KR20160126783A - Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode - Google Patents

Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode Download PDF

Info

Publication number
KR20160126783A
KR20160126783A KR1020150058289A KR20150058289A KR20160126783A KR 20160126783 A KR20160126783 A KR 20160126783A KR 1020150058289 A KR1020150058289 A KR 1020150058289A KR 20150058289 A KR20150058289 A KR 20150058289A KR 20160126783 A KR20160126783 A KR 20160126783A
Authority
KR
South Korea
Prior art keywords
mission
air
scenario
equipment
aircraft
Prior art date
Application number
KR1020150058289A
Other languages
Korean (ko)
Other versions
KR101680699B1 (en
Inventor
이현구
김윤수
Original Assignee
국방과학연구소
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 국방과학연구소 filed Critical 국방과학연구소
Priority to KR1020150058289A priority Critical patent/KR101680699B1/en
Publication of KR20160126783A publication Critical patent/KR20160126783A/en
Application granted granted Critical
Publication of KR101680699B1 publication Critical patent/KR101680699B1/en

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B64C2201/141—

Abstract

The present invention relates to an air mission performance system supporting a self-operation mode, an air mission interlocking device, and an air mission performance method. The air mission performance system according to the present invention which performs a mission by using air mission equipment provided in an aircraft comprises: an air mission interlocking device which stores a mission scenario performed by air mission equipment in response to at least one among position information, time information, and situation information, and generates a control signal for controlling the air mission equipment in response to the mission scenario; and air mission equipment which performs an air mission in accordance with the control signal transmitted from the air mission interlocking device. Accordingly, it is possible to secure stability of air mission performance by employing a proper air mission equipment operation mode depending on a data link state between a ground center and an aircraft.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an air navigation system, an air navigation system, an airborne navigation system,

The present invention relates to an air mission performance system, an air mission interlock device, and a method of performing an air mission, and more particularly, to an air mission performance system for operating an air mission device mounted on an aircraft, An interlock device and a method for performing an air mission.

Unmanned Aerial Vehicle (Unmaned Aerial Vehicle) is a vehicle designed to perform various air missions without pilots. It is widely used for military purposes. In recent years, for unmanned aerial vehicles such as remote sensing, communication relay, environmental monitoring, The application range is gradually expanding.

Unmanned aerial vehicles perform their assigned tasks using the onboard air mission equipment. For example, an unmanned aerial vehicle for Electronic Warfare (EW) is equipped with various signal information such as Communication Intelligence (COMINT), Electronic Intelligence (ELINT), Instrument Information (Foreign) Intrumentation Signal Intelligence, FISINT).

According to the conventional air mission execution system, data is transmitted and received through the data link established between the ground control center and the aircraft to perform the air missions. At the ground control center, the operator sends the control command through the uplink to perform the mission of the air mission equipment, and the mission result is transmitted to the ground control center through the downlink to achieve the desired purpose Respectively.

However, such a conventional air mission performance system has the following problems. That is, when control of the ground control center is impossible, for example, when a data link is disconnected or communication through it is not smooth, control data can not be transmitted from the ground control center to the aircraft It is impossible to carry out the mission of the air mission equipment.

As described above, the prior art has a problem in that the stability of the air mission performance can not be guaranteed because the availability of the air mission depends on the state of the data link and the control ability through the ground control center. Especially, in a situation where the importance of real-time information such as a battlefield is increased, the risk of this can be further increased.

Therefore, there is a need for a plan to carry out air missions that can flexibly cope with situations in which transmission / reception via a data link is not possible.

The object of the present invention is to provide an air mission execution system, an air mission interlock device, and an air mission execution method capable of smoothly performing an air mission even when transmission / reception through a data link between a ground center and an aircraft is impossible have.

An air mission execution system according to an embodiment of the present invention is an air mission execution system that performs an aeronautical mission execution using an aeronautical mission equipment mounted on an airplane. The system includes at least one of position information, time information, An air mission interlocking device for correspondingly storing mission scenarios performed by the air mission equipment and generating control signals for controlling the air mission equipment in response to the mission scenarios; And an air mission device that performs an air mission in accordance with the control signal transmitted from the air mission interlock device.

According to the embodiment of the present invention, the mission scenario may be created including mission contents according to at least one of flight altitude, flight area, time, flight situation, and encounter situation, The mission execution frequency, the mission execution resolution, and the mission execution position for each mission equipment, the mission execution time, the mission execution period, the mission execution frequency, the mission execution resolution, and the mission execution position.

According to the embodiment of the present invention, the air mission interlocking device can determine whether the mission fulfillment condition is satisfied based on the GPS module mounted on the aircraft and the situation recognition module.

