• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.10
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• pp.992-997
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• 2009

This paper focuses on the calculation of the missile angular velocity under the reduced sensor condition and its verification using the Flight Motion Simulator(FMS). The missile angular velocity is usually measured by the body gyroscopes, but we assume that the inertial sensors on the missile body are in the absence of pitch and yaw gyroscopes. Under this reduced sensor condition, this paper shows the missile angular velocity can be calculated by using the gimbal seeker gyroscope, the roll body gyroscope, the gimbal angle and its rate. The FMS experiment was carried out to verify the proposed algorithm.

• Defense and Technology
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• no.1 s.37
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• pp.53-64
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• 1982

• Journal of the Korea Society for Simulation
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• v.26 no.1
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• pp.13-19
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• 2017

6-DOF flight simulation program is most generally used M&S tool in domestic missile development procedure. The 6-DOF M&S method, however, cannot validate the performance of a imaging seeker-adopted missile in various conditions. A M&S tool for the analysis of the integrated-flight simulation is required since the tracking performance of the imaging seeker is highly dependent on the missile maneuvering, which introduces the displacement and rotation of the target in the seeker imagery. Through the development of the $3^{rd}$ generation anti-tank missile, Raybolt, the integrated-flight M&S tool was developed and applied to the missile configuration design. It integrates synthetic image generation S/W, imaging tracker, and flight simulation program and computes the main system performance criteria, hit probability by Monte-Carlo Simulation. In this paper, the issues in the $3^{rd}$ generation anti-tank missile configuration and the integrated-flight M&S method and results are described.

• Defense and Technology
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• no.4 s.4
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• pp.6-12
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• 1979

• Defense and Technology
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• no.4 s.86
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• pp.13-22
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• 1986

• Defense and Technology
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• no.9 s.33
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• pp.13-18
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• 1981

• Defense and Technology
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• no.9 s.67
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• pp.48-53
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• 1984

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.492-501
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• 2016

Three-Loop autopilot is generally used for the acceleration control of guided missiles. Because the acceleration command to the three-loop autopilot is given as values at the center of gravity, feedback information of IMU should be obtained at the same position. However, the position of IMU might not be located at the center of gravity due to the sub-system assignment. This paper presents the stability analysis of three-loop autopilot with respect to the arbitrary position of IMU and variation rate of center of gravity. Gain and phase margins are calculated for several trim points for general anti-tank missiles.

• Defense and Technology
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• no.10 s.296
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• pp.38-47
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• 2003

2차 세계 대전 이후 대형 로켓의 개발에 소극적이었던 미 정부는 미.소간의 냉전이 격화되던 1950년에 한국전쟁이 발발하게 되자 당시 미국의 트루먼 대통령은 안보강화를 위해, 폰 브라운에게 사정거리 300km이 레드스톤 지대지 유도탄개발을 지시하였고, 1953년 8월 플로리다의 케이프커내버럴 공군기지에서 유도탄 발사에 성공하였다. 이어서 대륙간 탄도탄개발이 본격적으로 추진되었다. 이와 더불어 미국 정부는 미국의 국가위상을 고양하고 기술적 우위를 세계에 과시하기 위해 인공위성의 발사가 절대적으로 필요하다는 결론을 내리고 인공위성사업을 추진키로 하였다.

• Defense and Technology
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• no.5 s.147
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• pp.64-73
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• 1991

제2차 세계 대전 이후 일련의 항공 및 지상 위협들이 출현하고 급속히 변천함에 따라, 전자전 분야의 발전을 알기 위해서는 Litton Applied Technology사를 알아야 한다. 위협 및 레이다 경보수신기 분야의 주역으로서 Litton사는 소련제 지대공 유도탄 체계와 MiG전투항공기의 레이다 방사 신호를 탐지하는 최초의 항공탑재 탐지기와 같은 새로운 분야를 개척하였다