JP2023021175A - Aircraft, control method, and control device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a processing system, an unmanned aircraft, and a dust condition estimation method capable of estimating a dust condition before the aircraft capable of flying in an unmanned state is affected by dust.

SOLUTION: A flight system includes an aircraft comprising a connection portion for connecting a cargo, the connection portion including a mechanism for connecting or releasing the cargo. The flight system performs detachment control for detaching, from the aircraft, the cargo connected by the connection portion, the detachment control causing the mechanism of the connection portion to perform release operation. Then, after the release operation of the mechanism is detected by release operation detection processing for detecting the release operation of the mechanism, the flight system performs load detection processing for detecting a mechanical load applied to the connection portion, and regarding movement of the aircraft after the detection of the mechanical load has be performed, and performs control which is variable according to the mechanical load.

SELECTED DRAWING: Figure 7

COPYRIGHT: (C)2023,JPO&INPIT

Description

TECHNICAL FIELD The present invention relates to a technical field such as a control method for releasing cargo loaded on an aircraft from the aircraft.

2. Description of the Related Art Conventionally, in order to transport cargo by an unmanned aircraft capable of flying, an aircraft is known which has a gripper for gripping the cargo and a support wire to which the cargo is connected at the tip. For example, the flying object disclosed in Patent Document 1 is configured to perform cargo handling by opening and closing grippers based on commands from a base station. Further, the unmanned aerial vehicle disclosed in Patent Document 2 is configured to detect the landing of the cargo when the cargo supported by the support wires is lowered from the sky toward the ground.

JP 2018-47866 A International Publication No. 2017/078118 WO2017/053386 WO2017/053392

By the way, when the above-mentioned aircraft automatically releases the cargo without human intervention at the destination (that is, when release control is performed), the cargo may get caught in some part of the aircraft. , the cargo may not release properly. This is undesirable for aircraft.

Therefore, an aircraft, a control method, and a control device are provided that are capable of taking appropriate measures according to the success or failure of the separation of cargo.

The invention according to claim 1 is a control method executed by a system including an aircraft having a connection for connecting cargo, the connection including a mechanism for connecting or releasing the cargo, a first control step of performing release control for causing the mechanism of the connection portion to perform a release operation, which is release control for releasing the cargo connected by the connection portion from the aircraft; and detecting the release operation of the mechanism. and a load detection step of performing a load detection process for detecting the mechanical load applied to the connecting portion after the release operation of the mechanism is detected by the release operation detection process. and a second control step of performing different control according to the dynamic load with respect to movement of the aircraft after the dynamic load is detected. As a result, it is possible to distinguish whether there is an abnormality in the mechanism of the connecting portion or whether the cargo is not released even though the mechanism operates normally.

The invention according to claim 2 is the control method according to claim 1, wherein the mechanism includes an actuator, and the release operation is performed by driving the actuator.

According to a third aspect of the present invention, in the control method according to the first aspect, the mechanism includes an electromagnet, and the releasing operation is performed by stopping power supply to the electromagnet.

The invention according to claim 4 is the control method according to claim 1, wherein the connection unit includes a wire to which the cargo is connected and a reel for feeding or winding the wire. is a state in which the aircraft is in flight, a first determination step of determining success or failure of detachment of the cargo based on the dynamic load; a second determination step of determining whether the aircraft can land safely based on the winding amount of the wire; and the second determination step determines whether the aircraft can land safely. is determined, in the second control step, control is performed to land the aircraft. As a result, it is possible to improve the accuracy of determining whether or not the aircraft can land safely.

The invention according to claim 5 is an aircraft comprising a connecting portion for connecting cargo, the connecting portion including a mechanism for connecting or releasing the cargo, wherein the cargo connected by the connecting portion is A first control unit that performs detachment control for detaching from the aircraft, and performs detachment control that causes the mechanism of the connection unit to perform a release operation; and a release operation that performs release operation detection processing for detecting the release operation of the mechanism. a detection unit, a load detection unit that performs load detection processing for detecting a mechanical load applied to the connection unit after the release operation of the mechanism is detected by the release operation detection processing, and detection of the mechanical load. and a second control unit that performs different control according to the dynamic load with respect to the movement of the aircraft after the is performed.

According to a sixth aspect of the present invention, there is provided a control device for controlling an aircraft comprising a connection portion for connecting cargo, the connection portion including a mechanism for connecting or releasing the cargo, wherein the connection portion a first control unit that performs release control for releasing the connected cargo from the aircraft and causes the mechanism of the connection unit to perform release operation; and release operation detection for detecting the release operation of the mechanism. a load detection unit that performs a load detection process for detecting a mechanical load applied to the connecting part after the release action of the mechanism is detected by the release action detection process; and a second control unit that performs different control according to the dynamic load with respect to the movement of the aircraft after the dynamic load is detected.

ADVANTAGE OF THE INVENTION According to this invention, an aircraft can be made to take appropriate measures according to the success or failure of the separation of cargo.

It is a figure which shows the example of an outline|summary structure of the cargo transportation system S. FIG. It is a figure which shows the schematic structural example of UAV1. It is a figure which shows an example of the external appearance of UAV1 provided with the support part 117. FIG. FIG. 3 is a diagram showing an example of the appearance of UAV 1 having a connecting portion 118. FIG. 3 is a diagram showing an example of functional blocks in a control unit 16; FIG. FIG. 10 is a diagram showing how departure control is performed while the UAV 1 is landing; FIG. 10 is a diagram showing how detachment control is performed while the UAV 1 is hovering; 4 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 in Embodiment 1. FIG. 10 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 in Embodiment 2. FIG. 14 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 in Embodiment 3. FIG. 14 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 in Embodiment 4. FIG.