According to an embodiment of the present invention, the air mission interlocking device may include a self-operation mode for monitoring the data link state between the aircraft and the ground center, and controlling the air mission equipment according to the mission scenario in response to the data link state And a ground operating mode for controlling the air mission equipment according to a control command transmitted from the ground center.

The air mission interlocking apparatus according to an embodiment of the present invention includes a scenario storage unit for storing a mission scenario performed by an air mission device mounted on an aircraft corresponding to at least one of position information, time information, and situation information; And a mission equipment control unit for determining whether the mission scenario fulfills mission performance conditions and generating a control signal for controlling the air mission equipment in response to the mission scenario.

According to the embodiment of the present invention, the mission equipment control unit can determine whether the mission execution condition is satisfied based on the GPS module and the situation recognition module mounted on the aircraft.

According to an embodiment of the present invention, there is provided a method for controlling an aircraft mission system, comprising: a self-operation mode for monitoring a data link state between the aircraft and a ground center and controlling the air mission equipment according to the mission scenario in response to the data link state; And a result storage unit for storing the mission execution result information performed by the air mission equipment. The operation mode selection unit may be configured to select one of the ground operation modes for controlling the air mission equipment according to the control command.

A method of performing an air mission in accordance with an exemplary embodiment of the present invention includes performing a task using an air mission device mounted on an aircraft, the method comprising the steps of: (a) Loading the mission scenario file of the air mission equipment created corresponding to at least one of the information of the at least one of the information and the information; (b) determining whether the air mission interlocking device conforms to the execution condition of the mission scenario, and generating a control signal for controlling the air mission device in response to the content of the mission scenario; And (c) performing the air missions by the air mission equipment in response to the control signals.

According to an embodiment of the present invention, before the step (a), the air mission interlocking device may include a ground operation mode in which the air mission equipment is operated by the ground center according to an established data link state between the aircraft and the ground center And may activate a self-running mode of operating the air mission equipment in accordance with the mission scenario.

As described above, according to the present invention, it is possible to ensure the stability of the air mission performance by adopting the appropriate air mission device operation mode among the self-operation mode and the ground operation mode according to the data link state between the ground center and the airplane.

Brief Description of the Drawings Fig. 1 is a schematic configuration diagram of an air mission performance system according to an embodiment of the present invention; Fig.
2 is a block diagram of an air mission interlock according to an embodiment of the present invention;
3 is an example of a mission scenario file configuration; And
FIG. 4 is a flowchart illustrating a process in which an air mission is performed by the system of FIG. 1;

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings so that those skilled in the art can easily carry out the technical idea of the present invention. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. In order to clearly explain the present invention, parts not related to the description are omitted, and like parts are denoted by similar reference numerals throughout the specification.

The aeronautical tasks described in this specification are meant to cover the entire range of missions carried out on unmanned aircraft without pilots on board and include various missions such as surveillance, reconnaissance, information gathering, combat, deception, exploration, can do.

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

1 is a schematic block diagram of an air mission system 100 according to an embodiment of the present invention.

Referring to FIG. 1, the air mission system 100 includes an air mission device 10, and an air mission interlock device 30. As shown in FIG. 1, it is assumed that an aircraft performs a task of collecting Signal Intelligence (SIGINT).

The air mission equipment (10) is various equipment to be mounted on an aircraft in order to carry out an air mission, and the kind of specific equipment is determined according to the task to be performed. For example, when an aircraft performs a task of collecting Signal Intelligence (SIGINT), it collects Communications Intelligence (COMINT), Electronic Intelligence (ELINT), and Foreign Instrumentation Signals Intelligence (FISINT) Aircraft mission equipment may be installed. At this time, each air mission equipment 10 may include various devices. For example, the COMINT mission equipment can be composed of various devices such as a signal distribution device, a broadband search device, a direction detection device, and the like. On the other hand, when the aircraft performs the mission such as exploration / surveillance, the image equipment for acquiring various images may be mounted as the air mission equipment 10.

The air mission interlock device (30) stores a mission scenario executed by the air mission device (10) created corresponding to at least one of position information, time information, and situation information, And generates a control signal for controlling the equipment 10.

In addition, the air mission interlock device 30 may enable air mission to be performed not only through the self-operation mode of the air mission based on the mission scenario described above, but also through the ground operation mode associated with the ground center (GC). That is, the air mission interlock device 30 receives the uplink signal from the ground center GC via the data link DL to control the air mission device 10, and transmits the mission results to the ground center GC).

