Lunar CubeSat Impact Trajectory Characteristics as a Function of Its Release Conditions

Abstract

As a part of early system design activities, trajectory characteristics for a lunar CubeSat impactor mission as a function of its release conditions are analyzed. The goal of this mission is to take measurements of surface magnetic fields to study lunar magnetic anomalies. To deploy the CubeSat impactor, a mother-ship is assumed to have a circular polar orbit with inclination of 90 degrees at a 100 km altitude at the Moon. Both the in- and out-of-plane direction deploy angles as well as delta-Vmagnitudes are considered for the CubeSat release conditions. All necessary parameters required at the early design phase are analyzed, including CubeSat flight time to reach the lunar surface, impact velocity, cross ranges distance, and associated impact angles, which are all directly affected by the CubeSat release conditions. Also, relative motions between these two satellites are analyzed for communication and navigation purposes. Although the current analysis is only focused on a lunar impactor mission, the methods described in this work can easily be modified and applied to any future planetary impactor missions with CubeSat-based payloads.

Flight Dynamics and Navigation for Planetary Missions in Korea: Past Efforts, Recent Status, and Future Preparations

“…Apart from these efforts, diverse areas related to planetary missions have already been initiated to prepare for future planetary missions. These studies include a planetary rover mission (Kim et al 2012;Eom et al 2012Eom et al , 2014, dynamic simulator development (Rew et al 2010), conceptual asteroid mission trajectory design (Yoo et al 2009;Song et al 2010c;Song & Park 2015), and a planetary mission trajectory concept generation using small satellites (Song et al 2015b(Song et al , 2015cLee et al 2017c). From these combined studies, it is believed that the cornerstone of the future Korean planetary missions, such as a lunar landing or asteroid sample mission, would be more achievable.…”

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

“…For these reasons, and as previously discussed, CubeSat-based payload planetary missions are vigorously promoted not only for the Moon, but also for Mars, Europa and other deep space exploration missions. Recently, Song et al (2015) analyzed CubeSat impact trajectory characteristics as a function of its release conditions from a mother-ship orbiting the Moon at about a 100 km altitude. They also analyzed relative motions between the CubeSat and the mother-ship during the impact phase.…”