An embodiment of the present invention will be described below with reference to the drawings. The following embodiments are embodiments in which the present invention is applied to a freight transport system that transports freight.

[ 1. Configuration and operation overview of cargo transportation system S ]
First, with reference to FIG. 1, the configuration and outline of operation of a freight transport system S according to this embodiment will be described. FIG. 1 is a diagram showing a schematic configuration example of a cargo transportation system S. As shown in FIG. As shown in FIG. 1, the cargo transport system S includes an unmanned aerial vehicle (hereinafter referred to as "UAV (Unmanned Aerial Vehicle)") 1 that flies in the atmosphere (air), and an operation management system (hereinafter referred to as "UTMS (UAV Traffic Management System) 2). UAV1 and UTMS2 can communicate with each other via communication network NW. The communication network NW is composed of, for example, the Internet, a mobile communication network and its radio base stations. Although one UAV 1 is shown in the example of FIG. 1, there may actually be more than one.

The UAV 1 can fly according to remote control by an operator from the ground or fly autonomously for cargo transportation (for example, delivery). UAV1 is also called drone or multi-copter. Examples of cargo include merchandise, deliveries, evacuation supplies, relief supplies, and the like. The UAV 1 detaches (in other words, cuts off) the cargo at the destination of the cargo (an example of the planned destination). The UAV 1 is managed by a GCS (Ground Control Station) and can be remotely controlled by an operator from the ground. The GCS is installed, for example, as an application in a control terminal connectable to the communication network NW. In this case, the operator is, for example, a person who operates the control terminal or a controller included in the control terminal. Alternatively, the GCS may be systematized by a server or the like. In this case, the operator is, for example, a system administrator or a controller provided with the server.

The UTMS 2 comprises one or more servers including a control server CS. UTMS2 manages the operation of UAV1. Operation management of UAV1 includes management of operation plan of UAV1, management of flight status of UAV1, and control of UAV1. The flight plan of the UAV 1 is a flight plan including a flight route (planned route) from the departure point (flight start point) of the UAV 1 to the cargo destination (route point or destination point). A flight path may be represented, for example, by latitude and longitude along the path, and may include a flight altitude. The flight status of UAV1 is managed based on the aircraft information of UAV1. The UAV1 aircraft information includes at least UAV1 position information. The position information of UAV1 indicates the current position of UAV1. The current position of UAV1 is the flight position of UAV1 during flight. The UAV1 aircraft information may include UAV1 speed information and the like. The speed information indicates the flight speed of UAV1.

[ 2. Configuration and function overview of UAV1 ]
Next, the configuration and functional overview of the UAV 1 will be described with reference to FIG. FIG. 2 is a diagram showing a schematic configuration example of the UAV1. As shown in FIG. 2, the UAV 1 includes a cargo loading section 11, a drive section 12, a positioning section 13, an imaging section 14, a wireless communication section 15, a control section 16, and the like. The control unit 16 is an example of a control device. Although not shown, the UAV 1 includes a rotor (propeller) that is a horizontal rotor, various sensors, a battery that supplies electric power to each part of the UAV 1, and the like. Various sensors include a triaxial acceleration sensor, a geomagnetic sensor, and the like. Also, the various sensors may include at least one of weight sensors, torque sensors, optical sensors, and ultrasonic sensors. Detection data detected by various sensors is output to the control unit 16 . Note that the UAV 1 may have a speaker for outputting sound.

The cargo loading section 11 carries one or more cargoes, and includes at least one of a support section 117 for supporting the loaded cargoes and a connection section 118 for connecting the cargoes. FIG. 3 is a diagram showing an example of the appearance of the UAV 1 provided with the support section 117. As shown in FIG. The support portion 117 includes a storage body 117a for storing the cargo C and a drive mechanism 117b for supporting or releasing the cargo C, as shown in FIG. The storage body 117a may be configured to be able to store a plurality of cargoes C. The drive mechanism 117b includes an actuator that converts a control signal (electrical signal) output from the controller 16 into mechanical motion. The actuator includes, for example, a motor and the like. Further, the container 117a includes a cargo receiver 117a1 for receiving the cargo C. As shown in FIG. The cargo receiver 117a1 is rotationally driven in the direction of the arrow by the drive mechanism 117b (that is, the cargo receiver 117a1 shifts from the closed state to the open state). The cargo C is released (dropped in this example) from the support portion 117 by such rotational driving (in other words, releasing operation). Such release operation is performed by driving the actuator in the drive mechanism 117b.

In addition, in the example of FIG. 3, since the side surface of the cargo C is not covered with the container 117a, the cargo C is visible from the outside of the container 117a. However, the container 117a may be configured in a box shape so as to cover the sides of the cargo C. As shown in FIG. That is, the storage body 117a may be configured as a storage box. In this case, the cargo C becomes invisible from the outside of the container 117a. Further, the support portion 117 may include a catcher (or an arm) capable of gripping the cargo C (or a ring attached to the cargo C) instead of the cargo receiver 117a1 in order to support the cargo C. The release operation in this case is also performed by driving the actuator in the drive mechanism 117b. Alternatively, the support section 117 may include a drive mechanism having an electromagnet capable of magnetically attracting a magnet attached to the cargo C instead of the drive mechanism 117b and the cargo receiver 117a1 to support the cargo C. The releasing operation in this case is performed by stopping the supply of electricity to the electromagnet.

