• Journal of Astronomy and Space Sciences
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• 제38권1호
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• pp.65-82
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• 2021

For the vast majority of geostationary satellites currently in orbit, station keeping activities including orbit determination and maneuver planning and execution are ground-directed and dependent on the availability of ground-based satellite control personnel and facilities. However, a requirement linked to satellite autonomy and survivability in cases of interrupted ground support is often one of the stipulated provisions on the satellite platform design. It is especially important for a geostationary military-purposed satellite to remain within its designated orbital window, in order to provide reliable uninterrupted telecommunications services, in the absence of ground-based resources due to warfare or other disasters. In this paper we investigate factors affecting the robustness of a geostationary satellite's orbit in terms of the maximum duration the satellite's station keeping window can be maintained without ground intervention. By comparing simulations of orbit evolution, given different initial conditions and operations strategies, a variation of parameters study has been performed and we have analyzed which factors the duration is most sensitive to. This also provides valuable insights into which factors may be worth controlling by a military or civilian geostationary satellite operator. Our simulations show that the most beneficial factor for maximizing the time a satellite will remain in the station keeping window is the operational practice of pre-emptively loading East-West station keeping maneuvers for automatic execution on board the satellite should ground control capability be lost. The second most beneficial factor is using short station keeping maneuver cycle durations.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.251-253
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• 2004

Automated east/west and north/south station-keeping maneuvers were simulated for the geostationary COMS (Communication, Ocean and Meteorological Satellite) satellite that will be launched around year 2008, The satellite has to be maintained within ${\pm}0.05^{\circ}$ at the nominal longitude of $128.2^{\circ}\;E$. The general perturbation method was used to keep the position of the geostationary satellite. Weekly based east/west and biweekly based north/south station-keeping maneuvers were investigated. The sun pointing perigee control method and two-bum strategy were used for the east/west station-keeping maneuver. Switching the right ascension of the ascending node to descending node was adopted for the north/south station-keeping maneuver. One year station-keeping maneuver was demonstrated and various station-keeping orbital parameters were analyzed.

• Journal of Astronomy and Space Sciences
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• 제12권1호
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• pp.102-111
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• 1995

A series of east/west and north/south station-keeping maneuvers were simulated for the KOREAST spacecraft which has to be maintained within $\pm$0.05 at the nominal longitude of $116^{\circ}$E. Weekly an biweekly based station-deeping maneuver plannings were used, and weekend maneuvers were avoided. All of the station-keeping maneuver plannings and executions were performed using KOREASTA Mission Analysis Software on VAX/VMS operating system. Fourteen weeks station-keeping maneuvers were performed and various station-keeping orbital parameters were obtained.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.122-128
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• 2007

In this paper, a method of station keeping strategy using relative orbital motion and numerical optimization technique is presented for geostationary satellite. Relative position vector with respect to an ideal geostationary orbit is generated using high precision orbit propagation, and compressed in terms of polynomial and trigonometric function. Then, this relative orbit model is combined with optimization scheme to propose a very efficient and flexible method of station keeping planning. Proper selection of objective and constraint functions for optimization can yield a variety of station keeping methods improved over the classical ones. Nonlinear simulation results have been shown to support such concept.

• Journal of Astronomy and Space Sciences
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• 제23권3호
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• pp.245-258
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• 2006

이 연구에서는 통신해양기상위성의 위치유지 조정을 분석하고 계획하는 자동화 알고리즘을 개발하였다. 섭동 계산 및 궤도 예측을 위해 일반섭동론을 사용하였으며 궤도 요소들을 각 섭동에 의한 장주기 변화, 영년 변화항으로 나누어 분석하는 해석적인 방법을 적용하였다. 이러한 분석을 통해 통신해양기상위성의 동서방향과 남북방향에 대한 위치유지 조정 시뮬레이션을 수행하였다. 위치유지를 위한 허용범위는 ${\pm}0.05^{\circ}$로 설정하였고 동서 방향은 7일 주기, 남북방향은 14일주기로 1년의 기간 동안 수행하였다. 통신해양기상위성의 경도가 동경 $128.2^{\circ}$와 동경 $116.0^{\circ}$ 사이에서 아직 확정되지 않았기 때문에 두 경우 모두에 대해서 시뮬레이션 해보았다. 2008년 12월부터 1년에 대해서 동경 $128.2^{\circ}$의 경우에는 동서방향 위지유지를 위해서 3.50m/s의 속도 변화량이 남북방향 위치유지를 위해서는 52.71m/s의 속도 변화량이 필요하다는 결과를 얻었다. 동경 $116.0^{\circ}$의 경우에는 동서방향 위치유지에는 3.86m/s, 남북방향 위치유지에는 52.71m/s의 속도 변화량이 필요하다는 결과를 얻었다. 이 결과를 통해서 통신해양기상위성의 위치유지 조정은 동경 $128.2^{\circ}$에 위치했을 때 효율적이라는 결론을 얻을 수 있었다.

