configured as an ECU (Electronic Control Unit).
  • the storage unit 51 has a ROM (Read Only Memory) and a RAM (Random Access Memory).
  • the CPU functions as a control unit 52 that controls the overall operation of the eVTOL 100 by executing a control program stored in advance in the storage unit 51.
  • the overall operation of the eVTOL 100 corresponds to, for example, a vertical takeoff and landing operation, a flight operation, an execution operation of a functional test of each EDS10, and the like.
  • the vertical takeoff and landing operation and the flight operation may be executed based on the set air route information, may be executed by the maneuvering of the occupant, and may be executed based on the command from the external control unit 510 included in the external device 500 described later. It may be executed.
  • the control unit 52 controls the rotation speed and rotation direction of the drive motor 12 of each EDS 10, the blade angle of each rotary blade 30, and the like.
  • each EDS10 is simple for the EDS10 that has been inspected and maintained after the EDS10 has been inspected, including periodic inspections and inspections when a problem occurs, and maintenance such as replacement of components of the EDS10 has been performed. It is executed to confirm the operation.
  • the EDS 10 that is the target of the functional test is referred to as a "test target system".
  • test target system operates normally and the rotary blade 30 (hereinafter, also referred to as “test target rotary blade”) that the test target system is rotationally driven rotates normally.
  • the airframe communication unit 64 has a function of performing wireless communication, transmits and receives information between the external communication unit 520 included in the external device 500 and the eVTOL 100, and is configured to be able to communicate with the control device 50.
  • wireless communication for example, wireless communication provided by a telecommunications carrier such as 4G (4th generation mobile communication system) or 5G (5th generation mobile communication system), or a wireless LAN according to the IEEE 802.11 standard. Communication etc. is applicable. Further, for example, USB (Universal Serial Bus) or wired communication according to the IEEE802.3 standard may be used.
  • the external device 500 corresponds to, for example, a computer for managing and controlling a server device or the like that controls a functional test and records test results.
  • the management / control computer may be, for example, a server device arranged in an air traffic control room, or a personal computer brought to the operation site of the eVTOL 100 by a maintenance worker who performs maintenance and inspection including a functional test. It may be.
  • the notification unit 66 notifies according to the instruction from the control device 50.
  • the notification unit 66 is composed of a display device mounted in the passenger room to display characters, images, etc., a speaker for outputting voice, warning sound, etc., and various types of notification units are provided to the passenger by visual information and auditory information. Notify information.
  • the operation confirmation device 70 shown in FIG. 4 is attached to the system under test when the functional test is executed.
  • the operation confirmation device 70 is fixed to the ground at an arbitrary place.
  • the operation confirmation device 70 measures and stores the thrust of the system under test in the functional test, and further determines the pass / fail of the functional test.
  • the operation confirmation device 70 includes a fixing unit 71, a connecting unit 72, a thrust-related value sensor unit 73, a main body unit 74, and a position adjusting unit 78.
  • the fixing portion 71 plays a role of fixing the entire operation checking device 70 to the ground via the position adjusting portion 78 described later.
  • the fixed portion 71 includes a rail-shaped rectangular plate extending in a direction parallel to the first support portion 23 and a rail-shaped rectangular plate extending in a direction perpendicular to the first support portion 23, and is formed in a grid pattern.
  • the fixing portion 71 is provided with four rail-shaped rectangular plates, any number of rectangular plates may be provided. Further, the fixing portion may be an arbitrary shape plate instead of the rail-shaped rectangular plate.
  • the connecting portion 72 is located at the upper end of the operation confirmation device 70, and plays a role of indirectly connecting to the EDS 10 via the body 20 of the eVTOL 100. Specifically, the connecting portion 72 is connected to the EDS 10 via the first supporting portion 23. The lower end side of the connecting portion 72 is connected to the thrust-related value sensor portion 73, which will be described later. The connecting portion 72 and the EDS 10 may be directly connected to each other.
  • the thrust-related value sensor unit 73 is arranged from the lower end of the connecting portion 72 to the upper end of the main body portion 74.
  • the thrust-related value sensor unit 73 has a columnar appearance shape.
  • the thrust-related value sensor unit 73 connects the connecting unit 72 and the main body 74, and incorporates a thrust sensor that measures the thrust of the EDS 10 of the system under test.
  • the thrust sensor has, for example, a spring and a strain gauge that detects a strain that is the elongation of the spring, and measures the thrust using the detected strain.
  • the main body 74 includes an interface 75, a pass / fail arithmetic unit 76, and a display 77.
  • the interface unit 75 outputs at least one of the output value of the EDS 10 acquired by the acquisition unit 76c described later and the execution result of the determination by the determination unit 76a described later to the outside.
  • the pass / fail determination arithmetic unit 76 includes a determination unit 76a, an arithmetic unit side storage unit 76b, and an acquisition unit 76c. In the present embodiment, the determination unit 76a determines whether or not the difference between the command value and the assumed output acquired by the interface unit 75 and the output value of the EDS 10 is within a predetermined range.
  • the arithmetic unit side storage unit 76b contains a command value acquired by the interface unit 75 and an assumed output (the theory of change patterns such as rotation speed, torque, motor temperature, thrust, and vibration when the drive motor 12 is test-driven. Value or estimated value) and the output value of EDS10 are stored.
