• Journal of Positioning, Navigation, and Timing
• /
• 제9권4호
• /
• pp.357-366
• /
• 2020

This paper addressed a relative navigation method for autonomous rendezvous and docking of cube-satellites using single frequency Differential GPS (DGPS) under the intermittent communication between satellites. Since the ionospheric error of GPS measurement is variable depending on the visible satellites, a few meters error of relative navigation is occurred in the Low-Earth Orbit (LEO) environment. Therefore, it is essential to remove the ionospheric error to perform relative navigation. Besides, an intermittent communication period for receiving GPS measurements of the target satellite is limited for getting information every sampling time. To solve this problem, a method combining range domain DGPS and orbit propagation is proposed in this paper. The proposed method improves the performance of DGPS by using Hatch filter and solves an intermittent communication problem by estimating the relative position and velocity using Hill-Clohessy-Wiltshire Equation. Through the simulation, it is verified that the suggested algorithm provides the relative position error within RMS 0.5 m and the relative velocity error within RMS 3 cm/s. Furthermore, it has the advantage that it is suitable for real-time implementation using single-frequency GPS measurements and is computationally efficient.

• 한국전자파학회논문지
• /
• 제21권6호
• /
• pp.642-650
• /
• 2010

본 논문에서는 주어진 임무에 대한 저궤도 위성용 TT&C(Telemetry Tracking and Command system) 안테나를 설계하기 위해 먼저 링크 버짓을 통해 요구 성능을 도출하고, 이에 따라 안테나를 설계한다. 전제된 임무 궤도는 태양 동기 원형 궤도이며, 지구 및 우주 관측 임무를 수행한다. TT&C 시스템의 링크 버짓을 설계하여 최소 3dB 마진을 가지기 위한 안테나의 요구 이득과 빔 폭을 도출하였으며, 이렇게 설계된 위성용 TT&C 안테나는 넓은 빔 폭을 가지는 원형 편파 턴스타일 안테나이다. 한편, 안테나를 위성에 설치하였을 때 방사 특성의 변화를 확인하였으며, 최적의 설치 위치를 제안하였다. 또한 설계된 턴스타일 안테나의 전기적 성능을 바탕으로 TT&C링크 모의실험을 통해 임무 중 안테나의 성능을 검증한다.

• 한국항공우주학회지
• /
• 제39권5호
• /
• pp.466-473
• /
• 2011

인공위성의 열제어는 인공위성이 운용궤도상에서 겪는 고진공, 극한의 온도변화 환경에서 위성 구성품의 온도변화를 허용한계 온도 범위 내에서 유지하는데 목적이 있다. 본 연구에서는 저궤도 관측위성(LEO)의 광학탑재체에 대한 열해석 과정으로 열진공 시험 조건, 열진공 챔버의 형상, 위성 탑재체 내부의 열적 환경을 고려하여 열해석 모델을 구성하고 궤도 조건에 따른 열해석을 수행하였다. 또한 광학탑재체의 지상 열진공 시험 조건에 따른 열해석 수행하여 열진공 시험을 위한 시험조건을 정립하였다.

• 해양환경안전학회:학술대회논문집
• /
• 해양환경안전학회 2006년도 추계학술발표회
• /
• pp.181-186
• /
• 2006

정지궤도위성은 태양 궤도위성과는 달리 넓은 지역의 매시간 측정이 가능하다. 정지 위성은 관측영역은 항상 고정되어 있으나 태양의 위치가 항상 변하므로 한 주어진 지점의 해수 신호의 크기는 기간에 따라 변하게 된다. 반면에 태양 궤도 위성은 하루 통일한 시간대에서 동일한 영역을 촬영하기 때문에 신호의 크기의 변화가 없다. 즉, 정지해양 위성에서 관측된 신호의 크기는 태양과 위성이 항상 수직 방향에 위치한다고 가정할 때 얻어지는 신호의 크기로 변경되어야한다. 이와 같은 신호의 보정은 지속적으로 변화하는 태양, 위성과 관측점의 기하학적인 위치변화에 따라 나타나게 되는데 이를 양방향 계수 (Bidirectional Factor) 라고 한다. 본 연구에서는 태양의 위치와 기하학적인 요인을 계산, 대기권 밖의 총 방사휘도와 반사율을 계산하였다. 그리고 양방향계수, 즉 관측점과 관측지점 사이의 규격화된 해면방사휘도$([L_W]_N)$의 비를 모의실험을 통해 확인하였다. 1년간의 값을 영상화 하였고 보다 정확한 양방향 계수 (Bidirectional Factor)를 얻기 위해 다양한 조건의 모의실험의 필요성을 제시하였다.

• Journal of Astronomy and Space Sciences
• /
• 제14권1호
• /
• pp.158-165
• /
• 1997

The Sun interference event predictions for the KOMPSAT TT&C station were performed to analyze the frequency of the event and the impact on the TT&C link. The KOMPSAT orbit was propagated including only J2 geopotential term for maintaining the Sun-synchronism and no other perturbations were included. Local time of ascending node of the KOMPSAT satellite was set to 10h50m00s. The TT&C station was assumed to locate in Taejon and have 9 meter antenna for S-band link. One year of simulation from 1999/07/01 were performed out of 3 year of mission lifetime of KOMPSAT satellite. Total four times of Sun interference events were occurred during 1 year of simulation and those lasted about 50 seconds altogether. The C/N degradation of the TT&C system was calculated about 4dB. The Sun interference event of 50 seconds of year are 0.0076 percents of the S-band contact time when the 30 minute of contact time is assumed in a day.

