A renewed interest in Moon exploration has been forming in recent years due to its close proximity as well as identification of key resources such as water ice in Lunar polar regions. Furthermore, the launch industry has been transforming with increased availability in the variety and instance of spacecraft launchers. Additionally, rideshare missions are becoming the new norm. Rideshare missions not only to LEO but even to Geosynchronous Transfer Orbit are currently available, reducing the cost of access to the deep space. Electric propulsion is also becoming more widespread. Advances in these varied fields will possibly converge in capable small spacecraft designs that will be able to carry out complex missions in deep space. This particular study focuses on identifying key sizing parameters of such a spacecraft. An initial trajectory design utilizing AGI's Systems Tool Kit (STK)was carried out involving low-thrust orbit raising from Geosynchronous Transfer Orbit with eventual Lunar capture. Preliminary lunar station keeping was examined. Later, key design parameters such as eclipse times, communication durations etc. were investigated. Overall, a broad framework was obtained upon which optimization studies and preliminary design can be conducted.
Geostationary Transfer Orbit to Moon Low Thrust Transfer Design for a Small Satellite
2019-06-01
1008499 byte
Conference paper
Electronic Resource
English
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