FIG. 4 is a diagram showing an example of the appearance of the UAV 1 provided with the connecting portion 118. As shown in FIG. As shown in FIG. 4, the connecting portion 118 has a hook 118a for hooking a ring R attached to the cargo C, a wire 118b to which the cargo C is connected via the hook 118a, and feeds or winds the wire 118b. reel (winch) 118c. The reel 118 c includes a motor and is driven and controlled by the control section 16 . The hook 118a may hook rings R attached to a plurality of cargoes C. Hook 118a may also include a drive mechanism for automatically connecting or releasing cargo C. The operation of the drive mechanism (that is, the opening and closing operation of the hook 118a) is performed by driving the actuator in the drive mechanism. In addition, in order to connect the cargo C, the connection part 118 may include a catcher (or an arm) capable of gripping the cargo C itself (or the ring R attached to the cargo C) instead of the hook 118a. . Alternatively, the connecting portion 118 may include a drive mechanism having an electromagnet capable of magnetically attracting a magnet attached to the cargo C in place of the hook 118a in order to connect the cargo C. The releasing operation in this case is performed by stopping the supply of electricity to the electromagnet.

The drive unit 12 includes a motor, a rotating shaft, and the like. The drive unit 12 rotates a plurality of rotors by means of a motor, a rotating shaft, and the like that are driven according to control signals output from the control unit 16 . The positioning unit 13 includes a radio wave receiver, an altitude sensor (for example, an atmospheric pressure sensor and a TOF sensor), and the like. The positioning unit 13, for example, receives radio waves transmitted from satellites of GNSS (Global Navigation Satellite System) with a radio wave receiver, and detects the current position (latitude and longitude) of the UAV 1 in the horizontal direction based on the radio waves. The current position of UAV1 is the flight position of UAV1 during flight. Note that the current position of the UAV 1 in the horizontal direction may be corrected based on image data captured by the imaging unit 14 or radio waves transmitted from the wireless base station.

Furthermore, the positioning unit 13 may detect the current position (altitude) of the UAV 1 in the vertical direction using an altitude sensor. Position information indicating the current position detected by the positioning unit 13 is output to the control unit 16 . The imaging unit 14 includes a camera (RGB camera or infrared camera). The image capturing unit 14 continuously captures images of the real space within the angle of view of the camera. Image data captured by the imaging unit 14 is output to the control unit 16 . The wireless communication unit 15 is responsible for controlling communication performed via the communication network NW.

The control unit 16 includes a CPU (Central Processing Unit) which is a processor, a ROM (Read Only Memory), a RAM (Random Access Memory), a nonvolatile memory, and the like. FIG. 5 is a diagram showing an example of functional blocks in the control unit 16. As shown in FIG. The control unit 16 functions as a detachment control unit 16a, a load detection processing unit 16b, a detachment success/failure determination unit 16c, an aircraft control unit 16d, etc. as shown in FIG. do. Here, the detachment control section 16a is an example of a first control section. The body control unit 16d is an example of a second control unit. Note that the nonvolatile memory stores an aircraft ID for identifying the UAV 1 and address information for accessing the control server CS. The control unit 16 transmits the aircraft ID of the UAV 1 and aircraft information to the control server CS via the wireless communication unit 15 at regular intervals or irregular intervals.

The detachment control section 16a detaches the cargo C supported by the support section 117 or the cargo C connected by the connection section 118 from the UAV 1 while the UAV 1 is in flight or landed. release control. Here, the state in which UAV1 is in flight means the state in which UAV1 is moving in the air (i.e., moving horizontally, vertically, or diagonally), or the state in which UAV1 is hovering (i.e., UAV1 is stationary in the air). However, the state in which UAV1 is hovering is not limited to the state in which UAV1 is completely stationary in the air, and UAV1 may move slightly (that is, if UAV1 floats in the air without landing good).

Detachment control for detaching the cargo C from the UAV 1 is performed by the detachment control unit 16 a outputting a control signal to the support unit 117 or the connection unit 118 . Such detachment control includes, for example, control for causing the drive mechanism of the support portion 117 or the connection portion 118 to perform a releasing operation. Here, the control for causing the drive mechanism of the support section 117 to perform the release operation is desirably performed while the UAV 1 is on the ground, but may be performed while the UAV 1 is in flight. FIG. 6 is a diagram showing how departure control is performed while the UAV 1 is on the ground. In the example of FIG. 6, the cargo C is released toward the ground from the UAV 1 landing at the port (takeoff and landing facility) P installed on the ground of the destination. However, depending on the type of cargo (for example, an object that does not break even when dropped), cargo C may be dropped toward the ground from UAV 1 hovering above port P installed on the ground of the destination. In addition, when the drive mechanism having the electromagnet described above is included in the support portion 117, the detachment control is a control to stop the energization of the electromagnet while the UAV 1 is on the ground (that is, the drive mechanism having the electromagnet control for release operation).

On the other hand, the control for causing the drive mechanism of the connecting portion 118 to perform the releasing operation is performed while the UAV 1 is hovering. FIG. 7 is a diagram showing how detachment control is performed while the UAV 1 is hovering. In the example of FIG. 7, cargo C is lowered toward the ground by sending out wire 118b from UAV 1 hovering above port P installed on the ground of the destination. It should be noted that the control to cause the drive mechanism of the connecting portion 118 to perform the releasing operation may be performed while the UAV 1 is in the landing state. In the example of FIG. 7, when the cargo C is manually detached from the hook 118a, the detachment control described above is a control to send out the wire 118b to the reel 118c of the connecting portion 118 (that is, to lower the cargo C). can also Further, when the drive mechanism having the electromagnet described above is included in the connecting portion 118, the above-described detachment control is, for example, a control to stop the energization of the electromagnet while the cargo C has landed on the port P.

