KR20190052792A - Engagement level model apparatus for aircraft survivability equipments based on discrete event system specification and Method thereof - Google Patents

Abstract

The present invention relates to a simulator technique and, more particularly, to an apparatus and a method for designing and constructing a discrete event system specification (DEVS) based simulator for analyzing the operability of aircraft survivability equipment (ASE). An apparatus of an aircraft survivability equipment battle model based on the DEVS comprises: a simulated missile installation module; a simulated helicopter processing module; and an analyzer.

Description

Technical Field [0001] The present invention relates to an apparatus and method for engaging survival equipment based on a discrete event system specification method,

The present invention relates to a simulator technology, and more particularly, to a design and structure for a discrete event system specification (DEVS) based simulator for analyzing the operability of aircraft survivability equipment (ASE) And to a method and a device for the same.

(AWAM), Extended Air Defense Simulation (EADSIM), etc., are available for the analysis of operability of survival equipment.

AWAM (Army weapon effectiveness analysis model) is a simulator for analyzing army weapon systems combat effectiveness mainly developed in Korea and has many domestic weapons and / or scenarios modeled. Also, it is advantageous that many DBs (DataBase) are actively used in Korea, and simulation suitable for domestic terrain and domestic operation situation is possible.

However, there is no way to apply survival equipment to helicopters, and there are limitations to the use of laser weapons such as Directional Infrared Counter Measures (DIRCM) among survival equipment, which are not modeled. Extended air defense simulation (EADSIM) was developed by Teledyne Brown Engineering in 1987 and is a mission-level simulation tool that has been continuously improved and utilized. This EADSIM has been used for many years and can simulate engaging class for some models.

However, for laser weapons such as DIRCM, input parameters are very limited, and there are many unnecessary parameters in the helicopter and / or missile, making it difficult to analyze the operability accurately. Therefore, it is required to develop a model for the design of an engaging class simulator for the analysis of operability of survival equipment including DIRCM. In addition, the design needs to present the core logic and functions and display it with the DEVS structure so that it is easy to transplant in a multilingual environment.

1. Korean Registered Patent No. 10-1737015 (2017.05.11) (Title: Discrete event system specification based war game simulation engine system) 2. Korean Registered Patent No. 10-1269528 (2013.05.24) (title: invention of graphic modeling technique of discrete event system)

1. Choi, Won-joon, "Expansion Study of Tank Engagement Simulation Model" Dissertation (MA) National Defense University 2003

Disclosure of Invention Technical Problem [6] The present invention has been proposed in order to solve the problem according to the above background art, and it is an object of the present invention to provide a discrete event system specification (DEVS) based simulator for analyzing the operability of aircraft survivability equipment It is an object of the present invention to provide an apparatus and method for engaging survival equipment based on a discrete event system specification method for design and construction.

The present invention provides a survival device engagement model device based on a discrete event system specification method in order to achieve the above-described problems.

The survival device engagement model device includes:

A simulated missile processing module 110 based on a discrete event system specification method to generate simulated missile coordinate information 130 according to activation of the simulated missile 111;

Generates simulated helicopter coordinate information 142 according to the activation of the simulated helicopter 151 and generates converted helicopter coordinate information 141 using the simulated missile coordinate information 130 and the simulated helicopter coordinate information 142, A simulated helicopter processing module 150 based on an event system specification method; And

An analyzer for calculating a missile hit rate by determining whether the simulated missile 111 is within a proximity range preset in the simulated helicopter 151 using the converted helicopter coordinate information 141 and the simulated missile coordinate information 130 120). ≪ / RTI >

In addition, the simulated helicopter processing module 150 includes: a simulated helicopter 151 that starts simulating; An operation unit 153 for operating the simulated helicopter 151 according to a predetermined scenario to generate simulated helicopter coordinate information 142; And a helicopter coordinate generator 152 for receiving the simulated missile coordinate information 130 and the simulated helicopter coordinate information 142 from the simulated missile processing module 110 to generate converted helicopter coordinate information 141. [ .

The helicopter coordinate generator 152 also includes a detection unit 152-1 that receives the simulated missile coordinate information 130 and detects a simulated missile; And a calculation unit 152-2 for calculating the converted helicopter coordinate information 141 by using the engagement distance and the deception rate when a simulated missile is detected.

In addition, the detection unit 152-1 may detect the simulated missile 111 using a MWR (Missile Warning Receiver) model.

Also, the calculating unit 152-2 may calculate the converted helicopter coordinate information using a Directional Infrared Counter Measures (DIRCM) model.

