Preliminary Mission Analysis for the ESMO Mission
- Paper number
IAC-07-E2.3.07
- Author
Mr. Matteo Ceriotti, University of Glasgow, United Kingdom
- Coauthor
Ms. Camilla Colombo, University of Glasgow, United Kingdom
- Coauthor
Mr. Nicolas Croisard, University of Glasgow, United Kingdom
- Coauthor
Mr. Timothee McLean, University of Glasgow, United Kingdom
- Year
2007
- Abstract
In recent times, numerous space agencies are re-examining both manned and unmanned lunar missions. These missions have both scientific and strategic objectives, such as a test-bed for the new technologies, or a launch pad towards Mars and other celestial bodies. However, current technology and economical resources are deeply different from the ones available at the time of the first Apollo missions. The recent trend of "better, cheaper, faster" is clearly applied to space missions, with low-cost being the priority. The requirement of low cost has a strong impact on the mission analysis: the trajectory must be reliable, the transfer time should be as short as possible, and ground stations must be chosen accurately. Moreover, the reduced budget strongly affects the trajectory design, since a low-cost mission inherently implies low Δv transfers. After introducing the objectives and requirement of the European Student Moon Orbiter (ESMO) mission, this paper focuses on the transfer strategies developed during the preliminary design phase. Both chemical propulsion and solar electrical propulsion (SEP) options have been considered leading to two different transfer trajectories. Two chemical transfers are considered: a trajectory through the Earth-Moon L1 Lagrangian point considering a restricted three body problem, and a more complex Belbruno transfer (or WSB transfer) using the perturbation of the Sun to freely incline the transfer plane. A SEP spacecraft requires a completely different kind of trajectory: due to the very low level of thrust available, the trajectory must be designed using continuous low-thrust and coastal arcs. Furthermore, the design and optimisation of a low-thrust trajectory requires the solution of an optimal control problem, rather than a Δv minimisation. In the second part, the problem of the launch window is examined. As ESMO is planned to be launched as a secondary payload, the mission analysis has to consider a one year launch window. The impact of such a constraint on the mission design is analysed, and possible solutions are presented. Various options for the operational lunar orbit were also analysed, in particular the stability trading off between the Δv required for the transfer into the desired lunar orbit, and the corresponding station-keeping while meeting the constraints imposed by the mission objectives. To complete the mission analysis, additional studies were performed on eclipse times, solar aspect angles and communication windows analysis.
- Abstract document
- Manuscript document
IAC-07-E2.3.07.pdf (🔒 authorized access only).
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