• Journal of Astronomy and Space Sciences
• /
• 제27권4호
• /
• pp.337-343
• /
• 2010

Optical observation system provides angle-only measurement for orbit determination of space object. Range measurement can be directly acquired using laser ranging or tone ranging system. Initial orbit determination (IOD) by using angle- only data set shows discrepancy according to the measurement time interval. To solve this problem, range measurement data should be added for IOD. In this study, two-site optical observation was used to derive the range information. We have observed nine geostationary earth orbit satellites by using two-site optical observation system. The determination result of the range shows the accuracy over 99.5% compared to the results from the satellite tool kit simulation. And we confirmed that the orbit determination by the Herrick-Gibbs method with the range information obtained from the two-site observation is more accurate than the orbit determination by Gauss method with the one-site observation. For more accurate two-site optical observation, a baseline should satisfy an optimal condition of length and more precise observation system needed.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 2003년도 ICCAS
• /
• pp.1465-1469
• /
• 2003

In general satellite verification process, the AOCS (Attitude & Orbit Control Subsystem) should be verified through several kinds of verification test which can be divided into two major category like FBT (Fixed Bed Test) and polarity test. And each test performed in different levels such as ETB (Electrical Test Bed) and satellite level. The test method of FBT is to simulate satellite dynamics with sensors and actuators supported by necessary environmental models in ETB level. The VDS (Vehicle Dynamic Simulator) try to make the real situation as possible as the on-board processor will undergo after launch. The purpose of FBT test is to verify that attitude control logic function and hardware interface is designed as expected with closed loop simulation. The VDS is one of major equipments for performing FBT and consists of software and hardware parts. The VDS operates in VME environments with target board, several commercial boards and custom boards based on the VxWorks real time operating system. In order to make time synchronization between VDS and satellite on-board processor, high reliable semaphore was implemented to make synchronization with the interrupt signal from on-board processor. In this paper, the real-time operating environment used on VDS equipment is introduced, and the hardware and software configurations of VDS summarized in the systematic point of view. Also, we try to figure out the operational concept of VDS and AOCS verification test method with close-loop simulation.

• Journal of Astronomy and Space Sciences
• /
• 제28권4호
• /
• pp.319-332
• /
• 2011

The objectives of this study are to analyze the satellite visibility at the randomly established ground sites, to determine the five optimal ground sites to perform the optical surveillance and tracking of domestic satellites, and to verify the acquisition of the optical observation time sufficient to maintain the precise ephemeris at optimal ground sites that have been already determined. In order to accomplish these objectives, we analyzed the visibility for sun-synchronous orbit satellites, low earth orbit satellites, middle earth orbit satellites and domestic satellites as well as the continuous visibility along with the fictitious satellite ground track, and calculate the effective visibility. For the analysis, we carried out a series of repetitive process using the satellite tool kit simulation software developed by Analytical Graphics Incorporated. The lighting states of the penumbra and direct sun were set as the key constraints of the optical observation. The minimum of the observation satellite elevation angle was set to be 20 degree, whereas the maximum of the sun elevation angle was set to be -10 degree which is within the range of the nautical twilight. To select the candidates for the optimal optical observation, the entire globe was divided into 84 sectors in a constant interval, the visibility characteristics of the individual sectors were analyzed, and 17 ground sites were arbitrarily selected and analyzed further. Finally, five optimal ground sites (Khurel Togoot Observatory, Assy-Turgen Observatory, Tubitak National Observatory, Bisdee Tier Optical Astronomy Observatory, and South Africa Astronomical Observatory) were determined. The total observation period was decided as one year. To examine the seasonal variation, the simulation was performed for the period of three days or less with respect to spring, summer, fall and winter. In conclusion, we decided the optimal ground sites to perform the optical surveillance and tracking of domestic satellites and verified that optical observation time sufficient to maintain the precise ephemeris could be acquired at the determined observatories.

• 한국위성정보통신학회논문지
• /
• 제1권2호
• /
• pp.76-82
• /
• 2006

한국전자통신연구원이 개발하여 항공우주연구원의 관제소에 설치한 아리랑2호 위성 관제시스템은 지난 7월 28일 발사된 아리랑2호 위성의 운용에 사용되고 있다. 아리랑2호 관제시스템의 대표적인 기능으로는 원격측정데이터 수신 및 처리, 원격명령 생성 및 송신, 위성 추적 및 거리측정, 궤도 예측 및 결정, 위성자세 조정계획, 그리고 위성 시뮬레이션 등이 있다. 아리랑2호 위성은 아리랑1호 위성의 임무를 이어받아 수행하며, MSC (Multi Spectral Camera) 및 정밀궤도결정, 정밀자세결정 등을 통해 아리랑1호에 비해 훨씬 향상된 해상도의 사진을 제공하는 성능을 가지고 있다.

• ETRI Journal
• /
• 제44권6호
• /
• pp.955-965
• /
• 2022

A low Earth orbit (LEO) satellite constellation could be used to provide network coverage for the entire globe. This study considers multi-beam frequency reuse in LEO satellite systems. In such a system, the channel is time-varying due to the fast movement of the satellite. This study proposes an efficient power and bandwidth allocation method that employs two linear machine learning algorithms and take channel conditions and traffic demand (TD) as input. With the aid of a simple linear system, the proposed scheme allows for the optimum allocation of resources under dynamic channel and TD conditions. Additionally, efficient projection schemes are added to the proposed method so that the provided capacity is best approximated to TD when TD exceeds the maximum allowable system capacity. The simulation results show that the proposed method outperforms existing methods.