Mission Concepts
Background
Currently, the SLAM team is developing a proposal for SOM for two alternative mission concepts: a lunar swing-by mission and a lunar orbit mission. The proposal will include such considerations as orbit design, communication architecture, carrier requirements, delta-V requirements, and rough budget estimates. The proposal development should end with quarter 1, at the end of March. In the second quarter, the SLAM team will shift focus to a hardware verification of the proposed communication architecture. Please see the Hardware Test link for more information about the test.
Mission Concept I: Lunar Swing-by
The first mission concept is to fly 6 CubeSats in a carrier satellite in a lunar swing-by, with a return to Earth orbit. The mission would be approximately a week in duration. A unique payload could be carried on each CubeSat. The communication architecture would be relatively simple, and commercial off-the-shelf components would probably be sufficient. Outreach is a good option for this mission due to its relatively simple nature. This mission has a deadline goal of 2008.
Mission Concept II: Lunar Orbit
The second mission concept is to fly 6 CubeSats in a carrier satellite into a lunar orbit. This mission would be longer in duration, possibly requiring more well-tested components than commercial off-the-shelf components. It would require a more complex communication architecture, as well. A unique payload could be carried on each CubeSat, as in mission concept I. This orbital mission would be more expensive than the swing-by mission due to its longer duration, the increased weight in fuel required, and the more complex technical development required. For these reasons, as well, the lunar orbit mission has deadline goal of 2010.