As a first step in the design of a Canadian micro-penetrator concept, an analysis of trajectories to multiple target bodies within the solar system is performed. The purpose is to determine Δv's required to decelerate the micro-penetrator to within acceptable limits prior to impacting the surface - the Lunar-A penetration speed limit of ∼300 m/s is used as a baseline. The Δv's determined from the these analyses are applied to Tsiolkovsky's rocket equation in order to determine propellant mass required assuming a solid rocket motor with lsp between 200 and 290 seconds. Results from both the trajectory analysis and propellant analysis are combined to characterize total payload mass and wet mass deliverable to each target body investigated. As a result of this analysis, the total wet mass of the micro-penetrator is constrained to a minimum 5 kg and maximum 40 kg, with payload masses ranging from 1 kg to 20 kg. These values will be carried forward to direct the next stage of the micro-penetrator design.

59th International Astronautical Congress 2008, IAC 2008
Department of Mechanical and Aerospace Engineering

Grove, D. (Dave), & Ellery, A. (2008). Trajectory analyses of multiple exploration missions for a Canadian micro-penetrator concept. In International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008 (pp. 1665–1673).