WO2019146577A1

WO2019146577A1 - Information processing device

Info

Publication number: WO2019146577A1
Application number: PCT/JP2019/001810
Authority: WO
Inventors: 山田　武史; 健甲本; 英利江原; 陽平大野; 雄一朗瀬川; 由紀子中村; 花野　真也
Original assignee: 株式会社Ｎｔｔドコモ
Priority date: 2018-01-26
Filing date: 2019-01-22
Publication date: 2019-08-01
Also published as: JPWO2019146577A1; JP7104071B2

Abstract

A degree-of-abnormality specification unit 202 specifies a degree of abnormality that corresponds to a detection value detected in a flight body 10. A parameter specification unit 203 specifies a derivation parameter for deriving a flight-incapable level that indicates the possibility that the flight body 10 will not be capable of flight at the degree of abnormality specified by the degree-of-abnormality specification unit 202. A flight control unit 204 establishes the flight-incapable level on the basis of the degree of abnormality specified by the degree-of-abnormality specification unit 202 and the derivation parameter specified by the parameter specification unit 203, and controls the operation of the flight body 10 in accordance with the flight-incapable level.

Description

Information processing device

TECHNICAL FIELD The present invention relates to a technique for suppressing danger by a flying object.

For example, with the spread of unmanned flying vehicles called drone, the establishment of technology for securing its safety is required. For example, Patent Document 1 discloses that, when the flying object is flying, any one of the battery's output voltage, output current, and output power becomes lower than a predetermined threshold, and the flying object elevation control is performed. ing.

JP, 2016-210404, A

Although the technology described in Patent Document 1 focuses only on so-called battery depletion in a flying object, factors other than the battery depletion may be considered as factors that make the flying object impossible to fly. Further, although the technology described in Patent Document 1 estimates whether or not there is an abnormality based on the output voltage, the output current, and the output power, whether or not these values correspond to an abnormality depends on It depends on the condition.

Therefore, it is an object of the present invention to provide a mechanism capable of more appropriately performing an operation for securing safety before the flight body becomes unflyable.

In order to solve the above problems, according to the present invention, there is provided an abnormality degree specifying unit which specifies an abnormality degree according to a detected value detected in a flying object, and the possibility that the aircraft can not fly at the specified abnormality degree. A parameter specifying unit for specifying a derived parameter for deriving a non-flyable level indicating a flight control, and a flight control for controlling the operation of the aircraft in accordance with the specified anomaly degree and the non-flyable level based on the derived parameter And an information processing apparatus characterized by comprising:

The flight control unit may control the operation of the aircraft when the non-flying level falls below a fluctuating safety standard.

The flight control unit may use the safety standard that varies in accordance with the attribute of the transported object transported by the aircraft.

The flight control unit may use the safety standard that changes according to an attribute of the ground corresponding to the airspace where the aircraft flies.

The flight control unit may use the safety standard that changes according to the attribute of the airspace where the aircraft flies.

The control by the flight control unit may include control of an operation related to the altitude reduction of the aircraft.

The control of the operation by the flight control unit may include the control of the operation related to the change of course of the flight object.

The control by the flight control unit may include control of an operation related to landing of the aircraft.

The control by the flight control unit may include control of an operation related to switching of the aircraft to an alternative aircraft.

According to the present invention, it is possible to more appropriately perform the operation for securing safety before the flight body becomes unflyable.

1 shows an example of the configuration of a flight control system 1. FIG. FIG. 2 is a view showing an example of the appearance of a flying object 10; It is a figure which shows the hardware constitutions of the flying body 10. As shown in FIG. FIG. 2 is a diagram showing a hardware configuration of a server device 20. FIG. 2 is a diagram showing an example of a functional configuration of a server device 20. It is a figure explaining the relationship between a flight impossible factor and flight control. It is a figure explaining the example of change of a safety standard. 5 is a flowchart showing an example of the operation of the server device 20.

1: Flight control system 10: Flight object 20: Server device 21: Processor 22: Memory 23: Storage 24: Communication device 25: Bus 200: Tracking unit 201: Acquisition unit 202: Abnormal Degree specification unit 203: Parameter specification unit 204: Flight control unit.