Hereinafter, the configuration of the air mission interlock device 30 will be described in more detail with reference to FIG.

2 is a block diagram of an air mission interlock device 30 in accordance with an embodiment of the present invention.

2, the air mission interlock device 30 includes a scenario storage unit 31, a mission equipment control unit 33, an operation mode selection unit 35, and a result storage unit 37.

A scenario storage unit (31) stores a mission scenario performed by the air mission equipment (10). Here, the mission scenario is a predetermined description of the specific mission performed by the air mission equipment 10 according to the position information of the flight position (altitude, area) of the aircraft, the status information such as the flight status, .

Mission scenarios can be classified into three categories: mission type, mission execution time, task execution frequency, task execution frequency, task execution resolution, And the position of the mission, and may be separately prepared for each type of aviation mission equipment 10 according to the type and characteristics of each equipment.

As an example of the scenario of signal information collection mission, it is assumed that the mission contents such as flight altitude, equipment performing collection by flight area, collection start / stop time, collection execution cycle, frequency range of mission execution, , And when the aircraft enters a specified altitude or zone location, it may be able to gather signal information according to defined mission content. Hereinafter, the configuration of the mission scenario will be described in more detail.

3 is an example of a mission scenario file configuration related to a signal information collection mission.

Referring to FIG. 3, the mission scenario file may be hierarchically configured for each air mission device 10, including mission execution conditions and mission contents.

Mission Scenarios for Signal Information Gathering Missions Scenario files can consist of single or multiple location tasks and time task assignments for each COMINT, ELINT, and FISINT air mission equipment (10).

Here, the position task is a task condition of an aircraft performing the information gathering mission and a task task to be performed at the corresponding position, and it means position information such as altitude, latitude and longitude to perform the mission and specific task contents to be performed, May be defined as a time condition such as a time to start an information gathering mission after the commencement of operation and a mission task to be performed at the relevant time. At this time, the message in the task assignment field can be created in the same manner as the message structure of the control command transmitted from the ground center (GC) to the data link.

On the other hand, the composition of the mission scenario may be made not only by the example given above, but also including the individual mission conditions and mission contents according to the given air mission and the characteristics of the air mission equipment (10).

Then, the mission equipment control unit 33 judges whether or not the mission condition fulfillment condition of the mission scenario is generated. If the condition is satisfied, the mission equipment control unit 33 generates a control signal for controlling the air mission equipment 10 in response to the mission scenario do.

At this time, the mission equipment controller 33 may be interfaced with a GPS module for acquiring time information, position information of an aircraft, and the like, and a situation recognition module for recognizing a flight, an encounter situation, etc., have.

For example, assuming that the mission scenario is created by performing the content of the B air mission when the aircraft enters the specific region A, the mission equipment control unit 33 determines whether the aircraft enters the A based on the location information acquired from the GPS module , It transmits a control signal to the air mission device 10 to perform the B air mission contents.

The operation mode selection unit 35 is configured to monitor a data link state between the aircraft and the ground center GC and to set a self-operation mode to perform the air mission according to the mission scenario in response to the data link (DL) And a ground operation mode for performing an air mission in accordance with a control command transmitted from the GC.

That is, when the data link DL is disconnected or the information transmission / reception through the data link DL is not smooth, the operation mode selection unit 35 cancels the ground operation mode and allows the self-operation mode based on the mission scenario to be performed, It may be possible to carry out the mission.

Meanwhile, the air mission interlock device 30 may further include a result storage unit 37 to store the mission results performed through the air mission equipment 10. At this time, it is needless to say that the performed mission results may be stored together with the storage device constituting the air mission device 10. [ In addition, when the result of all the tasks can not be stored due to the limitation of the size of the memory, priority may be set for each result and priority information may be preferentially stored.

The result of the stored mission may be transmitted to the ground center GC when it is determined that the data link DL has been resumed or may be provided to the operator through the collection of the result storage unit 37 after the execution of the mission of the aircraft .

Hereinafter, a process in which the air missions are performed through the air mission execution system will be described with reference to flowcharts.

FIG. 4 is a flowchart illustrating a process in which an air mission is performed by the system of FIG. 1;

Referring to FIG. 4, the air mission interlocking device 30 loads the mission scenario file to activate its own operation mode (S10). As described above, the mission scenario file includes at least one of the position information, the time information, and the situation information as the mission execution condition, and includes the contents of the mission performed when the condition fulfillment condition is fulfilled. It can be created separately for each equipment (10) and for each mission type.

