No abstract

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS.

As the capability of small spacecraft (<500 kg) platforms increases, so do the complexities of their missions. The need for such functions as orbit raising and de-orbiting lead to an ever higher requirement for mission AV. Traditionally a cold gas nitrogen system would have been sufficient for a small satellite, however this is usually only suited to low AV missions, such as drag compensation. Propulsion technologies with higher specific impulse and higher storage densities are required.Hydrazine is the traditional step up, but its use has a high cost in terms of safety and infrastructure due to its toxic and flammable nature. This can negate the low cost advantages, which can be gained by having a small spacecraft. A green propulsion system with the equivalent performance of a hydrazine system would offer the advantages of safety, and handlability and hence lower overall propulsion system costs.This paper details the research being undertaken at the Surrey Space Centre to fill the gap between cold gas nitrogen and toxic, storable propellants. Research in the following areas will be described :-• A nitrous oxide monopropeilant thruster • A novel geometry hybrid rocket using common polymers as fuel with various oxidisers • A small kerosene / hydrogen peroxide bipropellant engine • A hydrogen peroxide storage programme • A hydrogen peroxide catalyst investigation

No abstract

No abstract