Abstract
Abstract In the Frame of Romanian Incentive Scheme Programme under European Space Agency, a feasibility study of a Small Orbital Launcher was performed by “Politehnica” University of Bucharest. Building on the results obtained in the project, European Space Agency’s Space Transportation Directorate through the Future Launchers Preparatory Programme awarded INCAS a Phase 0/A contract for a Microlauncher concept. The targeted market is the micro-satellites sector developed by universities, but also by small companies for research purpose and validation of applications/products before commercialization, with a mass lower than 150 kg. This paper presents a conceptual design for a Microlauncher having a target mission to deliver a small satellite of 150 kg into a 600 km circular polar orbit with the launching site located in Europe. The Microlauncher concept is obtained using an in-house multi-disciplinary optimization tool, which contains four modules: weights and sizing, aerodynamics performance assessment, propulsion, trajectory computation and optimization.
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