• Journal of Astronomy and Space Sciences
• /
• 제7권1호
• /
• pp.11-21
• /
• 1990

점융궤도 요소는 평균 궤도 요소, 영년 섭동, 단주기, 장주기항이 포함되어 있다. 접융궤도 요소로부터 평균 궤도 요소로 변환시키는 알고리즘을 기술하였고, 평균 궤도 요소 $W_c,\;W_s$, L도 얻었다.

• Journal of Astronomy and Space Sciences
• /
• 제28권1호
• /
• pp.37-54
• /
• 2011

Two semi-analytic solutions for a perturbed two-body problem known as Lagrange planetary equations (LPE) were compared to a numerical integration of the equation of motion with same perturbation force. To avoid the critical conditions inherited from the configuration of LPE, non-singular orbital elements (EOE) had been introduced. In this study, two types of orbital elements, classical Keplerian orbital elements (COE) and EOE were used for the solution of the LPE. The effectiveness of EOE and the discrepancy between EOE and COE were investigated by using several near critical conditions. The near one revolution, one day, and seven days evolutions of each orbital element described in LPE with COE and EOE were analyzed by comparing it with the directly converted orbital elements from the numerically integrated state vector in Cartesian coordinate. As a result, LPE with EOE has an advantage in long term calculation over LPE with COE in case of relatively small eccentricity.

• Journal of Astronomy and Space Sciences
• /
• 제5권2호
• /
• pp.111-122
• /
• 1988

지구의 비대칭 중력장 $J_2$와 $J_3$가 원궤도에 가까운 인공위성의 궤도요소에 미치는 장, 단주기 섭동과 영년섭동을 해석적 방법으로 구하였다. 이 때 궤도의 이심률이 작은 경우에 섭동방정식에서 발생하는 특이점은 Taff(1985)가 제시한 방법중 궤도요소 e, $\omega$, M을 $e_s$=$esin\omega$, $e_c=e\;cos\;\omega$, $\ell=\omega+M$으로 치환하는 방법을 사용하여 제거시켰다. Walter(1967)의 방법을 이용하여 기상위성 NOAA-10호의 평균궤도요소를 결정하였고 이를 NASA의 Brouwer 평균 궤도요소와 비교하였다. 평균 궤도요소 a, i, $\Omega$는 TBUS의 결과와 거의 일치하나 평균 궤도요소 e, $\omega$, M은 약간의 차이를 보였다. 그리고 특이점을 제거하기 위한 Taff의 방법 중 e, $\omega$, M 대신에 $e_s=e\;sin(\Omega+\omega)$, $e_c=e\;cos(\Omega+\omega)$, $L=\Omega+\omega+M$으로 치환하는 방법이 극궤도위성에는 부적합한 것으로 나타났다.

• Journal of Astronomy and Space Sciences
• /
• 제19권4호
• /
• pp.395-402
• /
• 2002

The NORAD type Two Line Element (TLE) was obtained from the osculating orbital elements by an iterative approximation procedure. The mathematical model was presented and computer program was developed for the conversion. The osculating orbital elements of the KOMPSAT-1 were converted into the NORAD TLE. Then the effect of the SGP4 atmospheric drag coefficient ($B^*$) was analyzed by comparison of the orbit propagation results with different $B^*$ values.

• Journal of Mechanical Science and Technology
• /
• 제20권2호
• /
• pp.177-184
• /
• 2006

An orbital design method of the formation initialization based on the relative orbital element method is presented. It firstly constructed the relative motion equation of the satellite formation flying in terms of the leader and followers' orbital elements. Then the equation was simplified when the orbit eccentricity of the leader satellite was small. And according to the satellites' mission, a general design method for the relative trajectory was proposed. The advantage of this method is that one can get a very simple analytical formula of each follower satellite's orbital elements when the orbital eccentricity of the leader satellite is zero. The simulation results show that the method is effective.

• Journal of Astronomy and Space Sciences
• /
• 제6권2호
• /
• pp.91-100
• /
• 1989

정지 위성 궤도의 평균 궤도 요소를 비 특이점 궤도 요소 항으로 연구하였다. 실제 위성의 위치는 평균 궤도로부터 단주기 섭동 만큼 위성 위치가 진동하는데, 그 진동의 진폭은 1800m 이하이다. $e_c$ 와 $e_s$의 평균값도 얻었다.

• 천문학회지
• /
• 제2권1호
• /
• pp.10-22
• /
• 1969

Two-Color photoelectric observations were made at Flower and Cook Observatory, University of Pennsylvania. Since the spectroscopic elements are available for the system, derivation of an absolute physical dimension is now expected to be feasible. Results of computation of the orbital elements lead to a fact that the system shows an annular eclipse rather than a partial which is a finding reported by Shapley.

• Journal of Astronomy and Space Sciences
• /
• 제31권1호
• /
• pp.63-66
• /
• 2014

Since Rigollet first discovered a comet in 1939, many follow-up observations have been made, particularly in Europe. It is now known that the Rigollet comet is identical with the one observed by Herschel in 1788, and thus it is now called 35P/1939 O1 or the Herschel-Rigollet comet. Yumi, a Japanese astronomer, also observed the Rigollet comet in Korea using a 6-inch refractor telescope, and published his data in two Japanese journals (Bulletin of the Observatory of the Government-General of Korea and Publication of the Lecture on Meteorology). In his paper, Yumi also referred to observations by Hirose and Kanda in Japan. However, their works have not been given attention by international society. In this study, we analyze the observation data of Yumi and present preliminary orbital elements using it with a modified Gauss method. We expect that this study will be used to refine the orbital elements of the Rigollet comet by orbital-calculation experts. For that reason, we have also transcribed all the observational data presented by Yumi.

• 한국항공우주학회지
• /
• 제30권7호
• /
• pp.123-129
• /
• 2002

본 논문은 실제 저궤도 위성에서 GPS를 이용하여 궤도를 추정하는 연구 결과를 담고 있다. 우리별 3호의 GPS 수신기가 실제 측정한 3차원 위치 및 속도 정보를 이용하였으며, 추정 알고리즘으로는 실시간 계산을 위한 확장 칼만필터와 후처리를 위한 스무더를 사용하였다. 스무더는 확장 칼만필터를 통과한 값을 이용하여 다시 역으로 추정하는 과정을 거치게 되므로 전체적으로 안정화된 추정값을 제공한다. 본 논문에서는 스무더를 적용한 추정값을 이용하여 우리별 3호의 케플러 궤도 요소를 계산하고, 분석하였다.

• Journal of Astronomy and Space Sciences
• /
• 제31권3호
• /
• pp.199-204
• /
• 2014

This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.