  • the acquisition unit 76c acquires the command value and the assumed output for the EDS 10 and the output value of the EDS 10. In this embodiment, the acquisition unit 76c can directly acquire the thrust from the thrust-related value sensor unit 73.
  • the display unit 77 is a display for displaying the measurement result and the pass / fail judgment result.
  • the position adjusting unit 78 is arranged between the fixed portion 71 and the ground, and adjusts the fixed position with the ground.
  • the fixed position of the position adjusting portion 78 is adjusted by, for example, a caster with wheels mounted on the ground side of the fixing portion 71.
  • the position is adjusted by a universal vehicle whose traveling direction turns or a fixed vehicle whose traveling direction is fixed, and the rotation is stopped by a stopper (not shown) to fix the operation confirmation device 70 to the ground.
  • "fixed to the ground” means operation confirmation to the extent that the EDS 10 does not shift beyond a predetermined range even when stress is applied to the machine body 20 due to the execution of the functional test. It means that the device 70 is fixed to the ground.
  • Test processing procedure The test process shown in FIG. 5 means a process for exchanging the EDS 10 and performing a functional test of the EDS 10 after the exchange. Therefore, for example, it is executed when a part of the component parts of the EDS 10 breaks down, or when the periodic replacement time of the parts has come.
  • the operation confirmation device 70 is attached to the EDS 10 via the first support portion 23 (step S10). At this time, the EDS 10 is attached so that the vertical central axis of the EDS 10 and the vertical central axis of the operation confirmation device 70 coincide with each other.
  • the operation confirmation device 70 is fixed to the ground by the position adjusting unit 78 (step S11).
  • the above-mentioned steps S10 and S11 may be performed at the same time, or step S11 may be executed first and step S10 may be executed later.
  • the control unit 52 of the control device 50 outputs a rotation speed command to the drive unit 11 of the EDS 10 which is the test target system (step S12).
  • the system under test drives the rotor 30 to generate thrust (lift).
  • the operation confirmation device 70 is connected to the EDS 10 and fixed to the ground. Therefore, even if a thrust is generated by the execution of step S12, the operation confirmation device 70 generates a reaction force having the same magnitude as the thrust, so that the vertical displacement of the system under test is suppressed.
  • the thrust-related value sensor unit 73 measures the thrust of the test target system
  • the interface unit 75 is the thrust-related value sensor.
  • the measured value obtained by the unit 73 is stored in the arithmetic unit side storage unit 76b (step S13).
  • the determination unit 76a compares the thrust measured by the operation confirmation device 70 with the estimated thrust value to make a pass / fail determination (step S14). Specifically, as shown in FIG. 6, the determination unit 76a obtains the absolute value of the difference between the thrust measurement value and the thrust estimation value at predetermined time intervals. Then, if the absolute value of the difference obtained over the entire test period is smaller than a predetermined threshold value, it is determined to pass, and if it is equal to or more than the threshold value, it is determined to be rejected.
  • the test is determined to be unsuccessful.
  • the determination unit 76a outputs the measurement result and the pass / fail determination result to the control device 50 via the interface unit 75 (step S15). After the completion of step S15, the test process ends.
  • the fixing portion 71 to the ground is directly connected to the electric drive system 10 or indirectly via the body of the electric vertical take-off and landing aircraft. Since the connecting portion 72 is provided, it is possible to prevent the place for executing the functional test from being limited to the inspection site or the like. Therefore, the functional test of the system under test can be performed at the operation site of the electric vertical take-off and landing aircraft.
  • Second embodiment Since the configuration of the operation confirmation device 70 and the eVTOL 100 of the second embodiment is the same as the configuration of the operation confirmation device 70 and the eVTOL 100 of the first embodiment, the same components are designated by the same reference numerals. A detailed description will be omitted.
  • the pass / fail of the functional test is determined by using only the thrust, but in the second embodiment, the pass / fail of the functional test is determined by using parameters other than the thrust.
  • the sequence of test processing shown in FIG. 7 is started by a worker inputting an instruction to carry out a functional test from a user interface (not shown) connected to the control device 50.
  • the control unit 52 transmits a test start signal to the EDS 10 of the test target system (step S20). With such a signal as an opportunity, the EDS 10 confirms whether or not the rotary blade 30, the operation confirmation device 70, and the battery 40 are in a state in which the test can be started (Ready) (step S21). For example, if the rotor blade 30 is used, power is temporarily supplied to check whether or not the rotor blade 30 can rotate.
  • the operation confirmation device 70 If the operation confirmation device 70 is used, a predetermined operation confirmation signal is transmitted to the operation confirmation device 70, and it is confirmed whether or not the response signal is received. If it is the battery 40, the remaining capacity (SOC: StateOfCharge) of the battery 40 is confirmed. When the rotary blade 30, the operation confirmation device 70, and the battery 40 are Ready, the EDS 10 notifies the control device 50 to that effect (step S22).
  • the control device 50 that has received the Ready transmits input information such as the test date and time, latitude and longitude, the aircraft number, and temperature and pressure to the EDS 10 (step S23), and the EDS 10 transmits the received input information to the EDS side storage unit 18. Save to (step S24).