[Constitution]
FIG. 1 is a diagram showing an example of the configuration of a flight control system 1. The flight control system 1 is a system that controls the flight of the flying object 10. The flight control system 1 includes a plurality of aircraft 10 and a server device 20. The server device 20 is an information processing device that controls the flight of the flying object 10, and in this case, in particular, sets a limited flight area where the flight of the flying object 10 is limited. The flight restriction of the flying object 10 mentioned here typically assumes that the flying object 10 is not allowed to enter the flight restriction area. However, other than this, for example, limitation of the velocity or acceleration of the flying object 10 in the flight limited airspace, limitation of the direction change of the flying object 10 in the flight limitation airspace, limitation of the ascent or descent of the aircraft 10 in the flight limitation airspace, It may be any limitation on the flight of the flying object 10, such as the limitation of the staying period of the flying object 10 in the flight limitation airspace, and the weight limitation of the flying object 10 flying in the flight limitation airspace.

FIG. 2 is a view showing an example of the appearance of the flying object 10. The flying object 10 is, for example, a so-called drone, and includes a propeller 101, a drive device 102, and a battery 103.

The propeller 101 rotates about an axis. As the propeller 101 rotates, the flying object 10 flies. The driving device 102 powers and rotates the propeller 101. The drive device 102 includes, for example, a motor and a transmission mechanism that transmits the power of the motor to the propeller 101. The battery 103 supplies power to each part of the flying object 10 including the drive device 102.

FIG. 3 is a diagram showing the hardware configuration of the aircraft 10. The flying object 10 is physically configured as a computer device including a processor 11, a memory 12, a storage 13, a communication device 14, a positioning device 15, an imaging device 16, a beacon device 17, a bus 18, and the like. In the following description, the term "device" can be read as a circuit, a device, a unit, or the like.

The processor 11 operates an operating system, for example, to control the entire computer. The processor 11 may be configured by a central processing unit (CPU) including an interface with a peripheral device, a control device, an arithmetic device, a register, and the like.

Further, the processor 11 reads a program (program code), a software module or data from the storage 13 and / or the communication device 14 to the memory 12 and executes various processes in accordance with these. As a program, a program that causes a computer to execute at least a part of the operation of the flying object 10 is used. The various processes performed in the aircraft 10 may be performed by one processor 11 or may be performed simultaneously or sequentially by two or more processors 11. The processor 11 may be implemented by one or more chips. The program may be transmitted from the network via a telecommunication line.

The memory 12 is a computer readable recording medium, and includes, for example, at least one of a ROM (Read Only Memory), an EPROM (Erasable Programmable ROM), an EEPROM (Electrically Erasable Programmable ROM), and a RAM (Random Access Memory). It may be done. The memory 12 may be called a register, a cache, a main memory (main storage device) or the like. The memory 12 can store a program (program code), a software module, and the like that can be executed to implement the flight control method according to the embodiment of the present invention.

The storage 13 is a computer readable recording medium, and is, for example, an optical disk such as a CD-ROM (Compact Disc ROM), a hard disk drive, a flexible disk, a magnetooptical disk (for example, a compact disk, a digital versatile disk, Blu-ray A (registered trademark) disk, a smart card, a flash memory (for example, a card, a stick, a key drive), a floppy (registered trademark) disk, a magnetic strip, and the like may be used. The storage 13 may be called an auxiliary storage device.

The communication device 14 is hardware (transmission / reception device) for performing communication between computers via a wired and / or wireless network, and is also called, for example, a network device, a network controller, a network card, a communication module, or the like.

The positioning device 15 measures the three-dimensional position of the aircraft 10. The positioning device 15 is, for example, a GPS (Global Positioning System) receiver, and measures the current position of the aircraft 10 based on GPS signals received from a plurality of satellites.

The imaging device 16 captures an image around the flying object 10. The imaging device 16 is, for example, a camera, and captures an image by forming an image on an imaging element using an optical system. The imaging device 16 captures an image of a predetermined range in front of the aircraft 10, for example. However, the imaging direction of the imaging device 16 is not limited to the front of the aircraft 10, and may be above, below, or behind the aircraft 10. Further, for example, the imaging direction may be changed by rotating a pedestal supporting the imaging device 16.

