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달 탐사선의 동역학 모델링 및 관성 모멘트 추정에 관한 연구
심상현 ( Sang Hyun Shim ),김광진 ( Kwang Jin Kim ),이상철 ( Sang Chul Lee ),고상호 ( Sang Ho Ko ),류동영 ( Dong Young Rhyu ),주광혁 ( Gwang Hyeok Ju ) 한국항공운항학회 2010 한국항공운항학회지 Vol.18 No.4
This paper deals with attitude determination and parameter estimation problems for a lunar module. For this we first derive equations of motion for the lunar module by considering allocation locations (configurations) of reaction thruster and a reaction wheel assembly. The lunar module is assumed as a rigid body. In order to include the effect of fuel sloshing on the dynamics of the lunar module, we model it as a spherical pendulum for a simple analysis. For estimating angular rates and moment of inertia of the module, we employ an extended Kalman filter and the least mean square algorithms, respectively. Finally we construct a dynamical model for the lunar module by combining all these elements.
조상훈 ( Sang Hoon Jo ),강승은 ( Seung Eun Kang ),강자영 ( Ja Young Kang ),고상호 ( Sang Ho Ko ) 한국항공운항학회 2012 한국항공운항학회지 Vol.20 No.3
The recent transition to Performance Based Navigation in aviation enhances the accuracy of aircraft position, safety and efficiency in air traffic operations by using satellite-based navigation system such as GNSS. However, intentional interferences with GNSS signal as well as ones coming from natural phenomena such as solar storm increase. GNSS have very low power and therefore their signals are more susceptible to interferences than ground-based navigation signals. This paper introduces requirements of alternative positioning, navigation and timing(APNT) system and relevant technologies when the GNSS signals are not valid.
한국형 달탐사선 개발을 위한 탐사선의 자세제어 및 항법 기술에 관한 현황 연구
권순규,김우성,고상호,이상철,류동영,주광혁,Kwon, Soon-Kyu,Kim, Woo-Sung,Ko, Sang-Ho,Lee, Sang-Chul,Rew, Dong-Young,Ju, Gwang-Hyeok 항공우주시스템공학회 2010 항공우주시스템공학회지 Vol.4 No.3
After the first successful Apollo program, many countries around the world launched their own programs for exploring the moon. This paper surveys various navigation and attitude control systems of several past lunar exploration programs for the purpose of preparing a program for the first Korean lunar probe. For this first we investigate successful programs by introducing the sensors and actuators used for these programs, particularly focusing on those of Clementine and SMART-1 of USA and EU, respectively. Then based on the study, we suggest the necessary components of navigation and attitude control systems suitable for our lunar probe program.
초음속 그리드핀 3차원 유동해석을 통한 단위 그리드핀 개념의 타당성 연구
이형진(Hyeong Jin Lee),고상호(Sang Ho Ko),강태곤(Tae Gon Kang),이열(Yeol Lee) 한국항공우주학회 2021 韓國航空宇宙學會誌 Vol.49 No.8
SpaceX Falcon 9에 탑재된 초음속 그리드핀 유동 특성에 관한 3차원 수치해석이 수행되었다. 3차원 수치해석 결과를 기준으로 관련 수치해석 과정의 단순화와 효율성 향상을 위하여 과거 도입된 단위 그리드핀 접근의 타당성이 평가되었다. 아울러 마하수 2.8 초음속 비행조건에서 다양한 받음각을 갖는 SpaceX Falcon 9 그리드핀의 공력특성이 평가되었다. Three-dimensional numerical study was carried out to evaluate the aerodynamic characteristics of the supersonic grid fins installed on SpaceX Falcon 9. The present three-dimensional flow results were compared to the results by the concept of the unit grid fin previously introduced for more efficient and simpler flow calculations, and the validity of the approach of the unit grid fin were evaluated. The aerodynamic characteristics in supersonic flights Mach 2.8 of SpaceX Falcon 9 with various angle of attacks were also obtained.
강자영 ( Ja Young Kang ),이상철 ( Sang Chul Lee ),고상호 ( Sang Ho Ko ) 한국항공운항학회 2009 한국항공운항학회지 Vol.17 No.2
The problem of establishing weapon system safety especially during the development process has been one of the very important fields related with public safety in advanced countries such as USA, UK and so on. These countries have launched strong policies on system safety to reduce the chance of accidents. However, the Republic of Korea (ROK) has limited experiences and application of the system safety on domestically produced weapon systems. Therefore, it is imperative that the government starts a comprehensive and systematic policy on system safety to reduce the occurrence of potential accidents during the development of weapon systems. In this paper, we analyze system-level activities needed through the life-cycle of the weapon systems and provide a suggestion for application of the system safety.
