Presently, there is an increased interest in composite propellants that burn with low flame temperatures and do not contain chlorine or chlorine compounds. Appplications for such propellants may be found in turbine starters and in no or low smoke rocket engines. Phase-stabilized ammonium nitrate (ANS)-based propellants meet these requirements, but also other composite propellant formulations are feasible such as propellants based on a rubber binder and nitroglycerin (NC) or trimethylolethane-trinitrate (TMETN). In order to compare the performance of these propellants, three different families have been developed and tested: HTPB binder with ANS and various catalysts, PU binder with NG and nitroguanidine (NQ) or guanidine nitrate (GuNi), PU binder with TMETN and NQ or GuNi. With some exceptions all propellant formulations have calculated flame temperatures between 1200 K and 1400 K. In special burners the combustion characteristics of these propellants have been investigate in the pressure region between 1 and 10 MPa. The results of this study show that burning rates up to 7 mm/s at 10 MPa may vary between 0.3 and 0.7. In addition, the importance of catalysts to improve the ignitability of (ANS)-BASED propellants is confirmed.
Performance of no chlorine containing composite propellants with low flame temperatures
Leistungsfaehigkeit von chlorfreien Festtreibstoffgemischen mit niedriger Flammentemperatur
AIAA-Papers ; Jul ; 1-9
1987
9 Seiten, 11 Bilder, 4 Tabellen, 3 Quellen
Aufsatz (Konferenz)
Englisch
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