The beacon device 17 transmits a beacon signal of a predetermined frequency, and also receives a beacon signal transmitted from another flying object 10. The reach of this beacon signal is a predetermined distance such as 100 m. The beacon signal includes aircraft identification information that identifies the aircraft 10 that transmits the beacon signal.

The sensor unit 19 detects detected values such as a sign of component failure of the flying object 10, abnormal noise in the flying object 10, and a remaining battery level of a battery. The indication of the component failure of the flying object 10 is grasped by monitoring the operating state such as the voltage value and the current value of each component, for example. These detected values are provided to the server device 20.

The devices such as the processor 11 and the memory 12 described above are connected by a bus 18 for communicating information. The bus 18 may be configured as a single bus or may be configured as different buses among the devices.

FIG. 4 is a diagram showing a hardware configuration of the server device 20. As shown in FIG. The server device 20 is physically configured as a computer device including a processor 21, a memory 22, a storage 23, a communication device 24, a bus 25 and the like. The processor 21, the memory 22, the storage 23, the communication device 24, and the bus 25 are similar to the processor 11, the memory 12, the storage 13, the communication device 14, and the bus 18 described above, and thus the description thereof is omitted.

FIG. 5 is a diagram showing an example of a functional configuration of the server device 20. As shown in FIG. Each function in the server device 20 causes the processor 21 to perform an operation by reading predetermined software (program) on hardware such as the processor 21 and the memory 22, thereby performing communication by the communication device 24, the memory 22, and the storage 23. This is realized by controlling the reading and / or writing of data in

In FIG. 5, the tracking unit 200 records the flying object identification information of the flying object 10 under control of the server device 20 and the flight status thereof. The flight status includes the position where the flying object 10 is flying and the date and time at that position. The tracking unit 200 records position information and date and time information notified from the aircraft 10. In addition, the tracking unit 200 determines whether the position information and the date and time information are within a previously planned flight plan, and records the determination result. Thereby, the difference between the plan and the result of the flight of the flying object 10 is specified as the detected value detected in the flying object 10.

The acquisition unit 201 has attributes of the ground (that is, the ground immediately below the airspace) in the airspace that is a candidate for the flight of the aircraft 10, the attributes of the airspace, the attributes of the cargo transported by the aircraft 10, and the sensor of the aircraft 10 The detection value detected by the unit 19 is acquired. These attributes are information indicating features of the ground and airspace, and are acquired by the acquiring unit 201 from each of the flying objects 10 or from a database stored by the acquiring unit 201. In this database, the population distribution on the ground and the position, number, density, and type of equipment or natural objects on the ground are stored as attributes of the ground, and each of the airspaces is a candidate for the flight object 10 to fly as the attribute of airspace. The position (latitude / longitude / altitude) and the number and attributes of flight vehicles scheduled to fly in the airspace, and information on the communication environment of the flight vehicle 10 in each airspace, the weather in each airspace, etc. are stored. These pieces of information are pre-specified or measured and stored in this database.

The abnormality degree specifying unit 202 specifies the degree of abnormality according to the detection value detected in the aircraft 10. How far is the aircraft 10 from normal levels from differences between the flight plan and the flight results, signs of component failure of the aircraft 10, abnormal noise in the aircraft 10, battery remaining amount of battery etc. The degree of abnormality (that is, the degree of abnormality) can be obtained according to a predetermined algorithm. The degree of abnormality means, for example, that 0 is a normal level and 10 is a maximum abnormal level, and the larger the value is, the more it deviates from the normal level (that is, it is abnormal).

