• 한국항행학회논문지
• /
• 제22권2호
• /
• pp.57-63
• /
• 2018

항공기 발사용 유도무기는 자체점검시험(BIT; built in test) 뿐만 아니라 MIL-STD-1760표준을 준수하여 전원, 이산신호, MUX(multiplexer)통신 등 다양한 시험을 수행해야 시스템 안전성 및 신뢰성이 입증된다. 본 사례 연구 목적은 MIL-STD-1760E 기반 항공기-무장간 연동용 테스트 벤치 구축을 통하여 공대지 유도탄 개발 시 유도탄 전원인가부터 표적정보 입력, 전달정렬, 유도탄 분리 절차에 이르기까지 정의된 TIME LINE에 의거 유도탄 발사 시퀀스 구현 방안을 제시하기 위함이고, 추가적으로 오류삽입기능을 통해 비 활성탄에서 시험할 수 없는 항목까지 검증 범위를 극대화하는 참조 방안이 될 수 있다.

• 한국군사과학기술학회지
• /
• 제6권3호
• /
• pp.22-35
• /
• 2003

This paper describes system technical requirement development process from operational concept using computer-aided Systems Engineering tool(CASysE Tool-CORE). The army tactical missile system-ATACMS's technical requirements are developed by the process as a case-study The scope of the work is context analysis and requirement definition process. The proposed process is as follows. At first, an integrated architecture could be developed from the operational concept. From the integrated architecture a capability needs, which includes KPPs, are generated. And the capability needs expanded according to the Mil-Std-961D format. Lastly, a system technical requirement could be generated automatically from the CASysE Tool-CORE.

• 한국소음진동공학회논문집
• /
• 제15권7호
• /
• pp.813-820
• /
• 2005

A deployable missile control fin has some structural nonlinearities because of the worn or loose hinges and the manufacturing tolerance. The structural nonlinearity cannot be eliminated completely, and exerts significant effects on the static and dynamic characteristics of the control fin. Thus, It is important to establish the accurate deployable missile control fin model. In the present study, the nonlinear dynamic model of 4he deployable missile control fin is developed using a substructure synthesis method. The deployable missile control fin can be subdivided Into two substructures represented by linear dynamic models and a nonlinear hinge with structural nonlinearities. The nonlinear hinge model is established by using a system identification method, and the substructure modes are improved using the Frequency Response Method. A substructure synthesis method Is expanded to couple the substructure models and the nonlinear hinge model, and the nonlinear dynamic model of the fin is developed. Finally, the established nonlinear dynamic model of the deployable missile control fin is verified by dynamic tests. The established model is In good agreement with test results, showing that the present approach is useful in aeroelastic stability analyses such as time-domain nonlinear flutter analysis.

• 한국정보통신학회:학술대회논문집
• /
• 한국정보통신학회 2017년도 춘계학술대회
• /
• pp.371-372
• /
• 2017

미국은 냉전시대부터 미사일방어체계를 구축해왔으나, 냉전시대 종식 이후 국제 정세와 위협 세력에 많은 변화가 있었다. 미국과 소련으로 양분되어있던 힘의 세력이 중국의 대외적 영향력 확장 의지, 강한 러시아의 표방, 북한과 이란의 핵 무장 및 탄도미사일 기술 고도화 등으로 인해 대응해야 할 위협이 다양해졌다. 이러한 위협 변화에 대해 미사일방어청(Missile Defense Agency : MDA)은 전략 및 정책을 수립하였으나, 이의 근간인 상위법은 개정되지 않다가 2017년 국방수권법(FY2017 National Defense Authorization Act : FY2017 NDAA)에 변화된 미국의 미사일방어 전략이 명문화되었다. 본 논문에서는 FY2017 NDAA에 반영된 미국의 탄도미사일방어 전략을 확인하고, 기존의 전략에서 어떤 부분이 변화하였는지 비교하였다.

• 제어로봇시스템학회논문지
• /
• 제14권12호
• /
• pp.1218-1225
• /
• 2008

This paper presents the design of a neural network based adaptive control for missile is presented. The application model is Exocet MM40, which is derived from missile DATCOM database. Acceleration of missile by tail Fin control cannot be controllable by DMI (Dynamic Model Inversion) directly because it is non-minimum phase system. So, the inner loop consists of DMI and NN (Neural Network) and the outer loop consists of PI controller. In order to satisfy the performances only with PI controller, it is necessary to do some additional process such as gain tuning and scheduling. In this paper, all flight area would be covered by just one PI gains without tuning and scheduling by applying mixture control technique of conventional controller and NN to the outer loop. Also, the simulation model is designed by considering non-minimum phase system and compared the performances to distinguish the validity of control law with conventional PI controller.

• 한국국방경영분석학회지
• /
• 제23권1호
• /
• pp.1-13
• /
• 1997

This research investigates a kill probability model for the performance evaluation of guided missile system, and also develops the user interface implementation for the output of the model based on the visual object-oriented programming application. This paper describes in detail the methodology for the kill probability attained by a missile warhead detonating near an airborne target. The major simulation events used in this research are missile guidance homing point, burst points, and kill mechanism(direct kill, blast kill and fragment kill). For the user interface, we also design and implement the visualization system that can show the graphic style of the kill probability attained by the model. This research will bridge the gap between the sophisticated kill probability model and users who want to see the results interactively with visualization, which can benefit many of other military systems. Some examples are shown, but these will be improved to be better with visual simulation which can visualize all the simulation process of the model.

• 산업경영시스템학회지
• /
• 제46권4호
• /
• pp.190-198
• /
• 2023

The purpose of this study was to propose an operational concept for a ship in a fleet equipped with an interceptor missile system, a naval surface to air defense system, and to develop a simulation program that reflects it. The results of the defense activities of other ships in the fleet can be reflected by receiving information about the status of the enemy missiles. The allocation of defensive assets is based on the survival probability of the ship, not on the destruction of enemy attacks, which can be obtained as the product of the expected survival probability for each enemy missile. In addition, the concept of predicted survivability was introduced to assess the loss of future defense opportunities that would result from assigning a new command. A simulation program was also developed as a tool for realizing the proposed concept of operations, which generated cases.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 1986년도 한국자동제어학술회의논문집; 한국과학기술대학, 충남; 17-18 Oct. 1986
• /
• pp.498-502
• /
• 1986

A generalized singular linear quadratic control technique is developed to design an optimal trajectory tracking system. The output feedback control law is designed using this technique. The feedback gain matrix is synthesized to minimize tracking errors with pole placement capability to satisfy the control activity requirements. An applications to a bank-to-turn missile coordinated autopilot system design is presented.

• 한국정밀공학회지
• /
• 제33권10호
• /
• pp.781-787
• /
• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2006년도 제26회 춘계학술대회논문집
• /
• pp.343-346
• /
• 2006

본 연구에서는 유도무기 MDO 프레임워크 개발을 위한 최적화 과정을 구성하였다. MDO 프레임워크에 통합될 각 해석 자원과 통합설계를 위한 해석 자원간의 데이터 흐름을 분석하였다. 분석된 자료를 토대로, 개발될 MDO 프레임워크의 최적설계 시나리오를 작성하였다. 그리고 작성된 시나리오의 검증을 위해 유도무기에 대한 최적설계 문제를 구성하여 이를 수행하였다.