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http://dx.doi.org/10.5140/JASS.2015.32.3.257

Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations  

Song, Young-Joo (Lunar Exploration Mission Team, Korea Aerospace Research Institute)
Ho, Jin (School of Space Research, Kyung Hee University)
Kim, Bang-Yeop (Lunar Exploration Mission Team, Korea Aerospace Research Institute)
Publication Information
Journal of Astronomy and Space Sciences / v.32, no.3, 2015 , pp. 257-268 More about this Journal
Abstract
Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements. Results provided through this work will be helpful in further detailed system definition and design activities for future lunar missions with a CubeSat-based payload.
Keywords
lunar cubesat impactor; Delta-V; impact trajectory;
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Times Cited By KSCI : 7  (Citation Analysis)
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