RT Journal Article ID 472b9ed118d8f593 A1 van der Heijden, A. E. D. M. A1 Keizers, H. L. J. A1 Veltmans, W. H. M. T1 HNF/HTPB BASED COMPOSITE PROPELLANTS JF International Journal of Energetic Materials and Chemical Propulsion JO IJEMCP YR 2002 FD 2002-01-01 VO 5 IS 1-6 SP 587 OP 596 K1 HNF K1 HTPB K1 propellant K1 thermal stability K1 ballistics K1 mechanical properties K1 hazard properties AB In a search for new storable high performance propellants for the European Space Agency (ESA), the solid oxidizer Hydrazinium Nitroformate (HNF) was identified as a very promising ingredient for a new storable composite propellant, currently in its development phase. Two distinct advantages of HNF based propellants over presently used Ammonium Perchlorate (AP) based propellants were the basis of this promise: a very high specific impulse which dramatically increases the performance of the solid propellant and chlorine free exhaust products which prevent the formation of HCl in the environment.
Modern solid rocket motors are generally based on AP in a hydroxy-terminated polybutadiene (HTPB) binder system. Replacement of the AP with HNF will, as indicated above, result in performance gains, chlorine free exhaust products, and a reduced smoke trail; whereas it represents a relatively small change in composite propellant production (all existing knowledge and production infrastructure for HTPB based systems can be kept in place). Early investigations in the USA, during the 1960s, seemed to indicate that HNF could not be combined with HTPB. However, recent studies performed at TNO Prins Maurits Laboratory show that acceptable propellants can be produced using this combination. A summary of the results obtained with HNF/HTPB formulations will be presented. PB Begell House LK https://www.dl.begellhouse.com/journals/17bbb47e377ce023,76f8e14974df93a8,472b9ed118d8f593.html