• 한국항공우주학회지
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• 제45권4호
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• pp.318-327
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• 2017

최근 날씨와 주야 조건에 상관없이 지구 관측을 수행할 수 있는 영상레이더 탑재체가 활발하게 연구되고 있다. 한국항공우주연구원은 2013년 한국 최초의 영상레이더 위성인 다목적실용위성5호를 성공적으로 개발 및 발사하였으며 현재 영상레이더 차세대 시리즈 위성인 다목적실용위성6호를 개발하고 있다. 본 논문은 영상레이더 탑재체의 설계와 분석을 위하여 필수적인 영상레이더 탑재체 시스템 성능 분석 시뮬레이터의 개발에 관한 것이다. 시스템 성능 분석 시뮬레이터는 안테나 패턴 생성 시뮬레이터와 시스템 성능 분석 시뮬레이터, 그리고 영상 품질 분석 시뮬레이터로 이루어진다. 영상레이더시스템 성능 분석 시뮬레이터의 시뮬레이션 결과로부터 영상레이더 설계 단계에서 위성용 영상레이더 탑재체의 설계 및 분석 툴로써 적용 가능할 것으로 기대한다.

• Journal of Astronomy and Space Sciences
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• 제30권4호
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• pp.279-290
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• 2013

Due to the continuous space development by mankind, the number of space objects including space debris in orbits around the Earth has increased, and accordingly, difficulties of space development and activities are expected in the near future. In this study, among the stages for space debris removal, the implementation of a vision-based approach technique for approaching space debris from a far-range rendezvous state to a proximity state, and the ground test performance results were described. For the vision-based object tracking, the CAM-shift algorithm with high speed and strong performance, and the Kalman filter were combined and utilized. For measuring the distance to a tracking object, a stereo camera was used. For the construction of a low-cost space environment simulation test bed, a sun simulator was used, and in the case of the platform for approaching, a two-dimensional mobile robot was used. The tracking status was examined while changing the position of the sun simulator, and the results indicated that the CAM-shift showed a tracking rate of about 87% and the relative distance could be measured down to 0.9 m. In addition, considerations for future space environment simulation tests were proposed.

• 한국항공운항학회지
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• 제17권1호
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• pp.9-16
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• 2009

The analysis of an aircraft flight dynamics is recently very convenient because of the introduction of state-space method and a well-developed package software. The representation of a dynamic system is described as a simple form of matrix calculation and the unique form of model is available for the linear or nonlinear, time variant or time invariant, mono variable or multi variable system with state-space method. And this analysis can be simplified with the specific functions of a package software and it is very simplified to execute the simulation of the dynamic characteristics for an aircraft model with an interactive graphical treatment. The purpose of this study is to develope an educational flight simulator for the students who need to analyze the dynamic characteristics of an aircraft that is primarily to execute the simulation for the analysis of the transient response and frequency response of an aircraft stability. Furthermore the dynamic characteristics of an aircraft motion is set up as dynamical animation tool for the control response on 3-axis motions of an aircraft.

• 천문학회보
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• 제42권2호
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• pp.51.3-51.3
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• 2017

We present a general N-body exoplanet simulator in anticipation of upcoming next generation telescopes. Illustrative examples are presented on P-type orbits in stellar binary stellar systems, that should be fairly common as in Kepler 16AB. Specific attention is paid to reduced orbital lfetimes of exoplanets in the habitable zone by the stellar binary, known from Dvorak (1986).

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2007년도 한국우주과학회보 제16권2호
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• pp.64-64
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• 2007

• 한국항공우주학회지
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• 제39권1호
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• pp.69-75
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• 2011

우리나라는 우주 개발의 일환으로 달 탐사를 위한 달 탐사선과 달 착륙선의 발사를 계획하고 있다. 향후 멀티미디어 기반의 달 탐사 정보를 전송하기 위해서는 대용량 Telemetry 데이터를 전송하기 위한 통신 시스템을 구축하는 것이 필요하다. CCSDS 표준에서는 신뢰성 있는 원거리 심우주 통신 시스템을 위한 ARQ 기법으로 Deferred NAK mode를 권고하고 있다. 본 논문에서는 달 탐사선과 지상국 및 우주 환경 모델을 반영하여 Deferred NAK mode 통신 시스템 시뮬레이터를 구현하며, 시뮬레이터에는 대용량 Telemetry 데이터를 전송하기에 적합한 변조 방식과 터보 부호화 기법을 사용한다. 시뮬레이션을 통해 Telemetry 데이터의 전송 성능을 분석한다.

