本文針對環境影響衛星軌道參數作分析，及以福衛三數據作為分析在不同環境下之異變基準。文中所提的環境以大氣密度造成對衛星阻力影響為主。其他干擾的潛在因素，可結合其他運算方程計算出來，本文只討論在衛星長週期軌道附近受太陽黑子的影響之變化。對地球的假設理論為地球是一個橢球形，但根據近來衛星資料分析，地球已不是一個球狀而是呈梨狀，配合不同之大氣模式而讓地球上空之密度較以往為複雜。在地球低軌道0-1000km（Low Earth orbit，LEO）[1]，大氣密度對衛星影響最為嚴重，而衛星在地球中軌道1000-10000km（Medium Earth Orbit，MEO）[1]，則加受到地球重力場及太陽與三者之影響較大。由於太陽黑子在Cycle24將得到新的高峰。在1977年，Skylab因受大氣不穩定的影響，而提前掉落，所以對衛星來說，環境變化是非常重要的關係。而福爾摩沙衛星三號（FORMOSAT-3）高度約為在700-800km，如果衛星軌道脫離原先預測之軌道範圍，則在地面無法接收信號，經過一定時間後，該衛星將失去控制。因此，如何利用有效工具及適當的參數來模擬衛星軌跡是非常重要的。本文內容則說明在衛星環境中「太空天氣」對衛星之軌道參數作分析。
This paper contains orbital trajectory analysis and basic simulate program with post-flight satellite data. Atmospheric drag effects on a satellite is usually computed by including a drag disturbing potential with the central body, ot her disturbing potentials, and integrating the equations of motion else. We are interested only in the long term drag effects on the satellite's perigee and apogee with analytic study by calculating the effect of solar spots. A computer program based on King-Hele's most basic theory of a spherical, atmosphere with constant scale height and shuttle collect data have been included, and its results are compared with those from different types of atmosphere model. Low-Earth-Orbiting Satellites most affected by the atmospheric density, medium-orbit satellites affected by the Earth's gravity field and atmosphere interactions affect with moon and the distant planet .But all are affected by the active solar flare within the solar system. As the sunspots at Cycle24 will get new height activity in 2013, with the influence of Earth's magnetic field each other, and the effect of Van Allen radiation belt the satellite will affect satellite or bital every month. In 1977, Cycle21 made SKYLAB decay to atmosphere unpredictably, so it is very important to simulate of where the environmental change of the satellite. FORMOSAT-3 is running around the surface height of 700-800km. If the satellite orbit miss-calculation a little, then the signals back to the ground is distorted because of orbital elements changing, then the ground cannot receive signals. Once after a certain time, the satellite will out of control and lost in space. Therefore, how to use and effective program(FUARMOS-2011) with proper parameters to simulate the trajectory is very important. This analysis will contain in this paper.
