Trajectory Analyses of Multiple Exploration Missions for a Canadian Modular Micropenetrator Concept
- Paper number
IAC-08.A3.6.16
- Author
Mr. Dave Grove, Carleton University, Canada
- Coauthor
Prof. Alex Ellery, Carleton University, Canada
- Year
2008
- Abstract
High-velocity kinetic penetrators have been proposed and developed as a modest-cost exploration tool to sample geophysical data and perform in-situ scientific analysis both at the surface and to depths ranging from 1 to 5 meters. Previous penetrator concepts (Mars ’96, Deep Space 2, Lunar-A) each used unique EDL mechanisms for deceleration, impact mitigation, surface deployment, etc. designed specifically to operate in the environment targeted for exploration. Re-targeting a penetrator for deployment to a significantly different environment could require equally significant changes to the unique mechanisms - a potentially lengthy and costly re-design.
A different approach is proposed whereby the core spacecraft components (propulsion, EDL, structure, etc.) would be designed modularly; components could be added, altered, or removed where necessary allowing the overall concept to be tailored to fit a variety of mission scenarios. The goal of this approach is to create a flexible penetrator design capable of rapid response to flight opportunities by reducing overall design time and cost.
While aerobraking devices such as those utilised by the Mars ’96 and DS2 penetrators provide deceleration mechanisms in atmospheric bodies, deployment to airless bodies (asteroids, comets, or planetary moons) will require the use of an on-board propulsion system to reduce the penetrator impact velocity to within survivable limits (<300 m/s). As a first step in this design, deceleration requirements are quantified by determining arrival velocities at various target bodies including the Moon, Mars, NEA Apophis, Europa and Enceladus. This investigation is achieved through solutions to Lambert’s problem and iterative impulsive/finite trajectory simulations in STK, and indicates that propulsion will have to deliver at least 1.0-1.5 km/s Δv in order to achieve the required impact velocity. Propulsion therefore becomes a key driver to the overall concept mass.
The following paper discusses the approach and algorithms used in the simulations and presents arrival velocity ranges/deceleration Δv’s for each body investigated. The resulting implications on propulsion system design and overall concept design is discussed, and a propulsion system concept is presented.
- Abstract document
- Manuscript document
IAC-08.A3.6.16.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.