The simulated missile processing module 110 includes a tracking unit 112 that receives simulated helicopter coordinate information 142 activated according to a scenario and converts the target coordinates of the target simulated helicopter 151 to a Kim speed; And an induction unit (113) for generating missile coordinate information (130) in accordance with the guidance information by tracking the gimbal speed.

The analyzer 120 also includes a counter 122 for counting elapsed time; And a proximity checking unit (121) for determining whether the simulated missile approaches the simulated helicopter by comparing the difference between the converted helicopter coordinate information and the simulated missile coordinate information with a predetermined set reference value according to the elapsed time .

In addition, the missile hit rate may be calculated by applying a delta function type deemed distribution.

In addition, the missile hit rate may be calculated by using a user-specified value and applying a deception rate to the distance.

On the other hand, according to another embodiment of the present invention, (a) the simulated missile processing module 110 based on the discrete event system specification method generates the simulated missile coordinate information 130 according to the activation of the simulated missile 111 step; (b) The simulated helicopter processing module 150 based on the discrete event system specification method generates the simulated helicopter coordinate information 142 in accordance with the start of the simulated helicopter 151, and generates the simulated missile coordinate information 130 and the simulated helicopter coordinates Generating transformed helicopter coordinate information (141) using information (142); And (c) the analyzer 120 determines whether the simulated missile 111 is within a proximity range preset in the simulated helicopter 151 using the converted helicopter coordinate information 141 and the simulated missile coordinate information 130 And calculating a missile hit rate based on the calculated missile hit rate and the missile hit rate.

 According to the present invention, it is possible to develop a tool for analyzing survival equipment operational performance modeling that has not been developed before, such as analysis of optimum location of survival equipment, analysis of effectiveness during operation, and development of operation technique.

Further, as another effect of the present invention, even if the simulator is not constituted by a software, the models for the respective models are expressed manually and / or language-independent, so that continuous variable insertion environment addition and / Can be performed freely regardless of language.

Another effect of the present invention is that each atom is modeled and expressed in a class diagram so that a third developer can quickly apply it.

Further, as another effect of the present invention, it is possible to obtain data similar to the actual situation by modeling the delta function type distribution so as to increase the reliability probability by using a user-specified value and applying a deception rate to each distance have.

Further, another advantage of the present invention is that a cross-validation of the developed products can be performed by constructing various simulators for ASE (Aircraft Survivability Equipment) including DIRCM (Directional Infrared Counter Measures) based on the drawings.

1 is a block diagram of a survival device engagement model apparatus having a simulator and a determiner according to an embodiment of the present invention.
FIG. 2 is a flowchart illustrating a process of implementing a survival equipment engagement model based on a discrete event system specification method according to an embodiment of the present invention.
FIG. 3 is a class diagram modeling each atom according to an embodiment of the present invention.
FIG. 4 is a conceptual diagram showing a method of applying a missile hit rate according to a distance according to an embodiment of the present invention.
FIG. 5 is a three-dimensional Gaussian distribution diagram of a missile hit rate and a deception rate according to a distance according to an embodiment of the present invention.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

Like reference numerals are used for similar elements in describing each drawing.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another.

For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component. The term " and / or " includes any combination of a plurality of related listed items or any of a plurality of related listed items.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.

Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Should not.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an apparatus and method for survival device engagement model based on a discrete event system specification method according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a block diagram of a survival device engagement model apparatus having a simulator and a determiner according to an embodiment of the present invention. Figure 1 is a drawing of a design and construction for a DEVS (Discrete Event System Specification: Discrete Event System Specification or Discrete Event Specification Method) based simulator for analyzing the operability of an aircraft survivability equipment (ASE).

The simulator can be constructed by constructing the simulator according to the drawing of Fig. 1 irrespective of the base programming language. 1 includes a simulated missile processing module 110 for simulating a missile, a simulated helicopter processing module 150 for simulating a helicopter, an analyzer 120, and the like. The survival equipment engage model device 100 shown in FIG. . The survival device engagement model device 100 is composed of a hybrid system such as a continuous time and a discrete time system for system configuration for analysis of the operability of survival equipment.

The simulated helicopter processing module 150 includes a simulated helicopter 151 that is simulated and an operation unit 153 that generates simulated helicopter coordinate information 142 by operating the simulated helicopter 151 according to a predetermined scenario, A helicopter coordinate generator 152 for receiving the simulated missile coordinate information 130 and the simulated helicopter coordinate information 142 from the processing module 110 to generate converted helicopter coordinate information 141,

The helicopter coordinate generator 152 includes a detection unit 152-1 that detects the simulated missile by receiving the simulated missile coordinate information 130 and a converted helicopter coordinate information And a calculating unit 152-2 for calculating the number of pixels (e.g., pixels) 141 and the like.