The load detection processing unit 16b detects a mechanical load applied to the support portion 117 or the connection portion 118 (in other words, a dynamic load acting on the support portion 117 or the connection portion 118) after the above-described separation control is performed. load detection processing. For example, the load detection processing unit 16b performs the load detection processing based on the weight data detected by the weight sensor provided in the UAV 1, thereby more easily detecting the mechanical load applied to the support unit 117 or the connection unit 118. can do. In this case the mechanical load is expressed in weight. A weight sensor is attached to the UAV 1 at a position where the weight of the cargo C can be detected. The above load detection process can be executed in either the state in which the UAV 1 is moving in the air or the state in which the UAV 1 is hovering. can detect the above weight data more accurately.

In the example of FIG. 3, the weight sensor WS1 is attached to the top of the container 117a. In this case, the load detection processing unit 16b detects the load for detecting the mechanical load applied to the support part 117 based on the weight data indicating the weight of the support part 117 (container 117a) detected by the weight sensor WS1. Perform detection processing. Thereby, the detection accuracy of the mechanical load applied to the support portion 117 can be improved. For example, when the cargo C is released from the support portion 117, the weight of the container 117a does not include the weight of the cargo C, so the detected weight is small (that is, the mechanical load is light). On the other hand, when the cargo C is not released from the support portion 117, the weight of the container 117a includes the weight of the cargo C, so the detected weight increases. The case where the cargo C is not released from the support portion 117 includes, for example, the case where the cargo C is not completely released from the support portion 117 because it is caught in the container 117a.

The weight sensor WS1 may be attached to the cargo receiver 117a1 so that only the weight of the cargo C can be detected when the cargo receiver 117a1 is closed. In this case, when the cargo receiver 117a1 is opened, the weight of the cargo C is no longer detected (that is, the pressure from the cargo C disappears), so it is presumed that the cargo C has been released. However, in this case, if the cargo C is caught in the storage body 117a, the weight of the cargo C will not be detected even though the cargo C has not been released (that is, the cargo C will be mistaken for being released). Presumed). Therefore, as shown in FIG. 3, when the weight sensor WS1 is attached to the upper portion of the storage body 117a, the detection accuracy of the mechanical load applied to the entire support portion 117 can be improved.

On the other hand, in the example of FIG. 4, the weight sensor WS2 is attached to the top of the reel 118c. In this case, the load detection processing unit 16b performs load detection processing for detecting the mechanical load applied to the connection part 118 based on the weight data indicating the weight of the connection part 118 detected by the weight sensor WS2. Thereby, the detection accuracy of the mechanical load applied to the connecting portion 118 can be improved. For example, if cargo C is released from connection 118, the weight of cargo C is not included in the weight of connection 118, so the sensed weight is less. On the other hand, if the cargo C has not been released from the joint 118, the weight of the cargo C is included in the weight of the joint 118, so the detected weight is increased. The case where the cargo C is not released from the connecting portion 118 includes, for example, the case where the cargo C is not completely released from the connecting portion 118 because it is caught on the wire 118b or the hook 118a.

Alternatively, the mechanical load may be detected without using a weight sensor. For example, the load detection processing unit 16b may detect the rotation speed of the rotor motor while the UAV 1 is hovering, and perform the load detection processing based on the detected rotation speed. In this case, the dynamic load is represented by the number of revolutions per unit time. For example, when the cargo C is released from the support 117 or the connection 118, the support 117 or the connection 118 becomes lighter, so the number of revolutions detected decreases. On the other hand, if the cargo C is not released from the support portion 117 or the connection portion 118, the support portion 117 or the connection portion 118 will be heavy, so the detected number of revolutions will be large.

As another example, the load detection processing unit 16b determines the rising speed of the UAV 1 based on the flight altitude (altitude difference) detected by the altitude sensor and the time while controlling the rotor motor so as to achieve a predetermined number of revolutions. can be calculated. Then, the load detection processing unit 16b may perform load detection processing for detecting the mechanical load applied to the support portion 117 or the connection portion 118 based on the calculated rising speed. In this case, the mechanical load applied to the support portion 117 or the connection portion 118 is represented by the rising speed. For example, when the cargo C is released from the support portion 117 or the connection portion 118, the support portion 117 or the connection portion 118 becomes lighter, so the calculated rising speed increases. On the other hand, if the cargo C is not released from the supporting portion 117 or the connecting portion 118, the supporting portion 117 or the connecting portion 118 becomes heavy, so the calculated rising speed becomes slow.

Alternatively, when the UAV 1 includes the connection unit 118, the load detection processing unit 16b may measure the torque of the motor of the reel 118c using a torque sensor. Then, the load detection processing unit 16b may perform load detection processing for detecting the mechanical load applied to the connection unit 118 based on the measured torque. In this case, the mechanical load applied to the connection 118 is represented by torque. For example, if cargo C is released from connection 118, connection 118 will be lighter and the measured torque will be lower. On the other hand, if the cargo C is not released from the connection 118, the connection 118 will be heavier and the measured torque will be higher. Alternatively, the load detection processing unit 16b may measure the tension of the wire 118b and perform load detection processing for detecting the mechanical load applied to the connection unit 118 based on the measured tension.