The parameter specifying unit 203 specifies a parameter (hereinafter referred to as a derived parameter) for deriving the non-flyable level indicating the possibility that the flying object 10 can not fly in the abnormality degree specified by the abnormality degree specifying unit 202. . Here, the derived parameters include, for example, the production time of the flying object 10, the use start time or an elapsed period from the previous maintenance time, the weather at the time of flight, and the like. For example, based on the abnormal noise in the flying object 10, when the abnormality degree is "7", whether the flying object 10 is actually impossible to fly or not depends on the manufacturing time of the flying object 10, the use start time or the last maintenance time. It depends on the time elapsed from and the weather at the time of flight. For example, in the case where the degree of abnormality is "7", the possibility of being unable to fly is X1% if the time when the aircraft 10 is manufactured, the start time of use, or the elapsed time since the previous maintenance time is more than a threshold. If the duration of is less than the threshold, the probability of becoming unflyable is X2% (X2 <X1). In addition, when the elapsed period from the use start time is short (the so-called initial failure occurrence period in a failure rate curve called a bathtub curve), the possibility of becoming unflyable may be increased. In other words, in this period, it is not abnormal due to wear or aging, but it is often an abnormality due to initial failure, so even if the degree of abnormality is the same, the probability of being unable to fly is not possible after this period It becomes higher than the possibility of becoming. Also, for example, when the degree of abnormality is "7", the possibility of being incapable of flying is Y1% when the weather is "fine, wind speed 1 m or less", but the weather is "rain, wind speed 10 m or more" The possibility of becoming unflyable is Y2% (Y1 <Y2). As described above, the parameter specifying unit 203 stores the derived parameters for deriving the non-flyable level (for example, X1, X2, Y1, Y2% described above) from each abnormality degree, and specifies by the abnormality degree specifying unit 202. The derived parameters corresponding to the identified abnormality degree are identified.

The flight control unit 204 determines the non-flyable level based on the abnormality degree specified by the abnormality degree specifying unit 202 and the derived parameter specified by the parameter specifying unit 203, and the operation of the aircraft 10 according to the non-flyable level. Control. Specifically, the flight control unit 204 performs a predetermined calculation using the abnormality degree and the derived parameter to calculate the above non-flyable level such as X1, X2, Y1, Y2%, and the non-flyable level is safe. When the level is lower than the standard, the flying object 10 is controlled to perform an action according to the factor of the level of the non-flight being lower than the safety standard. This safety standard is an attribute of a transported object transported by the aircraft (referred to as a transported object attribute), an attribute of the ground corresponding to an airspace where the aircraft flies (grounded attribute), or an attribute of an airspace where the aircraft flies It changes according to the attribute).

The ground attributes relate to, for example, the density of the population on the ground of the airspace where the aircraft 10 is a candidate to fly, and the number, density or type of equipment or natural objects on the ground. The population includes cases that change with time. The equipment is, for example, a building (including the presence of a roof), a road, a field, a drone landing equipment, a vehicle, etc., including those fixed on the ground and those moving on the ground. Equipment includes time-dependent cases. Natural products include mountains, rivers, seas, lakes, etc.

The airspace attribute may, for example, be the altitude of the airspace, the communication environment of the airborne vehicle 10 in the airspace, the number or density of the airborne vehicles 10 in the airspace, or an airspace allocated exclusively for the particular airborne vehicle 10 It relates to whether or not to assign to a plurality of aircrafts 10 to be shared.

The transported item attribute is information indicating the features of the transported object transported by the flying object 10, and includes, for example, its weight, fragility, and importance.

FIG. 6 is a view for explaining a variation example of the safety standard. For example, when the transported item is a broken item, the safety standard is Th1, and when it is not a broken item, the safety standard is Th2. However, it is Th1> Th2. That is, in the case where the transported object is a broken object, it is likely that the safety of the flying object 10 is needed more. Also, the safety standard is Th3 when there are many people on the ground attribute (for example, the population density is above the threshold), and the safety standard is Th4 when the population is low (for example, the population density is less than the threshold) . However, Th3> Th4. That is, as the population is larger, it is likely to be necessary to ensure the safety of the flying object 10. At high altitude (if altitude is above threshold) as airspace attribute, the safety standard is Th5, and at low altitude (e.g. altitude is below threshold), the safety standard is Th6. However, it is Th5> Th6. That is, as the altitude of the flying object 10 is higher, it is likely to be necessary to ensure the safety of the flying object 10.