The detection unit 152-1 detects a simulated missile 111 using a MWR (Missile Warning Receiver) model, which is a lower model of the helicopter model.

The calculating unit 152-2 calculates the converted helicopter coordinate information using Directional Infrared Counter Measures (DIRCM), which is a lower model of the helicopter model. That is, the engagement distance and the deception rate of the DIRCM are set in advance.

Further, the calculating unit 152-2 adds a delay from the target position (i.e., helicopter coordinate information) to provide a message (fire) on the debris rate of the DIRCM, and outputs the helicopter coordinate information 142 acquired from the operating unit 153 The converted helicopter coordinate information 141 is generated.

The operation unit 153 may include model information corresponding to the operation of the helicopter including path information (PATH), map attitude information, team collaboration information, and the like to create a scenario. The operation unit 153 inputs, as path information (PATH), a user-specified scenario to each passage point on the terrain through which the helicopter must pass, with respect to the position of the point and the altitude and speed of the helicopter between starting points, . At this time, the altitude is the sea level altitude, and when the terrain is higher than the designated altitude, the altitude information of the terrain is received for exception processing, and the altitude information of the helicopter can be modified so that the helicopter maintains the altitude of 30m at the exception point.

In addition, in order to express the size of the helicopter in the current coordinates between each helicopter, the distance information between the helicopters is exchanged to maintain the set distance for the designated size.

The simulated helicopter processing module 150 implements the scenario in which the MWR detects the simulated missile 111 while the simulated helicopter 151 is activated, tracks the position thereof, engages the DIRCM, and analyzes the result of the engagement. At this time, the scenario is a battle scenario and is usually performed through a process of start-detection-tracking-engagement-determination.

The simulated missile processing module 110 includes a tracking unit 112 for receiving the simulated helicopter coordinate information 142 activated according to the scenario and converting the target coordinates of the target simulated helicopter 151 to a gimbal rate, And an induction unit 113 for generating the missile coordinate information 130 according to the guidance information by tracking the speed.

The analyzer 120 compares the difference between the converted helicopter coordinate information and the simulated missile coordinate information with a preset reference value according to the elapsed time to determine whether the simulated missile approaches the simulated helicopter A proximity check unit 121, and the like.

The counter 122 performs a role of collecting the number of times of helicopter input to the analyzer 120 from the operation unit 153 and analyzing the state of the missile input to the analyzer 120 from the helicopter state and the missile coordinate information 130 . Its functions include time management, checking the number of helicopters, checking the missile's launch count, checking the distance between the missile and the helicopter, checking the number of helicopters that have been shot down, and checking the number of deceased missiles. And performs the role of the simulation result judgment.

Referring to FIG. 1, the simulated missile processing module 110, the simulated helicopter processing module 150, and the analyzer 120 are composed of a top-most coupled model.

Also, the coordinate information 130, 141, 142 indicated by a bold box represents an external message, and the coordinate information indicated by a thin box represents an output message. PNL is a proportional navigation induction that induces a target from the missile's flight axis to the target direction, and directs it toward the target direction.

FIG. 2 is a flowchart illustrating a process of implementing a survival equipment engagement model based on a discrete event system specification method according to an embodiment of the present invention. 2, a simulated helicopter is activated in accordance with the approved scenario after the simulation begins, and the simulated helicopter processing module 150 continues to map the helicopter coordinate information 142 to the analyzer 120 and / or the simulated missile processing module 110 (step S210). The simulated missile processing module 110 also continues to send the simulated missile coordinate information 130 to the simulated helicopter processing module 150 and / or the analyzer 120.

 The internal transition time of the simulated helicopter processing module 150, the simulated missile processing module 110, and the analyzer 120 may be determined as an input of a scenario according to the public start table. The public start table is a concept implemented as a path information (PATH) on the simulator. When the user inputs the location of the point and the altitude and speed of the helicopter between maneuvers between the points for each passage point on the terrain the helicopter must pass, ) Is implemented on the simulator as a helicopter coordinate form.

On the other hand, the simulated missile coordinate information 130 exists as a trigger for transmitting a missile alarm.

The simulated missile processing module 110 determines whether the simulated helicopter 151 is within the field of view of the operator according to the simulated helicopter coordinate information 142 and the converted helicopter coordinate information 141. If the simulated helicopter 151 exists in the field of view , It transitions to the ready to launch state.

