福爾摩沙衛星五號初始任務軌道調整分析與策略

Initial Orbit Adjustment Analysis and Strategy for FORMOSAT-5 Mission

薛創維(Chuang-Wei Hsueh) ； 黃楓台(Feng-Tai Hwang)

《航測及遙測學刊》 22卷1期 (2017/03) Pp. 1-11

https://doi.org/10.6574/JPRS.2017.22(1).1

摘要

國家太空中心(以下簡稱太空中心)已完成整合測試的福衛五號預計在2017年發射，其任務軌道為720公里高的太陽同步軌道，這種軌道特性具有地面軌跡兩天再訪，在衛星轉動視角(Field of Regard，簡稱FOR)45度的條件下可以達成兩天全球覆蓋。然而日月的吸引力導致福衛五號軌道傾角些微的變化，2到3年後升交點赤經累積的差異量將會非常顯著而導致降交點地方時漂移離開原任務所定的區間。本文提出三種不同模擬情境以描述福衛五號的初始軌道條件並利用商用軌道分析軟體AGI Systems Tool Kit (STK)進行模擬、分析並說明不同初始軌道的長期變化對於福衛五號後續軌道維護的影響性。最後提出任務軌道調整分析與策略，藉由在適當的降交點地方時正確的加入偏差值於初始理想軌道將可減少軌道維護的次數與燃料的使用，亦可延長衛星的任務周期與壽命。

關鍵字

福衛五號 ； 軌道分析 ； 傾角調整 ； STK模擬

並列摘要

FORMOSAT-5 is the fifth space program initiated by National Space Organization (NSPO) of National Applied Research Laboratories (NARL)， the Republic of China (ROC). FORMOSAT-5 will be operated in a sun-synchronous orbit at altitude of 720 km. Operating in this orbit， FORMOSAT-5 can have two-day revisit property， and can reach the goal of two-day global coverage with FOR of 45 degrees. However， the lunisolar attraction causes a slight variation in the satellite inclination， the accumulated deviation in Right Ascension of Ascending Node (RAAN) can be significant after 2 to 3 years， and the Local Time of Descending Node (LTDN) will drift out of the range of mission-required value. Three different scenarios for different initial orbits are proposed. For each scenario， the initial orbit and the long-term evolution of FOMOSAT-5 are simulated through STK simulation. Finally， initial orbit adjustment analysis and strategy are proposed， and adding some proper inclination in the ideal orbit at the appropriate LTDN will reduce fuel use and will extend the life cycle of a satellite mission.

並列關鍵字

FORMOSAT-5 ； Orbit adjustment ； Orbit analysis ； STK simulation