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Initial Evaluation of ADN as Oxidizer in Solid Propellants for Large Space Launcher Boosters. Final Report.

Initial Evaluation of ADN as Oxidizer in Solid Propellants for Large Space Launcher Boosters. Final Report. Beställ tryckt exemplar Lägg i kundvagnen
Författare: Sten Andreasson, John De Flon, Mattias Liljedahl, Carl Oscarson, Marita Wanhatalo, Niklas Wingborg
Ort: Stockholm
Sidor: 58
Utgivningsår: 2010
Publiceringsdatum: 2010-05-05
Rapportnummer: (FOI-R--2988--SE)
Keywords solid propellant, ammonium dinitramide, ADN, HTPB, performance, compability, formulation, burn rate
Abstract The aim of this work is to perform an initial evaluation of ammonium dinitramide, ADN, as substitute for ammonium perchlorate, AP, in solid rocket propellants for large space launch boosters. This final report includes performance evaluation, compatibility and curing assessments, propellants formulation and determination of ballistic properties. The results show that the theoretical specific impulse increases from 262 s to 270 s by replacing AP with the same volume ADN in a typical HTPB/Al-based formulation. ADN is found to be chemically compatible with HTPB. However, ADN seems to accelerate the oxidative degradation of HTPB and thus a suitable antioxidant is required. ADN/HTPB/Al-based propellants have been formulated and cured successfully using isocyanates. The formulations were found to be thermally stable. Ballistic properties were determined using a strand burner. ADN/Al/HTPB propellant with a solid loading of 80 % had a burn rate of 12.8 mm/s at 6 MPa and a pressure exponent of 0.9. The pressure exponent is high. However, no burn rate modifiers or ballistic additives were used. This encourages continued evaluation. The report also includes information on how to handle ADN with respect to transportation, toxicity and hazard properties. This work was performed on NASA contract NNC09CA11C.

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