When the ready-to-fire state is finished, the simulated missile 111 transitions to the inductive state and starts induction (steps S211, S213, and S215). The helicopter coordinate information is received by the tracking unit 112 and the position of the mock helicopter 151 as the target is measured and then the lobe rate Line of Sight), and transmits the simulated missile coordinate information indicating the position of the missile to the analyzer 120. When the simulated missile 111 is launched, the detection unit 152-1 transmits the missile alarm to the calculation unit 152-2.

The simulated helicopter processing module 150 receiving the simulated missile coordinate information 130 receives the missile alert and requests the position information of the simulated missile 111 To the simulated missile processing module (110). The simulated missile processing module 110 that received the request message transmits the request message to the simulated helicopter processing module 150 and / or the analyzer 120, which transmits the simulated missile coordinate information 130 indicating the position, speed, and altitude of the simulated missile 111, (Steps S220 and S230).

The simulated helicopter processing module 150 sends a meshing rate corresponding to the position, altitude and speed of the simulated missile 111 to the simulated helicopter 151 as a message to the simulated missile processing module 110 (steps S221 and S223 , S225, S228, S229).

Thereafter, the simulated missile processing module 110 maintains the state according to the dejection probability or sends a miss signal to the analyzer 120. Here, the miss signal is transmitted to the analyzer 120 when the simulated missile 111 is deceived by the deception rate message and when the simulated helicopter disappears from the FoV of the tracking unit 112.

The simulated helicopter processing module 150 transmits the converted helicopter coordinate information 141 and the simulated missile processing module 110 transmits the missile coordinate information to the analyzer 120 at intervals of 1/60 frame. The helicopter coordinate information-missile coordinate information) is within the predetermined reference value (about 8 m), it is judged as hit (steps S230 and S240).

In addition, when the simulated helicopter processing module 150 performs all of the predetermined scenarios or about four simulated helicopters 151 are hit, the analyzer 120 declares the end of the model and outputs the result.

On the other hand, DIRCM, receiving the missile warning, can detect the position of the missile and the location of the simulated helicopter and transmit the position of the simulated helicopter reflecting the deception rate to the simulated missile to deceive and disable the missile. Each model is designed based on DEVS, and other survival equipment is easy to implant.

FIG. 3 is a class diagram modeling each atom according to an embodiment of the present invention. Referring to FIG. 3, a control value is input to Main from a Main UI (User Interface) 310, and a Main function sets functions of a simulated helicopter, MWR, DIRCM, and a simulated missile. The parameter 320 of the MWR has a detection rate, and the parameter 330 of the simulated helicopter has a mounting position, an altitude, and a speed. The DIRCM parameter 340 includes delay (including deception time), FOV, deception rate, and the like. Finally, the parameter 350 of the simulated missile has the type of missile, the maximum speed, the maximum operating time, and the detection distance.

Each of the functions receives the parameter setting value and transmits information to the task manager 360.

The task manager 360 maps the start point, the end point, the path, the count, the distance, and the missile position as parameters, calculates the distance by calculating the distance after performing the map check, and displays the position. And calculate the survival rate for the missile.

FIG. 4 is a conceptual diagram showing a method of applying a missile hit rate according to a distance according to an embodiment of the present invention. Referring to FIG. 4, a model similar to the actual situation is obtained by applying a delta function type deference distribution, using a user-specified value, and applying a deception rate to each distance to increase the reliability probability. Of course, these elements can be applied in combination. For example, only delta functional deception distributions and user-specified values can be applied.

In addition, it is possible to cross-validate development products by constructing a variety of simulators for ASE including DIRCM based on drawings.

401: Direc-delta functional deception distribution where the stability value is a user-defined deception rate

402: Maximum deception rate (maximum value 100%)

403: Rate of deception based on user-defined deception rate

404: Normal distribution where extreme values are maximum deception rate

405: Normal distribution where extreme values are user-defined deception rate

406: Deception rate difference by user's dejection rate

FIG. 5 is a three-dimensional Gaussian distribution diagram of a missile hit rate and a deception rate according to a distance according to an embodiment of the present invention. The actual phenomenon of DIRCM's deception rate is influenced by external environmental factors such as humidity, temperature, temperature, distance, etc., and the user can use the distance The trust level of the deception rate can be determined. That is, the user can determine the extent to which the Z-axis deception rate is interfered by external factors, and the distance DISTANCE indicates the distance between the DIRCM and the missile.