• 항공우주시스템공학회지
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• 제18권1호
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• pp.88-98
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• 2024

본 논문에서는 디지털 지형 고도 데이터를 이용한 자동 지형 추종 시뮬레이터를 제안하였다. ATF Simulator는 Flight Simulator, Radar Simulator, TFC Simulator로 구성하였다. 지형 추종에 필요한 지형 정보로 디지털 지형 고도 데이터와 디지털 지형 고도 데이터를 이용하여 생성한 레이다 스캔 데이터를 활용하였다. ATF Simulator는 디지털 지형 고도 데이터를 이용하는 Passive mode, 레이다 스캔 데이터를 이용하는 Active mode, 두 가지 모두 이용하는 Hybrid mode로 세 가지 운용모드를 제공한다. LabVIEW 개발 환경과 MATLAB App Designer 개발 환경을 통해 지형 추종 시스템 개발에 소요되는 비용 및 시간을 줄일 수 있는 ATF Simulator를 개발하였으며 기능요구사항을 충족하는지 확인하여 검증하였다.

• ETRI Journal
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• 제27권2호
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• pp.140-152
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• 2005

In this paper, we present design features, implementation, and validation of a satellite simulator subsystem for the Korea Multi-Purpose Satellite-2 (KOMPSAT-2). The satellite simulator subsystem is implemented on a personal computer to minimize costs and trouble on embedding onboard flight software into the simulator. An object-oriented design methodology is employed to maximize software reusability. Also, instead of a high-cost commercial database, XML is used for the manipulation of spacecraft characteristics data, telecommand, telemetry, and simulation data. The KOMPSAT-2 satellite simulator subsystem is validated by various simulations for autonomous onboard launch and early orbit phase operations, anomaly operation, and science fine mode operation. It is also officially verified by successfully passing various tests such as the satellite simulator subsystem test, mission control element system integration test, interface test, site installation test, and acceptance test.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2009년도 한국우주과학회보 제18권2호
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• pp.46.3-46.3
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• 2009

The SAR (Synthetic Aperture Radar) satellite has the advantage of implementing the imaging mission even though it is night time, cloudy weather, and all weather conditions, which is different from the satellite with the optical payload. This is the reason why the SAR satellite comes into the spotlight in the observation satellite field. The Korea Aerospace Research Institute (KARI) has been developing the first Korean SAR satellite and is currently integrating and testing the Flight Model. For the launch vehicle service, KARI finalized the selection of the launch vehicle service provider and finished Critical Design Review (CDR) of the interface between the bus and the launch vehicle. KARI and launch vehicle service provider also finished the test of the telemetry interface between the bus and the launch vehicle. The test of the telemetry interface has the purpose of checking the interface of the telemetry which is the SOH(State-of-Health) of the satellite in an early launch stage. For this test, KARI has finished the development of the spacecraft simulator which is composed of the bus simulator to generate the analog telemetry and the launch vehicle simulator to gather the telemetry. In this research, the result of the hardware implementation and the software implementation for the spacecraft simulator were described. Finally the results of the launch vehicle telemetry MUX test which were performed at the launch vehicle provider's design office by using the spacecraft simulator were summarized. It is expected that this simulator will be used in the next test after the manufacture of the launch vehicle.

• Journal of Power Electronics
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• 제14권3호
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• pp.444-457
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• 2014

This paper presents the design and realization of a digital PV simulator with a Push-Pull Forward (PPF) circuit based on the principle of modular hardware and configurable software. A PPF circuit is chosen as the main circuit to restrain the magnetic biasing of the core for a DC-DC converter and to reduce the spike of the turn-off voltage across every switch. Control and I/O interface based on a personal computer (PC) and multifunction data acquisition card, can conveniently achieve the data acquisition and configuration of the control algorithm and interface due to the abundant software resources of computers. In addition, the control program developed in Matlab/Simulink can conveniently construct and adjust both the models and parameters. It can also run in real-time under the external mode of Simulink by loading the modules of the Real-Time Windows Target. The mathematic models of the Push-Pull Forward circuit and the digital PV simulator are established in this paper by the state-space averaging method. The pole-zero cancellation technique is employed and then its controller parameters are systematically designed based on the performance analysis of the root loci of the closed current loop with $k_i$ and $R_L$ as variables. A fuzzy PI controller based on the Takagi-Sugeno fuzzy model is applied to regulate the controller parameters self-adaptively according to the change of $R_L$ and the operating point of the PV simulator to match the controller parameters with $R_L$. The stationary and dynamic performances of the PV simulator are tested by experiments, and the experimental results show that the PV simulator has the merits of a wide effective working range, high steady-state accuracy and good dynamic performances.