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.

1. INTRODUCTION
 2. CUBESAT IMPACT PROBLEM
 3. SIMULATION SETUP
 4. RESULTS ANALYSIS
  4.1 Impact Trajectory Characteristics Deployed fromDifferent Altitudes
  4.2 Divert Burn Characteristics for Different onboardThrusters
 5. CONCLUSIONS
 ACKNOWLEDGEMENTS
 REFERENCES

• Young-Joo Song(Lunar Exploration Mission Team, Korea Aerospace Research Institute) Corresponding Author
• Jin Ho(School of Space Research, Kyung Hee University)
• Bang-Yeop Kim(Lunar Exploration Mission Team, Korea Aerospace Research Institute)