The detachment success/failure determination unit 16c determines whether the cargo C has been detached based on the dynamic load detected by the load detection processing unit 16b. As a result, the UAV 1 can be made to take appropriate measures according to the result of the determination of success or failure of the separation of the cargo C (that is, the status of success or failure of the separation). For example, it is determined whether the dynamic load is greater than a threshold while UAV1 is flying or UAV1 is landing. Here, when the mechanical load is represented by weight, the above threshold is, for example, the weight (known) of the support part 117 or the connection part 118 when the cargo C is not mounted while the UAV 1 is hovering + preset to the margin. Alternatively, when the dynamic load is represented by the number of rotations, the threshold is the number of rotations of the motor when the cargo C is not loaded while the UAV 1 is hovering (in other words, the number of rotations of the motor when the cargo C is not loaded). The number of rotations of the motor at which the hovering state of the UAV 1 is maintained in the case) + margin is preset.

Then, if the dynamic load is not greater than the threshold value (less than the threshold value), it is determined that the separation of the cargo C has succeeded. On the other hand, if the dynamic load is greater than the threshold, it is determined that the separation of cargo C has failed. Alternatively, when the dynamic load is represented by the rising speed, the threshold value is set in advance to the rising speed (average value) when the cargo C is not loaded. In this case, if the dynamic load is not greater than the threshold value (that is, the rising speed is slow), it is determined that the separation of cargo C has failed. On the other hand, if the dynamic load is greater than the threshold, it is determined that cargo C has successfully released.

By the way, the success or failure of the detachment of the cargo C can be determined by using image data captured by a camera. It is difficult to determine the success or failure of the detachment of the cargo C using the image data captured by the camera. In addition, if there is a blind spot where the cargo C cannot be captured depending on the mounting position of the camera, it is difficult to determine the success or failure of the detachment of the cargo C using the image data captured by the camera (this problem is particularly It becomes conspicuous when multiple cargoes C are loaded). On the other hand, by using the dynamic load detected by the load detection processing section 16b, these problems can be solved and the success or failure of the detachment of the cargo C can be accurately determined.

The fuselage control unit 16d controls the fuselage of the UAV 1 using the position information acquired from the positioning unit 13, the image data acquired from the imaging unit 14, the detection data acquired from various sensors, and the flight plan information indicating the flight plan. control. In the airframe control, for example, control of the number of rotations of the rotor motor, and control of the position, attitude and traveling direction of the UAV 1 are performed. The aircraft control of the UAV1 includes takeoff control of the UAV1, movement control of the UAV1, hovering control of the UAV1, landing control of the UAV1, and the like. Here, the take-off control of the UAV 1 includes control not to take off the UAV 1 depending on the situation. Note that the flight plan information is acquired from, for example, GCS or UTMS2. The flight plan information includes location information of the destination of cargo C. The body control unit 16d can remotely control or autonomously fly (move) the UAV 1 to the destination of the cargo C according to the position information of the destination. The autonomous flight of the UAV 1 is not limited to autonomous flight in which the control unit 16 provided in the UAV 1 performs movement control. Autonomous flight is also included.

Further, the body control unit 16d performs different controls according to the dynamic load regarding the movement of the UAV 1 after the load detection processing unit 16b detects the dynamic load. For example, if the load detection process is performed while the UAV 1 is landing, the airframe control unit 16d causes the UAV 1 to take off or restricts the takeoff of the UAV 1 depending on the magnitude of the dynamic load. For example, the machine body control unit 16d presets the numerical range of the dynamic load. Then, when the dynamic load detected by the load detection process falls within the set numerical range, the airframe control unit 16d causes the UAV 1 to take off (or, in this case, restricts the takeoff of the UAV 1). good).

Further, when the success/failure determination of the separation of the cargo C is performed while the UAV 1 is on the ground, the airframe control unit 16d determines whether the movement of the UAV 1 after the load detection process has been performed depends on the result of the success/failure determination. different controls depending on the For example, when it is determined that the cargo C has successfully departed, the body control unit 16d performs control to take off the UAV 1 (takeoff control of the UAV 1). This allows the UAV 1 to take off safely. On the other hand, when it is determined that the separation of the cargo C has failed, the body control unit 16d performs control to restrict takeoff of the UAV 1 (for example, control to stop the rotor motor). Thereby, the safety of UAV1 can be secured.

Further, when the above-described load detection processing is performed while the UAV 1 is in flight, the body control unit 16d selects the UAV 1 to move to the next planned destination (for example, the next transport destination, or return destination), hover UAV1 in the air, or land UAV1. For example, the body control unit 16d presets the numerical range of the dynamic load in a plurality of stages (for example, sets different first to third numerical ranges). Then, the body control unit 16d directs the UAV 1 to the next planned destination when the dynamic load detected by the load detection process falls within the first numerical range, and when it falls within the second numerical range, Hover UAV1 in the air and land UAV1 if it comes within the third numerical range.

Further, when the success/failure determination of the departure of the cargo C is performed while the UAV 1 is in flight, the airframe control unit 16d determines whether the movement of the UAV 1 after the load detection process has been performed depends on the result of the success/failure determination. different controls depending on the For example, when it is determined that the cargo C has successfully separated, the body control unit 16d performs control (movement control of the UAV 1) to direct the UAV 1 to the next planned destination. As a result, the UAV 1 can be safely directed to the next planned destination. On the other hand, when it is determined that the cargo C has failed to leave, the airframe control unit 16d performs control to hover the UAV 1 in the air (UAV 1 hovering control) or control to land the UAV 1 (UAV 1 landing control). I do. The safety of UAV1 can be ensured by hovering UAV1. Also, by landing the UAV 1, it is possible to prevent the UAV 1 from moving in an unstable state.