論文(논문) : 달 착륙선 지상시험모델의 경로 추종을 위한 추력기 기반 제어기 설계
김광진 ( Kwang Jin Kim ),이정숙 ( Jeong Sook Lee ),이상철 ( Sang Chul Lee ),고상호 ( Sang Ho Ko ),류동영 ( Dong Young Rhyu ),주광혁 ( Gwang Hyeok Ju ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.4
Lunar exploration program has been prepared with the aim of launch in the 2020`s. As part of it, a lunar lander demonstrator has been developed which is the model for verifying all the system, such as structure, propulsion and control system before launch to deep space. After verifying all the system, the demonstrator will be evaluated by flight test. This paper deals with path tracking controller based on thrusters for the demonstrator. For this, first we derive equations of motion according to the allocation of thrusters and design the path tracking controller. The signal generated from the controller is continuous so PWPF(Pulse-Width Pulse-Frequency) modulator is adopted for generating on/off signal. Finally MATLAB simulation is performed for evaluating the path tracking ability and the final landing velocity.
상호작용 다중모델-무향 칼만필터 기반 공대공 기관포 정밀 타격 성능 향상 기법에 관한 연구
한승우(Seung-woo Han),김종섭(Chong-sup Kim),고기옥(Gi-oak Koh),고상호(Sang-ho Ko) 한국항공우주학회 2023 韓國航空宇宙學會誌 Vol.51 No.3
본 논문에서는 공대공 근접 교전 상황에서 기관포의 정밀 타격 성능 향상을 위한 신호처리 기법에 관한 연구를 수행한다. 목표 항공기의 상태 추정 시 단일모델을 사용한 경우와 다중모델을 병렬로 사용한 경우 발생하는 추정 오차를 비교하고 분석한다. 결과적으로 상호작용 다중모델 기법과 무향 칼만필터를 활용하여 기동하는 목표 항공기의 상태를 추정한다. 또한 목표 항공기의 정밀 타격을 위한 가상추적점 생성 기법을 제안한다. 가상추적점을 추종하기 위한 비행제어시스템을 구현하고 기관포를 활용한 목표 항공기 정밀 타격 시뮬레이션을 수행하여 임무 수행 능력과 생존성 향상을 확인한다. This paper describes a signal processing technique to improve the precision aiming performance in close range air-to-air combat. We compare and analyze the state estimation error that occurs when a single model is used or multiple models are used parallel. As a result, the state of the target aircraft is estimated using Interactive Multiple Model method and Unscented Kalman Filter. Also a method to generate virtual pursuit point (VPP) for precision aiming is proposed. Finally, the flight control system is designed to pursuit VPP and close range air-to-air pursuit simulation is performed to evaluate the mission performance and viability.
대기요소 고려를 통한 무인항공기 비행시험계획 수립에 대한 연구
김영래 ( Yeong Rae Kim ),이정숙 ( Jeong Suk Lee ),이상철 ( Sang Cheol Lee ),고상호 ( Sang Ho Ko ),강자영 ( Ja Yeong Kang ),최종욱 ( Jong Uk Choi ),성덕용 ( Deoky Yong Seong ) 한국항공운항학회 2010 한국항공운항학회지 Vol.18 No.4
Flight test is the final and a mandatory process for the development of unmanned aerial vehicles(UAVs) as well as manned. Since most UAVs fly in a low speed and are prone to adverse weather conditions such as air turbulence, atmospheric weather environment around flight test regions will be a critical item to be considered for a flight test planning for UAVs. In this paper, we suggest a decision method for a UAV flight test schedule based on weather conditions of surface and upper atmospheres and also introduce a program for an effective flight test planning through weather forecasts.
소형 무인항공기용 이동표적 표시기법에 대한 기술 동향 분석
윤승규(Seung Gyu Yun),강승은(Seung Eun Kang),고상호(Sang Ho Ko) 한국항공우주학회 2014 韓國航空宇宙學會誌 Vol.42 No.7
본 논문에서는 소형무인항공기용 이동표적 표시기법(MTI, Moving Target Indication)에 대한 기술 동향분석을 하였다. MTI는 크게 이미지 정렬과 차영상 오류보정 단계로 구성되는데 이중 이미지 정렬 기법에는 매개변수방식과 비매개변수방식이 있으며 본 논문에서는 매개변수방식을 사용한 이용한 MTI에 초점을 맞췄다. 소형무인항공기의 경우, 저고도 운용에 의한 시차문제가 발생하는데 이를 보정하기 위해서 등극기하학이 사용된다. MTI의 성능을 향상시키기 위한 관련기법들도 살펴보았으며 향후 발전방향을 제시하였다. In this paper, we survey the Moving Target Indication(MTI) techniques for small UAVs. MTI consists of image alignment phase and frame differencing correction phase, and image alignment has two ways of parametric approach which is mainly focused in this paper and non-parametric approach. Since small UAVs are operated in the low altitude, the parallax is considerable and the epipolar geometry is applied to compensate the parallax. The related works and future works are presented.