FIG. 7 is a diagram for explaining the relationship between the non-flying factor and the flight control. The control by the flight control unit 204 includes instructions such as the flight date, flight path, flight speed, etc. of the flying object 10. As shown in FIG. 7, when the factor below the safety standard is a factor related to the failure of the flying object, the control by the flight control unit 204 includes the control of the operation related to the altitude reduction of the flying object. The factors relating to the failure of the flying object include differences in flight plans and results, indications of component failure of the flying object 10, and abnormal noise in the flying object 10. If the factor falling below the safety standard is a factor relating to the collision of the flying object, the control of the operation by the flight control unit 204 includes the control of the operation relating to the turning of the flying object. As factors related to the collision of the flying object, the number, attributes, communication state, etc. of other flying objects are to be detected. When the factor falling below the safety standard is a factor related to the power shortage of the aircraft, the control by the flight control unit 204 includes control of the operation regarding landing of the aircraft. The factors relating to the power shortage of the flying object include the battery remaining amount of the flying object 10 or the weather.

The reason why the control of the flying object 10 is different depending on the factor that the non-flyable level is lower than the safety standard is as follows. For example, even if there is a factor related to the failure of the flying object as a factor below the safety standard, if the flying object 10 can continue the flight, it becomes impossible to fly compared to the factor related to the power shortage (that is, the flying object 10 Is not likely to fall). Therefore, in such a case, rather than landing the flying object 10, it is preferred to lower the altitude of the flying object 10 to reduce, for example, the risk of crash and to fulfill the flight purpose of the flying object 10 Let In this way, appropriate motion control for the aircraft 10 is considered to be different depending on the factor below the safety standard. In addition, regarding factors related to the power shortage of the aircraft, multiple levels of safety standards are provided, and when the safety level falls below the first safety standard, operation control for the altitude reduction of the aircraft 10 is performed. The motion of the flying object 10 may be controlled stepwise, such as performing motion control relating to the landing of the flying object 10 when the safety level falls below the second lower safety standard.

[Operation]
Next, the operation of this embodiment will be described. In the following description, when the server device 20 is described as a subject of processing, specifically, the processor 21 is read by reading predetermined software (program) on hardware such as the processor 21 and the memory 22. Means that the process is executed by performing an operation and controlling communication by the communication device 24 and reading and / or writing of data in the memory 22 and the storage 23.

FIG. 8 is a flowchart showing an example of the operation of the server device 20. In the server device 20, the acquisition unit 201 acquires various attributes such as an article attribute, a ground attribute, and an airspace attribute for a certain flying object 10, and a detection for identifying a plurality of factors that make the flight object impossible to fly. The data (difference between flight plan and results, indication of parts failure of the flying object 10, abnormal noise in the flying object 10, number and attributes of other flying objects, remaining battery capacity of the flying object 10, weather, etc.) It acquires (step S11).

The abnormality degree specifying unit 202 specifies the degree of abnormality of the flying object 10 based on the detection value for specifying each factor (step S12).

The parameter specifying unit 203 specifies a derived parameter for deriving the non-flyable level at the identified abnormality degree (step S13).

The flight control unit 204 determines the non-flyable level based on the identified abnormality degree and the derived parameter, and compares the non-flyable level with the safety standard (step S14). Here, the safety standard to be compared with the non-flyable level is determined for each of the transported item attribute, the ground attribute, and the airspace attribute. For example, if the transported item is, for example, a broken item, the safety standard is Th1. If not, the safety standard is Th2. Also, the safety standard is Th3 when there are many people on the ground attribute (for example, the population density is above the threshold), and the safety standard is Th4 when the population is low (for example, the population density is less than the threshold) . At high altitude (if altitude is above threshold) as airspace attribute, the safety standard is Th5, and at low altitude (e.g. altitude is below threshold), the safety standard is Th6.

The flight control unit 204 compares the identified non-flyable level with the safety standard for each of the transported object attribute, ground attribute, and airspace attribute of the airframe 10, and if there is a non-flyable level below the safe standard. (Step S14: YES) As described with reference to FIG. 7, the flight control determined for the factor corresponding to the non-flyable level below the safety standard is performed (step S15). That is, when the factor below the safety standard is a factor related to the failure of the aircraft, the control by the flight control unit 204 includes the control of the operation related to the altitude reduction of the aircraft. In addition, when the factor below the safety standard is a factor related to the collision of the flying object, the control of the operation by the flight control unit 204 includes the control of the operation related to the turning of the flying object. In addition, when the factor below the safety standard is a factor related to the power shortage of the aircraft, the control by the flight control unit 204 includes control of the operation regarding the landing of the aircraft.