  • the EDS 10 transmits a test drive synchronization signal to the operation confirmation device 70, and the operation confirmation device 70 transmits a notification to the EDS 10 that the synchronization signal has been received (step S25). By transmitting and receiving such a synchronization signal, the test drive of the rotary blade 30 and the measurement of the thrust in the operation confirmation device 70 can be synchronized.
  • the operation confirmation device 70 that has received the synchronization signal records the rotation speed command value from the control device 50, the thrust measurement value acquired from the thrust related value sensor unit 73, and the data measured by the rotation speed sensor 34 and the torque sensor 35.
  • the EDS 10 transmits an output command request to the control device 50 (step S26).
  • the control device 50 transmits a command of the assumed output and the rotation speed to the EDS 10 (step S27).
  • the EDS 10 test-drives the drive motor 12 according to a test program stored in advance in the EDS-side storage unit 18 (step S28).
  • the drive unit 11 is controlled so as to supply the current value and the voltage value of a predetermined test pattern to the drive motor 12, and the electric power is supplied from the battery 40.
  • Thrust-related value The thrust measurement value acquired from the sensor unit 73, the assumed output from the EDS 10, and the rotation speed command are sequentially received and stored in the arithmetic unit side storage unit 76b (step S29).
  • the rotation speed sensor 34 and the torque sensor 35 transmit the measured data to the EDS 10 (step S30).
  • the EDS 10 sequentially transmits the measurement data measured by each sensor to the operation confirmation device 70 and the control device 50 (step S31).
  • the control device 50 and the operation confirmation device 70 sequentially store the measurement data from each sensor in the storage unit 51 and the arithmetic unit side storage unit 76b (step S32). Steps S27 to S32 are repeated by changing the frequency at which the drive voltage or the like is changed.
  • the control device 50 sends a signal for the end of the functional test to the EDS 10, and the EDS 10 that has received the signal for the end of the functional test sends a signal for the end of the functional test to the device 70 requiring operation confirmation (step S33).
  • a pass / fail determination is performed in the determination unit 76a of the operation confirmation device 70 (step S34), the pass / fail determination result is transmitted to the EDS 10 and transmitted from the EDS 10 to the control device 50 (step S35).
  • the pass / fail of the functional test is determined by using parameters other than the thrust. Therefore, a detailed functional test can be performed on the EDS 10 which is the test target system.
  • the thrust-related value sensor unit 73 has a built-in thrust sensor for measuring the thrust of the EDS 10 of the test target system, and the main body 74 includes the interface unit 75 and the determination unit 76a. , The arithmetic unit side storage unit 76b, the acquisition unit 76c, and the display unit 77 are provided, but the present embodiment is not limited to this.
  • the operation confirmation device 70 of the present embodiment includes a thrust sensor that measures the thrust of the EDS 10 of the system under test, an interface unit 75, a determination unit 76a, an arithmetic unit side storage unit 76b, an acquisition unit 76c, and a display unit. Of 77, some may be omitted.
  • the thrust-related value sensor unit 73 may be simply for connection. According to such a configuration, the configuration of the operation confirmation device 70 can be simplified.
  • Embodiment 2 The operation confirmation device 70 of each of the above embodiments includes a position adjusting unit 78 for adjusting a fixed position with the ground, but the operation confirmation device 70 of the present embodiment does not include the position adjustment unit 78. You may.
  • the thrust-related value sensor unit 73 in the operation confirmation device 70 of each of the above embodiments has a built-in thrust sensor for measuring the thrust of the EDS 10 of the test target system, but the present embodiment is not limited to this.
  • the output value of the EDS 10 includes a thrust-related value related to the thrust of the motor, and a thrust-related value sensor for measuring the thrust-related value may be further provided.
  • the acquisition unit 76c may acquire the thrust-related value from the thrust-related value sensor.
  • the thrust-related value is, for example, the vibration of the motor, which is measured by a vibration sensor which is a thrust-related value sensor. According to such a configuration, even in a configuration in which the EDS 10 does not have a vibration sensor, it is possible to determine the pass / fail of the functional test regarding the vibration of the motor.
  • Embodiment 4 In the operation confirmation device 70 of each of the above embodiments, the thrust-related values related to the thrust of the drive motor 12 have been acquired from the thrust-related value sensor unit 73 or the EDS 10, but this embodiment is limited to this. Absent. In the present embodiment, the thrust-related values related to the thrust of the drive motor 12 may be acquired from the control device 50.
  • Embodiment 5 In the operation confirmation device 70 of each of the above embodiments, the position of the operation confirmation device 70 with respect to the ground is adjusted by the position adjusting unit 78, but the operation confirmation device of the present embodiment is not limited to this.
  • the height of the operation confirmation device may be variable. For example, the length of the thrust-related value sensor unit 73 in the height direction may be changed.
  • the thrust-related value sensor unit 73 has a columnar appearance shape, but the thrust-related value sensor unit 73 in the present embodiment may have an arbitrary shape. Good. For example, it may have a rectangular parallelepiped appearance shape.
  • the present disclosure is not limited to the above-described embodiment, and can be realized by various configurations within a range not deviating from the purpose.
  • the technical features in each embodiment corresponding to the technical features in the embodiments described in the column of the outline of the invention may be used to solve some or all of the above-mentioned problems, or one of the above-mentioned effects. It is possible to replace or combine as appropriate to achieve a part or all. Further, if the technical feature is not described as essential in the present specification, it can be appropriately deleted.

