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추력벡터제어 비행체의 일관된 탄도 성형을 위한 피치각명령 산출 방법
이용인,최동균,황태원,Lee, Yong-In,Choe, Dong-Gyun,Hwang, Tae-Won 한국군사과학기술학회 2013 한국군사과학기술학회지 Vol.16 No.6
In this paper, we propose a method of generating pitch commands for consistent initial trajectories irrelevant to flight conditions in the initial boosting phase of a thrust-vector-controlled vehicle. After shape assumption of the pitch command profile, parameters of the profile are determined in real time in order for the summit height of the trajectory to be a desired value by deriving the summit height considering thrust performance, gravity, and other flight conditions. Computer simulation results demonstrate good performance of the proposed method.
이용인,조성진,최동균,Lee, Yong-In,Cho, Sungjin,Choe, Dong-Gyun 한국군사과학기술학회 2015 한국군사과학기술학회지 Vol.18 No.6
In this paper, an in-flight prediction method of thrust profiles for solid rocket motors is proposed. Actually, it is very difficult to have detailed information about the performance of the rocket motors beforehand because it is quite sensitive to combustion environments. To overcome this problem, we have developed an algorithm for generating in-flight prediction of rocket motor performance in realistic environments via a reference burnback profile and accelerations measured at a short time-interval just after launch. The performance is evaluated through a lot of flight test results.
3자유도 추력방향제어용 노즐의 2측 제어시 유발되는 커플링 보상 알고리듬
조성진(Sungjin Cho),김승환(Seung-Hwan Kim),최동균(Dong-Gyun Choe),김을곤(Eulgon Kim) 대한전기학회 2009 정보 및 제어 심포지엄 논문집 Vol.2009 No.10
3자유도를 갖는 추력방향제어(Thrust Vector Control: TVC) 노즐을 2축으로 제어하기 위해서는 롤 회전 방지 장치가 필요하거나 이를 고려한 알고리듬이 필요하다. 본 논문에서는 롤 회전을 고려한 알고리듬을 적용할 경우, 2축에 장착된 구동기의 응답 속도 불균형에 의해 유발되는 커플링을 보상하는 알고리듬에 대해 제안한다. 제안된 알고리듬은 모의시험 결과를 통해 이에 대한 타당성을 검증한다.
황익호(Ick-Ho Whang),조성진(Sungjin Cho),최동균(Dong-Gyun Choe) 대한전기학회 2010 대한전기학회 학술대회 논문집 Vol.2010 No.7
Waypoint guidance is one of the most widely used guidance algorithm to make UAV(unmanned air vehicle) follow desired path. In this paper, we consider a waypoint guidance strategy consisting of line followings and line changes. In the strategy, the UAV is guided to follow the reference trajectory made up of sequently connected line segments. Since [1] already proposed a guidance law to make line following, we proposed an optimal scheme to find the reference line change point. We introduce a linear time invariant system to approximate the closed loop response of the line following guidance loop, and a new optimal strategy for reference line change is proposed based on the approximated system. Simulations are carried out to demonstrate the proposed method.