According to the embodiment described above, it is possible to more appropriately perform the operation for securing safety before the flying object 10 becomes unflyable.

[Modification]
The present invention is not limited to the embodiments described above. You may deform | transform the embodiment mentioned above as follows. Also, the following two or more modifications may be implemented in combination.

The control by the flight control unit 204 may include control of operations relating to switching of the aircraft 10 to an alternative aircraft. Specifically, the flight control unit 204 instructs the first flying object 10 in flight to land on the landing base, and for the second flying object 10 waiting at that base, It instructs to fly as a substitute for the first flying object 10.

In the embodiment, the server device 20 uses all of the transported object attribute, the ground attribute, and the airspace attribute, but at least one of the attributes may be used. Moreover, the position of the flying object 10 may be measured by the method which does not use GPS.

The block diagram used for the description of the said embodiment has shown the block of a functional unit. These functional blocks (components) are realized by any combination of hardware and / or software. Moreover, the implementation means of each functional block is not particularly limited. That is, each functional block may be realized by one physically and / or logically coupled device, or directly and / or indirectly two or more physically and / or logically separated devices. It may be connected by (for example, wired and / or wireless) and realized by the plurality of devices.
In addition, at least a part of the functions of the server device 20 may be implemented on the aircraft 10. Similarly, at least part of the functions of the aircraft 10 may be implemented on the server device 20.
In summary, in the information processing system according to the present invention, a step of specifying an abnormality degree according to a detected value detected in a flight object, and a flight showing a possibility that the aircraft can not fly at the specified abnormality degree. If the steps of identifying the derived parameter for deriving the impotence level and controlling the operation of the aircraft according to the identified abnormality degree and the impromptu level based on the derived parameter are performed. Good.

Each aspect / embodiment described in the present specification is LTE (Long Term Evolution), LTE-A (LTE-Advanced), SUPER 3G, IMT-Advanced, 4G, 5G, FRA (Future Radio Access), W-CDMA (Registered trademark), GSM (registered trademark), CDMA2000, UMB (Ultra Mobile Broadband), IEEE 802.11 (Wi-Fi), IEEE 802.16 (WiMAX), IEEE 802.20, UWB (Ultra-Wide Band), The present invention may be applied to a system utilizing Bluetooth (registered trademark), other appropriate systems, and / or an advanced next-generation system based on these.

As long as there is no contradiction, the processing procedure, sequence, flow chart, etc. of each aspect / embodiment described in this specification may be reversed. For example, for the methods described herein, elements of the various steps are presented in an exemplary order and are not limited to the particular order presented.
Each aspect / embodiment described in this specification may be used alone, may be used in combination, and may be switched and used along with execution. In addition, notification of predetermined information (for example, notification of "it is X") is not limited to what is explicitly performed, but is performed by implicit (for example, not notifying of the predetermined information) It is also good.

The terms "system" and "network" as used herein are used interchangeably.

The information or parameters described in the present specification may be represented by absolute values, may be represented by relative values from predetermined values, or may be represented by corresponding other information. For example, radio resources may be indexed.

The names used for the parameters described above are in no way limiting. In addition, the formulas etc. that use these parameters may differ from those explicitly disclosed herein. Since various channels (eg PUCCH, PDCCH etc.) and information elements (eg TPC etc.) can be identified by any suitable names, the various names assigned to these various channels and information elements can be Is not limited.

The terms "determining", "determining" as used herein may encompass a wide variety of operations. For example, “judgment” and “decision” may be judging, calculating, calculating, processing, processing, deriving, investigating, looking up (for example, a table) (Searching in a database or another data structure), ascertaining may be regarded as “decision” or “decision”. Also, "determination" and "determination" are receiving (e.g. receiving information), transmitting (e.g. transmitting information), input (input), output (output), access (Accessing) (for example, accessing data in a memory) may be regarded as "determined" or "determined". In addition, "determination" and "decision" are to be considered as "determination" and "determination" that they have resolved (resolving), selecting (selecting), choosing (choosing), establishing (establishing), etc. May be included. That is, "determination" "determination" may include considering that some action is "determination" "determination".