The terms " part, " " unit, " " module, " and the like, which are described in the specification, refer to a unit that processes at least one function or operation, and may be implemented by hardware or software or a combination of hardware and software.

... "... And the like may be implemented in hardware, software, or a combination thereof. In hardware implementation, an application specific integrated circuit (ASIC), a digital signal processing (DSP) A programmable logic device (PLD), a field programmable gate array (FPGA), a processor, a controller, a microprocessor, other electronic units or a combination thereof. In a software implementation, The software may be stored in a memory unit and executed by a processor. The memory unit or processor may employ various means well known to those skilled in the art

100: survival equipment engagement model device
110: simulated missile processing module
111: Mock missiles
112: tracking section 113:
120: Analyzer
150: Mock helicopter processing module
152: Helicopter coordinate generator
153:
152-1:
152-2:

Claims (10)

A simulated missile processing module 110 based on a discrete event system specification method to generate simulated missile coordinate information 130 according to activation of the simulated missile 111;
Generates simulated helicopter coordinate information 142 according to the activation of the simulated helicopter 151 and generates converted helicopter coordinate information 141 using the simulated missile coordinate information 130 and the simulated helicopter coordinate information 142, A simulated helicopter processing module 150 based on an event system specification method; And
An analyzer for calculating a missile hit rate by determining whether the simulated missile 111 is within a proximity range preset in the simulated helicopter 151 using the converted helicopter coordinate information 141 and the simulated missile coordinate information 130 120);
And a survival device engagement model device based on the discrete event system specification method.
The method according to claim 1,
The simulated helicopter processing module (150)
A simulated maneuvering helicopter 151;
An operation unit 153 for operating the simulated helicopter 151 according to a predetermined scenario to generate simulated helicopter coordinate information 142; And
And a helicopter coordinate generator 152 for receiving the simulated missile coordinate information 130 and the simulated helicopter coordinate information 142 from the simulated missile processing module 110 to generate converted helicopter coordinate information 141 Survival equipment engagement model device based on discrete event system specification method.
3. The method of claim 2,
The helicopter coordinate generator 152,
A detection unit (152-1) for detecting the simulated missile by receiving the simulated missile coordinate information (130); And a calculation unit (152-2) for calculating the converted helicopter coordinate information (141) by using the engagement distance and the deception rate when the simulated missile is detected. The survival equipment engagement model based on the discrete event system specification method Device.
The method of claim 3,
The detection unit 152-1 detects the simulated missile 111 using a MWR (Missile Warning Receiver) model. The survival equipment engagement model unit is based on the discrete event system specification method.
The method of claim 3,
And the calculating unit 152-2 calculates the converted helicopter coordinate information using a DIRCM (Directional Infrared Counter Measures) model.
3. The method of claim 2,
The simulated missile processing module (110)
A tracking unit 112 that receives the simulated helicopter coordinate information 142 activated according to the scenario and converts the target coordinates of the target simulated helicopter 151 to the Kim speed; And
And an induction unit (113) for tracking missed speeds and generating missile coordinate information (130) according to the guidance information. The survival device engagement model device based on the discrete event system specification method.
3. The method of claim 2,
The analyzer (120)
A counter 122 for counting elapsed time; And
And a proximity checking unit (121) for comparing the difference between the converted helicopter coordinate information and the simulated missile coordinate information with a preset reference value to determine whether the simulated missile approaches the simulated helicopter according to the elapsed time Survival equipment engagement model device based on discrete event system specification method.
The method according to claim 1,
Wherein the missile hit rate is calculated by applying a delta function type deception distribution to the survival device engagement model device based on the discrete event system specification method.
The method according to claim 1,
Wherein the missile hit rate is calculated by using a user-specified value and applying a deception rate to each of the distances, wherein the survival device engagement model device is based on the discrete event system specification method.
(a) generating a simulated missile coordinate information (130) according to the activation of the simulated missile (111) by the simulated missile processing module (110) based on the discrete event system specification method;
(b) The simulated helicopter processing module 150 based on the discrete event system specification method generates the simulated helicopter coordinate information 142 in accordance with the start of the simulated helicopter 151, and generates the simulated missile coordinate information 130 and the simulated helicopter coordinates Generating transformed helicopter coordinate information (141) using information (142); And
(c) The analyzer 120 determines whether the simulated missile 111 is within a proximity range preset in the simulated helicopter 151 using the converted helicopter coordinate information 141 and the simulated missile coordinate information 130 Calculating a missile hit rate;
A survival device engagement model based on a discrete event system specification method.

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