Note that when it is determined that the separation of the cargo C has failed, the body control unit 16d may determine whether the UAV 1 can land safely. Then, when the body control unit 16d determines that the UAV 1 can land safely, the aircraft control unit 16d causes the UAV 1 to land. This allows the UAV 1 to take off more safely. Whether or not the UAV 1 can land safely may be determined, for example, based on detection data detected by an optical sensor such as a camera. As a result, it is possible to improve the accuracy of determining whether the UAV 1 can land safely. Note that the detection data detected by the optical sensor may be image data.

In the examples of FIGS. 3 and 4, the optical sensor OS is attached to the leg 101 of the UAV1. In this case, if the body control unit 16d can determine that the cargo C does not protrude below the lower end of the leg 101 by analyzing the detection data detected by the optical sensor OS, the UAV 1 can land safely. I judge. Alternatively, whether or not the UAV 1 can land safely may be determined based on the winding amount of the wire 118b. As a result, it is possible to improve the accuracy of determining whether the UAV 1 can land safely. In this case, if it can be determined from the winding amount that the cargo C does not protrude below the lower ends of the legs 101, the body control unit 16d determines that the UAV 1 can land safely. On the other hand, when the body control unit 16d determines that the UAV 1 cannot land safely, it keeps the UAV 1 hovering.

[ 3. Operation of UAV1 ]
Next, the operation of the UAV 1 will be described separately for Examples 1 to 4. It should be noted that the operation described below is the operation after the cargo C is loaded on the UAV 1 at the departure point or the transit point and the UAV 1 takes off.

(Example 1)
First, with reference to FIG. 8, Example 1 of the operation of the UAV 1 will be described. FIG. 8 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 according to the first embodiment. Example 1 is an example in which the detachment control is performed while the UAV 1 having the support part 117 is in flight. In FIG. 8, after movement control of the UAV 1 toward the destination of the cargo C is started (step S1), the control unit 16 determines whether the UAV 1 has arrived at the destination of the cargo C (step S2). ).

When the control unit 16 determines that the cargo C has arrived at the transportation destination (step S2: YES), the control unit 16 performs detachment control for detaching the cargo C from the UAV 1 while the UAV 1 is moving (step S3). ). As a result, if there is no particular abnormality, the cargo C is dropped onto the port P installed at the transportation destination, for example. It should be noted that the detachment control may be performed while the UAV 1 is hovering.

Next, the control unit 16 performs hovering control of the UAV 1 (step S4). As a result, while the UAV 1 is hovering, the control section 16 performs load detection processing for detecting the mechanical load applied to the support section 117 (step S5). For example, load detection processing is performed by the load detection processing unit 16b based on the detected weight data or the number of rotations of the motor as described above.

Next, while the UAV 1 is hovering, the control unit 16 causes the separation success/failure determination unit 16c to determine whether the separation of the cargo C has been successful based on the dynamic load detected in step S5 (step S6).

Then, when the dynamic load detected in step S5 is equal to or less than the threshold value, the control unit 16 determines that the separation of the cargo C has succeeded (step S6: success), and determines the next planned destination (for example, the next Movement control of the UAV 1 is performed toward the transport destination or the return destination (step S7).

On the other hand, when the dynamic load detected in step S5 is greater than the threshold value (that is, when an abnormal load is applied to the support section 117), the control section 16 determines that the detachment of the cargo C has failed (step S6: Failed), go to step S8.

In step S8, the control unit 16 performs a withdrawal abnormality notification process. In the withdrawal abnormality notification process, a sound indicating the withdrawal abnormality is output from the speaker. In addition, in the separation abnormality notification process, an e-mail indicating the separation abnormality may be sent to the e-mail address of the mobile terminal possessed by the staff of the port P installed at the destination of the cargo C. As a result, the port P staff can be quickly notified of the departure abnormality.

For example, if the cargo C is caught on some part of the support part 117, the staff notified of the separation abnormality can appropriately respond. Since there is a possibility that the UAV 1 will occupy the port P until the abnormality is restored, a message indicating a departure abnormality may be sent to the control server CS together with the aircraft ID and aircraft information of the UAV 1 in the departure abnormality notification process. As a result, the control server CS can control the port P so that other UAVs 1 do not use it.

Next, the control unit 16 determines whether the UAV 1 can land safely based on the detection data detected by the optical sensor OS, for example (step S9). For example, when it can be determined that the cargo C does not protrude below the lower end of the leg 101, it is determined that the UAV 1 can land safely. Also, if the legs 101 of the UAV 1 are sufficiently long compared to the vertical length of the cargo C, the UAV 1 can land safely even if the cargo C is caught on some part of the support 117. can be determined.

When the controller 16 determines that the UAV 1 can land safely (step S9: YES), the controller 16 performs landing control of the UAV 1 (step S10). As a result, when the UAV 1 lands at the port P, the staff at the port P can remove the cargo C from being caught and retrieve the cargo C.

On the other hand, when the control unit 16 determines that the UAV 1 cannot land safely (step S9: NO), it performs control to maintain hovering (step S11). After that, the control unit 16 causes the UAV 1 to return to the starting point or waypoint.