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  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

L'invention concerne un dispositif de confirmation de fonctionnement (70) pour un système d'entraînement électrique (10) qui est monté sur un aéronef à décollage et atterrissage vertical électrique (100). Le système d'entraînement électrique comprend un moteur pour entraîner un rotor de l'aéronef à décollage et atterrissage vertical électrique. Le dispositif de confirmation de fonctionnement comprend : une partie de fixation (71) destiné à être fixé au sol ; et une partie de couplage (72) destinée à être couplée directement ou indirectement au système d'entraînement électrique par l'intermédiaire d'un fuselage (20) de l'aéronef à décollage et atterrissage vertical électrique.
PCT/JP2020/031147 2019-08-29 2020-08-18 Dispositif de confirmation de fonctionnement pour aéronef à décollage/ atterrissage vertical électrique WO2021039502A1 (fr)

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JP2019156471A JP7234865B2 (ja) 2019-08-29 2019-08-29 電動垂直離着陸機の動作確認用装置
JP2019-156471 2019-08-29

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CN113682492A (zh) * 2021-07-05 2021-11-23 中国人民解放军总参谋部第六十研究所 直升机起落架刚度和阻尼测试工装及测试方法

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CN102180270A (zh) * 2011-03-10 2011-09-14 北京航空航天大学 一种微小型旋翼飞行器实验平台及应用
CN105083588A (zh) * 2015-08-17 2015-11-25 华南农业大学 一种多旋翼无人飞行器性能测试平台及方法
US20160246304A1 (en) * 2015-02-24 2016-08-25 Qualcomm Incorporated Near-flight Testing Maneuvers for Autonomous Aircraft
JP2016188770A (ja) * 2015-03-30 2016-11-04 大分県 プロペラ特性測定装置
JP2017132461A (ja) * 2016-01-25 2017-08-03 大分県 無人飛行体の特性計測装置及びそれを用いた無人飛行体評価システム

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Publication number Priority date Publication date Assignee Title
CN102180270A (zh) * 2011-03-10 2011-09-14 北京航空航天大学 一种微小型旋翼飞行器实验平台及应用
US20160246304A1 (en) * 2015-02-24 2016-08-25 Qualcomm Incorporated Near-flight Testing Maneuvers for Autonomous Aircraft
JP2016188770A (ja) * 2015-03-30 2016-11-04 大分県 プロペラ特性測定装置
CN105083588A (zh) * 2015-08-17 2015-11-25 华南农业大学 一种多旋翼无人飞行器性能测试平台及方法
JP2017132461A (ja) * 2016-01-25 2017-08-03 大分県 無人飛行体の特性計測装置及びそれを用いた無人飛行体評価システム

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113682492A (zh) * 2021-07-05 2021-11-23 中国人民解放军总参谋部第六十研究所 直升机起落架刚度和阻尼测试工装及测试方法

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