Energies 2011, 4, 1779-1839; doi:10.3390/en4101779 OPEN ACCESS energies ISSN 1996-1073 www.mdpi.com/journal/energies Article Polymer Combustion as a Basis for Hybrid Propulsion: A Comprehensive Review and New Numerical Approaches Vasily Novozhilov 1,*, Paul Joseph 1, Keiichi Ishiko 2, Toru Shimada 3, Hui Wang 4 and Jun Liu 4 1 Fire Safety Engineering Research and Technology Centre, School of the Built Environment, Built Environment Research Institute, University of Ulster, Newtownabbey, BT37 0QB, UK; E-Mail:
[email protected] 2 Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji-Higashi, Chofu, Tokyo 182-8522, Japan; E-Mail:
[email protected] 3 Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo, Sagamihara, Kanagawa 252-5210, Japan; E-Mail:
[email protected] 4 School of Computing and Mathematics, Computer Science Research Institute, University of Ulster, Newtownabbey, BT37 0QB, UK; E-Mails:
[email protected] (H.W.);
[email protected] (J.L.) * Author to whom correspondence should be addressed; E-Mail:
[email protected]; Tel.: +44-28-9036-8705; Fax: +44-28-9036-8726. Received: 28 July 2011; in revised form: 11 October 2011 / Accepted: 12 October 2011 / Published: 24 October 2011 Abstract: Hybrid Propulsion is an attractive alternative to conventional liquid and solid rocket motors. This is an active area of research and technological developments. Potential wide application of Hybrid Engines opens the possibility for safer and more flexible space vehicle launching and manoeuvring. The present paper discusses fundamental combustion issues related to further development of Hybrid Rockets.