The air mission interlock device 30 recognizes the time information, the position information of the aircraft, the situation information, and the like based on the interfaced GPS module and the situation recognition module, and determines whether the mission information matches the mission execution conditions of the mission scenario (S11). If it is determined that they match, a control signal corresponding to the mission content of the mission scenario is generated and transmitted to the air mission equipment 10 (S13).

The air mission device 10 performs the air mission according to the control signal received from the air mission interlock device 30 (S15).

On the other hand, each of the steps described above can be modified or added appropriately depending on the situation. For example, if it is determined that the transmission / reception through the data link DL is not smooth, the air mission interlocking device 30 releases the initially activated ground operation mode and activates the self-operation mode based on the mission scenario . In addition, when the data link DL is resumed in the state where the self-operation mode is activated, the step of switching the operation mode to the ground operation mode may be further included.

According to the related art, there is a problem that it is impossible to perform the mission because the air mission equipment 10 can not be controlled in a situation where information transmission / reception through the data link (DL) can not be performed. In the present invention, in addition to the ground operation mode through interlocking with the ground center (GC), the aviation mission can be performed according to the self-operation mode based on the mission scenario, thereby solving the above- .

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined by the appended claims. There will be. For example, although the signal information gathering mission is described herein as an example of an air mission, the present invention is not limited to the above, and can be widely applied to various air mission.

Therefore, it is to be understood that the embodiments of the present invention are to be considered as illustrative only, and that the technical spirit of the present invention is defined from the description of the claims, and the scope of protection is to be applied to the equivalents.

10: Air mission equipment 30: Air mission interlock
31: scenario storage unit 33: mission equipment control unit
35: Operation mode selection unit 37: Result storage unit
100: Aviation Mission System

Claims (14)

A system for performing an aeronautical mission in which an aeronautical mission device mounted on an aircraft is used to perform an aeronautical mission,
And a control unit for storing a mission scenario performed by the air mission equipment in correspondence with at least one of the position information, the time information, and the situation information, and generating a control signal for controlling the air mission equipment in response to the mission scenario Mission Interlocking Device; And
And an air mission device for performing an air mission in accordance with the control signal transmitted from the air mission interlock device. The method according to claim 1,
Wherein the mission scenario includes at least one of a flight altitude, a flight area, a time, a flight status, and an encounter condition according to a mission execution condition of the flight mission. 3. The method of claim 2,
Wherein the air mission interlocking device determines whether the mission execution condition is satisfied based on a GPS module and a situation recognition module mounted on the aircraft. The method according to claim 1,
Wherein the mission scenario includes at least one of a mission type, a mission execution time, a mission execution cycle, a mission execution frequency, a mission execution resolution, and a mission execution position for each air mission device. Performance system. The method according to claim 1,
Wherein the air mission interlocking device comprises: a self-operation mode for monitoring a data link state between the aircraft and the ground center and for controlling the air mission equipment according to the mission scenario in response to the data link state; And a ground operating mode in which the air mission equipment is controlled according to the operation mode. A scenario storage unit for storing mission scenarios performed by the air mission equipment mounted on the aircraft corresponding to at least any one of position information, time information, and situation information; And
And a mission equipment control unit for determining whether the mission scenario fulfills the mission fulfillment condition and generating a control signal for controlling the air mission equipment in response to the mission scenario. The method according to claim 6,
Wherein the mission scenario is set up to include mission content according to at least one of flight altitude, flight area, time, flight status, and encounter status. The method according to claim 6,
Wherein the mission equipment control unit determines whether the mission execution condition is satisfied based on the GPS module of the aircraft and the situation recognition module. The method according to claim 6,
Wherein the mission scenario includes at least one of a mission type, a mission execution time, a mission execution cycle, a mission execution frequency, a mission execution resolution, and a mission execution position for each air mission device. Interlocking device. The method according to claim 6,
And a control unit operable to monitor a data link status between the aircraft and the ground center and to control the air mission equipment according to the mission scenario in response to the data link status, Further comprising an operation mode selection unit that selects one of the ground operation modes for controlling the operation of the air mission. The method according to claim 6,
And a result storage unit for storing mission performance result information performed by the air mission equipment. 1. A method of performing an air mission in which an air mission device mounted on an aircraft is used to perform a mission,
(a) loading a mission scenario file of an air mission device created by the air mission interlocking device in correspondence with at least one of position information, time information, and situation information;
(b) determining whether the air mission interlocking device conforms to the execution condition of the mission scenario, and generating a control signal for controlling the air mission device in response to the content of the mission scenario; And
and (c) performing the air mission in response to the control signal. 13. The method of claim 12,
Wherein the air mission interlocking device determines whether the execution condition of the mission scenario is met based on the GPS module and the situation recognition module of the aircraft. 13. The method of claim 12,
Before the step (a)
The air mission interlocking device releases the ground operation mode in which the air mission equipment is operated by the ground center in accordance with the data link state established between the aircraft and the ground center and operates the air mission equipment in accordance with the mission scenario Further comprising the step of activating a self-running mode.
KR1020150058289A 2015-04-24 2015-04-24 Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode KR101680699B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020150058289A KR101680699B1 (en) 2015-04-24 2015-04-24 Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020150058289A KR101680699B1 (en) 2015-04-24 2015-04-24 Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode

Publications (2)

Publication Number Publication Date
KR20160126783A true KR20160126783A (en) 2016-11-02
KR101680699B1 KR101680699B1 (en) 2016-11-29

Family

ID=57518511

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020150058289A KR101680699B1 (en) 2015-04-24 2015-04-24 Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode

Country Status (1)

Country Link
KR (1) KR101680699B1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180070130A (en) * 2016-12-16 2018-06-26 주식회사 한화 Apparatus and method for managing available resource of air vehicle equipped with mfr
KR102033750B1 (en) * 2019-05-17 2019-10-17 국방과학연구소 Electronic warfare signal low data generation device for avionics electronic warfare system and method of generating low data thereof
KR102237609B1 (en) * 2020-11-27 2021-04-12 대한민국(방위사업청장) Air Tasking Order Automatic Generation Apparatus for Military Operations Simulation Model
KR102631681B1 (en) * 2023-06-08 2024-02-01 국방과학연구소 Method of Controlling of Transmission Rate of Mission Equipment in Unmanned Aerial Systems and Apparatus Thereof

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180070130A (en) * 2016-12-16 2018-06-26 주식회사 한화 Apparatus and method for managing available resource of air vehicle equipped with mfr
KR102033750B1 (en) * 2019-05-17 2019-10-17 국방과학연구소 Electronic warfare signal low data generation device for avionics electronic warfare system and method of generating low data thereof
KR102237609B1 (en) * 2020-11-27 2021-04-12 대한민국(방위사업청장) Air Tasking Order Automatic Generation Apparatus for Military Operations Simulation Model
KR102631681B1 (en) * 2023-06-08 2024-02-01 국방과학연구소 Method of Controlling of Transmission Rate of Mission Equipment in Unmanned Aerial Systems and Apparatus Thereof

Also Published As

Publication number Publication date
KR101680699B1 (en) 2016-11-29

Similar Documents

Publication Publication Date Title
CN111656424B (en) Automatic flying unmanned aerial vehicle system based on big data and automatic flying method thereof
US11915598B2 (en) Fleet management of unmanned aerial vehicles and flight authorization system
US20220122473A1 (en) Computer aided dispatch of drones
US11874656B2 (en) Unmanned aerial vehicle modular command priority determination and filtering system
US10013885B2 (en) Airspace deconfliction system and method
CA2961367C (en) Fail safe aircraft monitoring and tracking
EP3505871B1 (en) Management system for unmanned aerial vehicles
US8979032B1 (en) Methods and systems for retrieving personnel
US9990854B1 (en) Unmanned aerial system mission flight representation conversion techniques and traffic management scheme
KR101680699B1 (en) Airborne mission perform system, airborne interface process unit, and airborne mission performing method providing autonomic operation mode
US11046450B1 (en) Aviation situation awareness and decision information system
US10929205B2 (en) Triggered automated operations for spaceborne and airborne nodes
CN107992077A (en) Aircraft fault rescue method and device
US10511515B1 (en) Protocol buffer avionics system
JP2021072091A (en) Computation load distribution method, computation load distribution device, mobile vehicle, data processing method, data processing device, and program
WO2015009705A2 (en) Mission component evaluation and response architecture
KR102249935B1 (en) Missile system including ads-b receiver
JP2020167485A (en) Communication management device, communication management system, communication management method, and communication management program
WO2015140795A1 (en) Core UxV Control System
US10303941B2 (en) Locating light sources using aircraft
US20180319511A1 (en) Systems for and methods of providing indicators useful for piloting an aircraft
KR101696248B1 (en) Aircrafts oeprating system, aircrafts of aircrafts operating system and operationg method of aircrafts
US20200110424A1 (en) Geofencing of unmanned aerial vehicles
US20200380878A1 (en) Method and system for avoiding mid-air collisions and traffic control
US20240119849A1 (en) Collision avoidance system and method

Legal Events

Date Code Title Description
A201 Request for examination
E701 Decision to grant or registration of patent right
GRNT Written decision to grant