The development and test of a hydrogen peroxide monopropellant microrocket engine using MEMS technology (spectrometer for planetary missions)
conference paper
Given the present, relatively limited deployment of low cost and mass space missions, there are clear opportunities for the application of small-scale propulsion systems in further enabling these small satellite missions. With this situation in mind, a team comprising ASTC, SSTL, TNO and QinetiQ – under funding from the European Space Agency – has undertaken the development of a MEMS-based micro-rocket engine concept with the intended capability of providing a specific impulse of greater than 100s. Both turbo-pump fed bi-propellant as well as mono-propellant concepts were investigated. For demonstration a mono-propellant design was selected of which an initial design concept was developed, based on hydrogen peroxide decomposition. Identified as the critical component in the mono-propellant system, several batches of the honeycomb wafers – upon which the decomposition occurs – have been manufactured. As a proof of concept, the wafers have been subjected to a set of structural and functionality tests. Given the results of the latest testing initiative, it is envisaged that, with adequate refinement and development of the current design, a reliable and deployable mono-propellant micro-rocket engine solution may be realised.
Topics
TNO Identifier
469231
Source title
5th ESA Round Table on Micro/Nano Technologies for Space, 3-5 October 2005, ESTEC, Noordwijk, The Netherlands
Collation
10 p.
Pages
750-759
Files
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