• Journal of the Korea Institute of Military Science and Technology
• /
• v.11 no.6
• /
• pp.21-29
• /
• 2008

Korean army currently considers the development of the advanced MLRS(Multiple Launcher Rocket System) as a new alternative, which responses on the renovation of the artillery and future battle field environment. Therefore, This study suggests that the development methods of MLRS based on the analysis of the future battle field environment, world wide development trends of the MLRS and operation states of the domestic MLRS. According to this study, the development methods of new generation MLRS should be included a 230/130mm combined launcher competible with conventional 227mm on the vehicle, advanced FCS(Fire Control System), GPS/INS integration navigation system, Pod of ammunitiom, ammunition carrring vehicle and guided rocket munitions, etc.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
• /
• 2011.06a
• /
• pp.13-15
• /
• 2011

전원 공급이 제한되거나 전원 공급이 불가능한 소형 요트, 작업선, 바지선 등에도 항해 안전을 위한 다양한 항법장치가 필요하고, 해양사고 발생 시 사고원인을 분석하기 위한 기능이 필요하다. 그러나 기존 상선 및 수상레저용 개별 항법 장치는 고가, 대용량 전원공급, 조작의 어려움, 넓은 설치 공간의 필요 등의 문제점이 있다. 본 연구에서는 3축 반도체 가속도 센서와 3축 반도체 경사 센서 및 다양한 기상 측정 센서와 CCD 카메라, 방수 캡슐에 내장된 메모리 등을 이용한 소형 스마트 항법 장치(Multi-Tasking Integrated Navigation System, MINS)를 설계하였다. 기존에 개발된 다양한 기술과 상용 센서 등을 이용하면 MINS 개발이 가능함을 알았고, 이러한 MINS 개발에 필요한 시스템을 제안하였다.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2005.06a
• /
• pp.1429-1432
• /
• 2005

This work is towards the development of a low-cost, small-sized inertial navigation system(INS) which consists of 3 accelerometers, 3 semiconductor gyros and a magnetic compass sensor. This paper explains in detail the structure of the developed system and proposes a 3 dimensional attitude estimation algorithm with Indirect Kalman Filter. The experiments are performed with the developed system attached to a 6 DOF robot for showing the effectiveness of the algorithm.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.19 no.4
• /
• pp.30-36
• /
• 2011

Inertial navigation systems requires gravity model to compute gravity acceleration and its trajectory accuracy depends on the gravity model accuracy especially for a long range flight. The gravity model accuracy is important for satellite orbit prediction as well. The precision gravity model requires a precision coordinate transformation between inertial and Earth fixed coordinates. Precision gravity acceleration algorithms with a coordinate transform are studied and a computer program is developed. The effects of individual model components on trajectory error are analyzed.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 1996.11a
• /
• pp.1028-1032
• /
• 1996

Stabilization performance of a sight stabilization system can be improved by proper selection of control algorithm and mechanism. In that aspect, in this paper, effects of an inertia balancer are studied. Parameters of the inertia balancer were obtained from the governing equation by assuming there is no external force and friction. Simulation and experimental results show that the inertia balancer contributes significantly to the stabilization of the line of sight(LOS). In particular, it was found that the inertia balancer is more effective as frequency of the disturbance increases.

• Journal of Ocean Engineering and Technology
• /
• v.27 no.2
• /
• pp.93-99
• /
• 2013

This paper describes a robust algorithm for an integrated underwater navigation system based on VKF (velocity Kalman filter). The proposed approach relies on a VKF, augmented by the altitude from an echo-sounder-based switching architecture to yield robust performance, even when DVL (Doppler velocity log) exceeds the measurement range and the measured value cannot be valid. The proposed approach relies on three parts: 1) PINS (pure inertial navigation system), 2) VKF design, and 3) VKF-aided integrated navigation filter design. To evaluate the proposed method, we compare the results of the VKF-aided navigation system with the simulation result from a PINS and conventional INS-DVL method.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.191.2-191.2
• /
• 2012

저궤도 위성을 설계함에 있어 시스템 수준에서 수행하는 질량특성의 계산은 위성을 구성하는 각각의 구성품에 대한 정보를 종합하여 전체 시스템의 특성을 예측하는 작업이다. 질량특성에 대한 요구조건은 발사체로부터 설정되는데 요구조건 항목은 탑재체질량, 무게중심 그리고 관성모멘트에 관한 것이다 또한, 자세제어면에서 추력에 의한 토크에 따른 무게 중심 등이며 최근 위성의 고기동화 요구에 따라 기동요구조건 및 자세구동장치의 용량에 따라 결정된다. 특히 위성의 궤도형상 관성모멘트는 위성 동특성을 표시하므로 이를 사용하여 제어시뮬레이션을 수행하는 자세제어계에 주요 입력 데이터로 활용된다. 본 논문에서는 저궤도 위성의 질량특성 요구조건을 검증하기 위해 수행한 질량특성 예측과 질량특성 측정 시험에 대해서 기술하고자 한다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
• /
• 2010.05a
• /
• pp.144-147
• /
• 2010

본 연구에서는 실내의 활동추적 시스템을 위해 가속도센서와 지자계 센서를 이용하여 외부로부터 독립적인 소형의 관성항법장치를 제안하였다. 기존의 실내 위치추적은 주로 GNSS(global navigation satellite system)의 정보를 가져와 실내 환경에 맞게 초음파와 RSSI(received signal strength indicator)등을 이용하여 구성한 경우가 연구되었으나 이러한 위성항법은 좌표 값이 미리 저장된 고정 노드가 필수적이라는 단점이 있다. 따라서 본 연구에서는 실내 환경과 같이 이동거리가 길지 않으며, 기존 환경 및 외부로부터의 영향에서 자유로운 관성항법을 이용한 실내 활동추적시스템을 제안하였다. 이를 위해 지자계 센서와 3축 가속도 센서를 사용한 신호 계측부와 Zigbee기반의 무선 센서 네트워크를 이용한 무선 전송부를 구성하였으며, 계측된 데이터의 분석으로부터 실내 위치추적의 가능성을 평가하였다.

• Journal of the Korea Convergence Society
• /
• v.13 no.4
• /
• pp.307-313
• /
• 2022

The importance of engine vibration reduction is increasing as the vehicle interior noise becomes more serious due to higher output and lighten weight trends. Recently, the balance shaft attachment has been proposed as a representative method for the engine vibration reduction. The balance shaft is a device that cancels the vibrations generated in the reciprocating motion of the piston and the conrod by using an arbitrary eccentric mass, and can improve fuel efficiency and ride comfort at the same time. This paper proposes the unbalance amount and shape of the balance shaft to induce and offset the inertia force generated by the engine structure. The proposed two-shaped balance shaft was implemented as an ADAMS multi-body dynamics model, and the reduction of the inertial force in the actual behavior was confirmed through dynamic simulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.5
• /
• pp.462-471
• /
• 2008

Flight recoder is used to analyze the accident factors and prevent the accident. In the analysis of the flight recorder, the most important factor is how to estimate the precise location of the flight. Traditional aviation navigation is based on stable sensors such as DME and VOR. In order to enhance the precision of the location estimation, the integrated navigation algorithm is designed to incorporate DME, Air data sensors and INS(Inertial Navigation System). The results demonstrate that the proposed algorithm can achieve better accuracy, comparing with the traditional navigation schemes, in flight location estimation.