The present invention may be provided as a flight control method or an information processing method including the steps of processing performed in the flight control system 1 or the server device 20. Also, the present invention may be provided as a program executed on the airframe 10 or the server device 20. Such a program may be provided in the form of being recorded in a recording medium such as an optical disk, or may be provided in the form of being downloaded to a computer via a network such as the Internet and installed and made available. It is possible.

Software, instructions, etc. may be sent and received via a transmission medium. For example, software may use a wireline technology such as coaxial cable, fiber optic cable, twisted pair and digital subscriber line (DSL) and / or a website, server or other using wireless technology such as infrared, radio and microwave When transmitted from a remote source, these wired and / or wireless technologies are included within the definition of transmission medium.

The information, signals, etc. described herein may be represented using any of a variety of different techniques. For example, data, instructions, commands, information, signals, bits, symbols, chips etc that may be mentioned throughout the above description may be voltage, current, electromagnetic waves, magnetic fields or particles, optical fields or photons, or any of these May be represented by a combination of

The terms described herein and / or the terms necessary for the understanding of the present specification may be replaced with terms having the same or similar meanings. For example, the channels and / or symbols may be signals. Also, the signal may be a message. Also, the component carrier (CC) may be called a carrier frequency, a cell or the like.

Any reference to an element using the designation "first," "second," etc. as used herein does not generally limit the quantity or order of those elements. These designations may be used herein as a convenient way of distinguishing between two or more elements. Thus, reference to the first and second elements does not mean that only two elements can be taken there, or that in any way the first element must precede the second element.

The “means” in the configuration of each device described above may be replaced with a “unit”, a “circuit”, a “device” or the like.

Insofar as "including", "comprising" and variations thereof are used in the present specification or claims, these terms as well as the term "comprising" are inclusive. Intended to be Further, it is intended that the term "or" as used in the present specification or in the claims is not an exclusive OR.

Throughout the disclosure, for example, when articles are added by translation, such as a, an, and the in English, these articles are not clearly indicated by the context, unless the article clearly indicates otherwise. It shall contain several things.

Although the present invention has been described above in detail, it is apparent to those skilled in the art that the present invention is not limited to the embodiments described herein. The present invention can be embodied as modifications and alterations without departing from the spirit and scope of the present invention defined by the description of the claims. Accordingly, the description in the present specification is for the purpose of illustration and does not have any limiting meaning on the present invention.

Claims

An abnormality degree specifying unit which specifies an abnormality degree according to a detected value detected in the flying object;
A parameter specifying unit specifying a derived parameter for deriving a non-flyable level indicating a possibility that the aircraft can not fly at the specified anomaly degree;
An information processing apparatus comprising: a flight control unit configured to control an operation of the flying object in accordance with the specified abnormality degree and the non-flyable level based on the derived parameter.
The information processing apparatus according to claim 1, wherein the flight control unit controls an operation of the flight body when the non-flyable level falls below a fluctuating safety standard.
The information processing apparatus according to claim 2, wherein the flight control unit uses the safety standard that changes in accordance with an attribute of a transported object transported by the aircraft.
The information processing apparatus according to claim 2, wherein the flight control unit uses the safety standard that changes in accordance with an attribute of the ground corresponding to an airspace where the aircraft flies.
The information processing apparatus according to claim 2, wherein the flight control unit uses the safety standard that changes in accordance with an attribute of an airspace in which the aircraft flies.
The information processing apparatus according to any one of claims 1 to 5, wherein the control by the flight control unit includes control of an operation related to a decrease in altitude of the aircraft.
The information processing apparatus according to any one of claims 1 to 5, wherein the control of the operation by the flight control unit includes the control of an operation related to a change in course of the flying object.
The information processing apparatus according to any one of claims 1 to 5, wherein the control by the flight control unit includes control of an operation related to landing of the aircraft.
The information processing apparatus according to any one of claims 1 to 5, wherein the control by the flight control unit includes control of an operation related to switching to the alternative aircraft of the flight vehicle.