• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.3
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• pp.353-358
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• 2011

In this paper, we have introduced a Missile In the Loop Simulation(MILS) Software developed for the missile ground test, which is based on a commercial hard real-time operating system(OS) on Windows platform called as Real-Time eXtension(RTX). MILS software makes it possible to test overall system functions of a integrated missile on the ground in the flight conditions by real-time imitating its inertial data. By means of MILS, we have performed missiles ground tests, which result in successful real flight tests.

• Proceedings of the KIEE Conference
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• 1993.07a
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• pp.421-423
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• 1993

A real time simulation is an effective tool for use in design, performance evaluation, and testing of the vehicle dynamic system. An alternate approach is to use a computer system designed specifically to provide an integrated simulation environment in which all aspects of hardware-in-the-loop simulation task have been taken into account.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.35 no.11B
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• pp.1659-1666
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• 2010

The High maneuver missiles use various interfaces and high speed guidance and control loop. Hardware-in-the-Loop(HWIL) simulation control system, therefore, should have high performance computing power and hardware interface capabilities, and should be developed using IT technology with which real time operating system, embedded system, data communication technology, and real time hardware control are integrated. This paper suggests the control system design techniques, such as a system hardware configuration, a job distribution algorithm for high performance multi-processors, a real time calculation and control mechanism, inter-processor communication mechanism, and a real time data acquisition technique, to perform the HWIL simulation for high maneuver missile system.

• 제어로봇시스템학회:학술대회논문집
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• 1992.10a
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• pp.165-170
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• 1992

In this paper, the Hardware-In-The-Loop Simulation(HILS) of missile systems are studied. The HILS is an effective performance evaluation technique that bridges the simulation fidelity gap between analytic all-digital simulations and actual flight tests of missile systems. The HILS may be required to perform system integration tests, performance evaluation at system or subsystem level. Major elements of this HILS facility will include the flight table, simulation computers, I/O computer and peripheral equipments. HILS of missile systems typically involve computer modeling of flight dynamics coupled with a hardware guidance and control(G/C) systems. This paper describes a real time performance evaluation technique of a G/C system, Development of a HILS for a Autopilot of SAM G/C will be used as an example.

• Journal of Korea Multimedia Society
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• v.22 no.8
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• pp.930-939
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• 2019

High-Level Architecture(HLA)/Run-Time Infrastructure(RTI) are standards for distributed simulation systems and offer a technology to interconnect them and form one single simulation system. In defense domain, M&S is the only way to prove effectiveness of weapon systems except for Live Fire Testing (LFT). This paper focuses on guided missile simulations in weapon systems for engagement analyses and proposes the integrated flying vehicle model that is based on HLA/RTI. There are a lot of missiles in real world; therefore, we should develop each missile models in M&S in order to apply battlefield scenarios. To deal with the difficulties, in this paper, firstly, I classify these missiles into three models: ballastic, cruise, and surface-to-air missile models, and then I design each missile model and integrates them into a single model. This paper also offers a case study with my integrated flying vehicle model. At the conclusion, this paper presents contributions of this paper.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.3
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• pp.197-204
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• 2021

If a failure or an abnormal maneuver occurs during the flight test of a missile, the missile is deliberately self-destructed so as not to continue the flight. At this time, debris are produced and it is important to estimate the impact area in real-time whether it is out of the safety area. In this paper, we propose a method to estimate the debris dispersion area and falling time in real-time using a Fully-Connected Neural Network (FCNN). We applied the Unscented Transform (UT) to generate a large amount of training data. UT parameters were selected by comparing with Monte-Carlo (MC) simulation to secure reliability. Also, we analyzed the performance of the proposed method by comparing the estimation result of MC.

• Journal of the Korea Institute of Military Science and Technology
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• v.23 no.4
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• pp.426-434
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• 2020

This paper studies the impact of the maintenance time of anti-ship missile Harpoon on operational availability with real field data. The Harpoon maintenance simulation model is developed as a testbed for identifying the optimal inventory levels on operational availability. Using multiple linear regression analysis and integer programming, the optimal inventory levels of essential assemblies are suggested. Finally, the result of sensitivity analysis shows the quantitative impact of maintenance time on operational availability and inventory costs. The authors believe that this quantitative analysis can support policy decisions to decrease maintenance time of missiles.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2659-2661
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• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• International Journal of Aeronautical and Space Sciences
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• v.18 no.4
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• pp.688-696
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• 2017

This paper presents an integrated roll-pitch-yaw autopilot using an equivalent based sliding mode control for skid-to-turn nonlinear time-varying missile system with lumped disturbances in its six-equations of motion. The considered missile model are developed to integrate the model uncertainties, external disturbances, and parameters perturbation as lumped disturbances. Moreover, it considers the coupling effect between channels, the variation of missile velocity and parameters, and the aerodynamics nonlinearity. The presented approach is employed to achieve a good tracking performance with robustness in all missile channels simultaneously during the entire flight envelope without demand of accurate modeling or output derivative to avoid the noise existence in the real missile system. The proposed autopilot consisting of a two-loop structure, controls pitch and yaw accelerations, and stabilizes the roll angle simultaneously. The Closed loop stability is studied. Numerical simulation is provided to evaluate performance of the suggested autopilot and to compare it with an existing autopilot in the literature concerning the robustness against the lumped disturbances, and the aforesaid considerations. Finally, the proposed autopilot is integrated in a six degree of freedom flight simulation model to evaluate it with several target scenarios, and the results are shown.

• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.6
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• pp.822-834
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• 2017

In M&S, radar model is a software module to identify position data of simulation objects. In this paper, we propose a radar performance model for simulations of air defenses. The previous radar simulations are complicated and difficult to model and implement since radar systems in real world themselves require a lot of considerations and computation time. Moreover, the previous radar simulations completely depended on radar equations in academic fields; therefore, there are differences between data from radar equations and data from real world in mission level analyses. In order to solve these problems, we firstly define functionality of radar systems for air defense. Then, we design and implement the radar performance model that is a simple model and deals with being independent from the radar equations in engineering levels of M&S. With our radar performance model, we focus on analyses of missions in our missile model and being operated in measured data in real world in order to make sure of reliability of our mission analysis as much as it is possible. In this paper, we have conducted case studies, and we identified the practicality of our radar performance model.