(Example 2)
Next, Example 2 of the operation of the UAV 1 will be described with reference to FIG. FIG. 9 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 according to the second embodiment. A second embodiment is an embodiment in which the detachment control is performed while the UAV 1 having the support part 117 is on the ground. The processing of steps S21 and S22 in FIG. 9 is the same as the processing of steps S1 and S2 in FIG.

When the control unit 16 determines that the cargo C has arrived at the transportation destination (step S22: YES), the control unit 16 performs landing control of the UAV 1 (step S23). As a result, after the UAV 1 lands at the port P, the control unit 16 performs detachment control for detaching the cargo C from the UAV 1 (step S24). As a result, if there is no particular abnormality, the cargo C is released onto the port P installed at the transportation destination, for example.

Next, the control unit 16 performs takeoff control of the UAV 1 (step S25). Next, when the control unit 16 determines that the UAV 1 has reached a predetermined altitude, the control unit 16 performs hovering control of the UAV 1 (step S26). Next, the control unit 16 performs load detection processing for detecting the mechanical load applied to the support unit 117 while the UAV 1 is hovering (step S27). The processing of steps S28 to S33 in FIG. 9 is the same as the processing of steps S6 to S11 in FIG.

(Example 3)
Next, with reference to FIG. 10, Example 3 of the operation of the UAV 1 will be described. FIG. 10 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 according to the third embodiment. Example 3 is an example in which the detachment control is performed while the UAV 1 having the support part 117 is on the ground. The processing of steps S41 to S44 in FIG. 10 is the same as the processing of steps S21 to S24 in FIG.

Next, the control unit 16 performs load detection processing for detecting the mechanical load applied to the support unit 117 while the UAV 1 is on land (step S45). Next, while the UAV 1 is on land, the control unit 16 determines whether or not the cargo C has been released based on the dynamic load detected in step S45 (step S46).

Then, when the dynamic load detected in step S45 is equal to or less than the threshold value, the control unit 16 determines that the separation of the cargo C has succeeded (step S46: success), and performs takeoff control of the UAV 1 (step S47). . Next, the control unit 16 controls the movement of the UAV 1 toward the next planned destination (for example, the next transportation destination or return destination) (step S48).

On the other hand, when the mechanical load detected in step S45 is greater than the threshold value, the control unit 16 determines that the separation of the cargo C has failed (step S46: failure), and performs the separation abnormality notification process as described above ( step S49). Next, the control unit 16 restricts takeoff of the UAV 1 (step S50). As a result, the UAV 1 remains landed at the port P, and the staff at the port P can remove the cargo C from being caught and retrieve the cargo C.

(Example 4)
Next, Example 4 of the operation of the UAV 1 will be described with reference to FIG. FIG. 11 is a flow chart showing an example of processing of the control unit 16 of the UAV 1 according to the fourth embodiment. A fourth embodiment is an embodiment in which the detachment control is performed while the UAV 1 having the connecting portion 118 is in flight. The processing of steps S61 and S62 in FIG. 11 is the same as the processing of steps S1 and S2 in FIG.

When determining that the cargo C has arrived at the destination (step S62: YES), the control unit 16 performs hovering control of the UAV 1 at a predetermined altitude (step S63). As a result, while the UAV 1 is hovering, the control unit 16 controls sending out the wire 118b (step S64). Thereby, the cargo C connected to the wire 118b via the hook 118a, for example, is lowered.

Next, when the cargo C reaches the port P (for example, based on the amount of wire 118b sent), the control unit 16 performs detachment control to detach the cargo C from the UAV 1 (step S65). For example, a release operation of the drive mechanism of the hook 118a is performed. Thereby, if there is no particular abnormality, the cargo C is released from the hook 118a, for example.

Next, the control unit 16 performs winding control of the wire 118b (step S66). Next, while the UAV 1 is hovering, the control unit 16 performs load detection processing for detecting the mechanical load applied to the connection unit 118 (step S67). Here, the control unit 16 may perform the load detection process after increasing the altitude of the UAV 1 (for example, by several meters) before performing the winding control in step S66. The processing of steps S68-S70 in FIG. 11 is the same as the processing of steps S6-S8 in FIG.

Next, the control unit 16 determines whether the UAV 1 can land safely based on, for example, the winding amount of the wire 118b (step S71). If it can be determined from the winding amount of the wire 118b that the cargo C does not protrude below the lower end of the leg 101, it is determined that the UAV 1 can land safely.

When the controller 16 determines that the UAV 1 can land safely (step S71: YES), the controller 16 performs landing control of the UAV 1 (step S72). On the other hand, when the control unit 16 determines that the UAV 1 cannot land safely (step S71: NO), it performs control to maintain hovering (step S73).

In the first to fourth embodiments described above, it is configured to determine the success or failure of the separation of the cargo C based on the detected dynamic load. Instead, the control of the UAV 1 (for example, the control after step S7 shown in FIG. 8) may be performed according to the dynamic load.

As described above, according to the above-described embodiment, separation control is performed to separate the cargo supported by the support portion 117 of the UAV 1 or connected by the connection portion 118 from the UAV 1. A load detection process is performed to detect the dynamic load applied to the unit 118, and the movement of the UAV 1 after the detection of the dynamic load is controlled differently according to the dynamic load. Since the dynamic load detected by the load detection process reflects the success or failure of the separation of the cargo, the UAV 1 can be made to take appropriate measures according to the success or failure of the separation of the cargo.

