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성재민(Jaemin Sung),김병수(Byoung Soo Kim) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.5
본 논문은 회전안정성을 갖는 탄도수정탄의 대기속도 추정을 위한 필터 설계에 대하여 설명한다. 대상 시스템은 운용상의 제약(공간, 파워)으로 인하여, 대기속도 측정을 위한 센서를 사용할 수 없다. 따라서 한정된 센서를 이용한 대기속도 추정이 필요하다. 따라서 본 연구에서는 IMU(가속도계, 자이로)에서 측정하는 3축 가속도와 각속도 데이터만 이용하여, 대기속도 추정을 위한 필터를 설계하였다. 대상 시스템의 경우, 넓은 속도, 고도의 운용범위를 커버하기 위한 추정 필터가 필요하므로 본 연구에서는 확장 칼만필터를 설계하여 기존의 연구와의 차별성을 두었다. 확장 칼만필터 설계를 위한 자코비안 행렬은 NRF(No-roll frame)에서의 간략화된 선형모델을 이용하여 구성하였다. 최종적으로 센서 오차와 바람 모델을 포함한 시뮬레이션을 통해 그 성능을 검토하였다. 이때, 시뮬레이션은 설계한 대기속도와 각속도 모델 오차의 영향을 분석하기 위하여 네 가지 경우의 프로세스 공분산 행렬 값에 대한 영향을 분석하였다. This paper represents a filter design to estimate the airspeed of a spin-stabilized, trajectory-correctible artillery ammunition. Due to the limited power and space in operational point of view, the airspeed sensor is not installed, and thus the airspeed need to be estimated using limited sensor measurements. The only IMU measurements(three-axis specific forces and angular rates) are used in this application. The extended Kalman filter algorithm is applied since a linear filter can not cover the its wide operational range in airspeed and altitude. In the implementation of the EKF, the state and measurement equations are transformed into the no-roll frame for simple form of Jacobian matrix. The simulation study is conducted to evaluate the performance of the filter under various environment conditions of sensor noise and wind turbulence. In addition, the effect of the choice in filter design parameters, i.e. process error covariance matrices is analyzed on the performance of the estimation of airspeed and angular rates.
신경회로망 기반 미사일 적응제어기의 모델 불확실 상황에 대한 시뮬레이션 연구
성재민(Jaemin Sung),김병수(Byoung Soo Kim) 제어로봇시스템학회 2010 제어·로봇·시스템학회 논문지 Vol.16 No.4
This paper presents the design of a neural network based adaptive control for missile. Acceleration of missile by tail fin control cannot be controllable by DMI (Dynamic Model Inversion) directly because it is non-minimum phase system. To avoid the non-minimum phase system, dynamic model inversion is applied with output-redefinition method. In order to evaluate performance of the suggested controllers we selected the three cases such as control surface fail, control surface loss and wing loss for model uncertainty. The corresponding aerodynamic databases to the failure cases were calculated by using the Missile DATACOM. Using a high fidelity 6DOF simulation program of the missile the performance was evaluates.
김종섭(Chong-sup Kim),성재민(Jaemin Sung),양인석(Inseok Yang),강명수(Myungsoo Kang),조인제(In-je Cho) 제어로봇시스템학회 2017 제어·로봇·시스템학회 논문지 Vol.23 No.9
In this paper, a nonlinear control technique for a high-performance fighter aircraft is considered. To increase survivability by adopting super-maneuver abilities, nonlinear flight characteristics must be considered while designing the control system. For many leading aerospace industries, nonlinear dynamic inversion (NDI) is considered as a suitable nonlinear control technique for fighter aircrafts, since it reflects nonlinear characteristics directly. In this paper, NDI is considered as the primary controller for a high-performance trainer. By analyzing the research and flight test examples of NDI for various aircrafts, the design methodology for the trainer is proposed. The efficiency of the NDI controller is verified using the piloted handling qualities simulator (HQS) results.
오세율(Seyool Oh),성재민(Jaemin Sung),김종섭(Chong-Sup Kim),조인제(Inje Cho) 한국항공우주학회 2016 한국항공우주학회 학술발표회 논문집 Vol.2016 No.4
본 논문에서는 최신의 전투기 적용된 제어법칙을 소개할 것이다. 특히 F-35전투기에 적용된 비선형 동적 역변환에 대해 살펴볼 것이다. 또한 기존의 T-50에 적용된 전통적인 제어법칙과의 차이를 간단히 살펴볼 것이다. 그리고 현재 개발중인 F-16이상의 중급 전투기인 한국형 전투기(KFX) 항공기는 두 개의 수직꼬리날개가 장착되어 조종면이 증가하고, 두 개의 엔진이 장착되어 T-50과 형상이 다르다. 그리고, 조종면을 활용하는 제동기 등을 사용하는 기술이 사용가능성이 있기 때문에 T-50과는 달리 새로운 제어법칙에 대한 연구가 필요하다. 이 논문에서는 또한 현재 개발중인 한국형 전투기(KFX)에 선진제어법칙을 적용가능성을 알아보고자 한다. This paper introduces the advanced control laws which were applied to new advanced combat aircraft. Specifically, advanced technology of nonlinear dynamic inversion on the F-35 “Joint Strike Fighter” aircraft was reviewed in detail. The paper further includes a comparison between the F-35 and its advanced control laws to the T-50 “Golden Eagle” aircraft with its classical control laws. The KFX advanced multirole fighter (intended to outperform the aging F-16 multirole fighter aircraft) has two vertical stabilizers and rudders as well as two engines compared to the F-16’s one. As a result, the number of available control variables is increased in lateral directional modes. Study on advanced control laws is necessary to exploit the capability of a virtual speed brake using the increasing number of control surfaces. This study explores these advanced control laws and shows the future development direction of advanced control laws for the KFX program.
기존제어기와 신경회로망의 혼합제어기법을 이용한 미사일 적응 제어기 설계
최광찬(Kwang Chan Choi),성재민(Jaemin Sung),김병수(Byoung Soo Kim) 제어로봇시스템학회 2008 제어·로봇·시스템학회 논문지 Vol.14 No.12
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.