• 한국항공우주학회지
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• 제31권9호
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• pp.75-81
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• 2003

정지궤도 위성의 위치는 여러 외부 교란력에 의해서 끊임없이 움직이기 때문에 우주에서 한 점으로 정의할 수 없다. 따라서 정지궤도 위성의 통신방송과 같은 일반적 임무를 수행하기 위해서는 우주의 한정된 공간인 위치유지박스 내에 운용되어야 한다. 본 연구에서는 남북위치유지 오차보다 상대적으로 큰 동서 위치유지 박스를 설정하기 위해서 여러 오차들을 유도하여 정립하였다. 이를 이용하여 무궁화위성에서 사용하고 있는 7일의 위치유지주기를 검증하고 14일로 위치유지 주기를 늘릴 경우의 문제점을 분석하였다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2006년도 Proceedings of ISRS 2006 PORSEC Volume I
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• pp.263-266
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• 2006

Now, on the developing COMS(Communication, Ocean and Meteorological Satellite) has solar panel on the South panel only. Therefore, the wheel off-loading has to be performed periodically to reduce a induced momentum energy by a asymmetric solar panel. One of two East/West station keeping maneuver to correct simultaneously longitude and eccentricity, orbit corrections may be performed during one of the two wheel off-loading manoeuvres per day to get enough observation time for meteorological and ocean sensor. In this paper, we applied a linearized orbit maneuver equation to acquire maneuver time and delta-V. Nonlinear simulation for the station keeping is performed and compared with general station keeping strategy for fuel reduction.

• ETRI Journal
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• 제22권1호
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• pp.12-19
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• 2000

Wireless communication systems using airship have been proposed in worldwide. The airship will be located at the stratosphere about $20{\sim}23\;km$ above the sea level. The position of airship will vary within the station keeping range with time due to the drag of the wind in the stratosphere. When the earth station antenna has a high gain without the tracking function, the antenna performance may be degraded by a small variation of the airship. This means that variation of airship location could result in serious degradation of the system performance. In this paper, degradation in earth station's Equivalent Isotropic Radiated Power (EIRP) and Gain to noise Temperature ratio (G/T) due to the stratospheric platform movements has been derived by calculating the deviation angle of the main beam directions between the earth station and the platform antenna. In this case, the antenna of the earth station has been assumed circular and/or patch array antennas.

• 한국위성정보통신학회논문지
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• 제2권2호
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• pp.16-21
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• 2007

태양과 달 그리고 지구의 비대칭 중력장에 의해 발생하는 다양한 섭동항은 정지궤도 위성의 위치를 지속적으로 변화시킨다. 따라서, 정지궤도 위성의 위치를 일정한 범위 내로 유지시키기 위해서는 궤도경사각과 승교점 적경을 조정하는 남북방향 위치유지와 이심률과 경도를 조정하는 동서방향 위치유지가 필요하다. 본 논문에서는 통신해양기상위성 비행역학 소프트웨어를 이용하여 통신해양기상위성의 위치유지 시뮬레이션을 수행하고 그 결과를 분석하였다. 통신해양기상위성은 경도 $128.2^{\circ}E$ 에서 위성을 ${\pm}0.05^{\circ}$ 범위 내에 유지시키기 위해 일주일 주기로 동서/남북방향 위치유지를 수행하며, 위성의 남쪽 패널에만 부착된 태양 전지판으로 부터 발생하는 자세오차를 줄이기 위해 하루 두 번 휠 오프로딩을 수행한다. 본 논문에서는 휠오프로딩을 고려한 위치유지 시뮬레이션을 수행하였고, 그 결과 통신해양기상위성 비행역학 소프트웨어를 이용하여 통신해양기상위성을 ${\pm}0.05^{\circ}$ 범위 내에서 안정적으로 유지시킬 수 있음을 확인하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1993년도 한국자동제어학술회의논문집(국내학술편); Seoul National University, Seoul; 20-22 Oct. 1993
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• pp.799-804
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• 1993

In this paper, the scheme of combining the orbit correction and attitude control of a 3-axis stabilized satellite is suggested. Being coupled and complimentary, it is preferable to achieve the required orbit correction and the desired attitude control simultaneously. A solution of the probes simultaneous control of orbit correction and attitude of a satellite, is obtained by solving the two point boundary value problem numerically. The first-order gradient algorithm is used to solve the numerical problem. The simulation results show that the East-West station keeping process with the combined system of an orbit correction and an attitude control is satisfactory.