(Application example)
In the above-described embodiment, the control unit 16 of the UAV 1 may perform release operation detection processing for detecting release operation of the drive mechanism of the support unit 117 or the connection unit 118 before performing the load detection processing. That is, the control unit 16 performs the load detection process after the release operation of the drive mechanism is detected. For example, when an actuator is included in the drive mechanism of the support portion 117 or the connection portion 118, the release operation of the drive mechanism can be detected by detecting the state (rotational position, load, etc.) of the motor in the actuator. On the other hand, if the drive mechanism includes an electromagnet, the release action of the drive mechanism is to detect whether the electromagnet is energized or to detect the magnetic force generated by the electromagnet. can be detected by Alternatively, the release operation of the drive mechanism may be detected on condition that a control signal is output from the detachment control section 16a to the support section 117 or the connection section 118, for example. According to such an application example, whether the drive mechanism of the support portion 117 or the connection portion 118 is malfunctioning (for example, there is a problem with the actuator or the electromagnet) due to the separate execution of the release motion detection process, Alternatively, it is possible to isolate an abnormality as to whether the cargo is not released (for example, caught) even though the drive mechanism operates normally.

The above-described embodiment is one embodiment of the present invention, and the present invention is not limited to the above-described embodiment. may be used, and that case is also included in the technical scope of the present invention. In the above embodiment, the UAV
1 control unit 16 serves as a first control unit that performs detachment control, a load detection unit that performs load detection processing for detecting the dynamic load, and a second control unit that performs different control according to the dynamic load, etc. Although a functioning case has been described as an example, the control server CS may include a first control section, a load detection section, a second control section, and the like as control devices. In this case, the control server CS appropriately acquires necessary information from the UAV 1 and performs detachment control for detaching the cargo supported by the support portion 117 of the UAV 1 or connected by the connection portion 118 from the UAV 1. After that, A load detection process is performed to detect the dynamic load applied to the support part 117 or the connection part 118, and different control is performed according to the dynamic load regarding the movement of the UAV 1 after the detection of the dynamic load. conduct. In this case, the departure control is performed by transmitting a departure control command from the control server CS to the UAV1 (or GCS). Further, different control depending on the dynamic load is performed by transmitting a control command according to the dynamic load from the control server CS to the UAV1 (or GCS). Further, in this case, the control server CS determines whether the cargo has been released based on the detected dynamic load, and regarding the movement of the UAV 1 after the load detection process is performed, may be controlled differently. Further, in the above embodiment, the case where the present invention is applied to UAV 1 has been described as an example, but the present invention is applied to a manned aircraft that can fly even if there is no operator (pilot) in the aircraft. It is also applicable to

1 UAVs
2 UTMS
11 Cargo loading unit 12 Driving unit 13 Positioning unit 14 Imaging unit 15 Wireless communication unit 16 Control unit 16a Detachment control unit 16b Load detection processing unit 16c Detachment success/failure determination unit 16d Aircraft control unit CS Control server S Cargo transportation system

Claims (6)

A control method performed by a system comprising an aircraft comprising a connection for connecting cargo, the connection including a mechanism for connecting or releasing said cargo, comprising:
a first control step of performing detachment control for detaching the cargo connected by the connecting portion from the aircraft, the detaching control causing the mechanism of the connecting portion to perform a release operation;
a release motion detection step of performing a release motion detection process for detecting a release motion of the mechanism;
a load detection step of performing a load detection process for detecting a mechanical load applied to the connecting portion after the release action of the mechanism is detected by the release action detection process;
a second control step of performing different control according to the dynamic load with respect to movement of the aircraft after the dynamic load is detected;
A control method comprising: the mechanism includes an actuator,
2. The control method according to claim 1, wherein the releasing operation is performed by driving the actuator. the mechanism includes an electromagnet,
2. The control method according to claim 1, wherein said releasing operation is performed by stopping power supply to said electromagnet. The connecting portion includes a wire to which the cargo is connected and a reel for feeding or winding the wire,
The control method is
a first determination step of determining success or failure of detachment of the cargo based on the dynamic load while the aircraft is in flight;
a second determination step of determining whether or not the aircraft can land safely based on the winding amount of the wire when the first determination step determines that the separation of the cargo has failed;
2. The control method according to claim 1, wherein when the second determination step determines that the aircraft can land safely, the second control step controls the landing of the aircraft. . An aircraft comprising a connection for connecting cargo, the connection including a mechanism for connecting or releasing said cargo,
a first control unit that performs detachment control for detaching the cargo connected by the connection part from the aircraft, the detachment control causing the mechanism of the connection part to perform a release operation;
a release motion detection unit that performs a release motion detection process for detecting a release motion of the mechanism;
a load detection unit that performs a load detection process for detecting a mechanical load applied to the connecting part after the release action of the mechanism is detected by the release action detection process;
a second control unit that performs different controls according to the dynamic load with respect to movement of the aircraft after the dynamic load is detected;
An aircraft comprising: 1. A control device for controlling an aircraft comprising a connection for connecting cargo, the connection including a mechanism for connecting or releasing said cargo,
a first control unit that performs detachment control for detaching the cargo connected by the connection part from the aircraft, the detachment control causing the mechanism of the connection part to perform a release operation;
a release motion detection unit that performs a release motion detection process for detecting a release motion of the mechanism;
a load detection unit that performs a load detection process for detecting a mechanical load applied to the connecting part after the release action of the mechanism is detected by the release action detection process;
a second control unit that performs different controls according to the dynamic load with respect to movement of the aircraft after the dynamic load is detected;
A control device comprising:

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