Der Einfluss einiger charakteristischer Triebwerksparameter auf die Systeminstabilitaet in einem Gas/Fluessig Zweistoffraketentriebwerk, (Influence of Some Characteristic Parameters on Systems Instability in a Gaseous/Liquid Bipropellant Rocket Motor),
DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V LAMPOLDSHAUSEN (WEST GERMANY)
Pagination or Media Count:
Boundaries of system instability were determined experimentally with the propellant combination gaseous-hydrogenliquid-oxygen over broad ranges of operating and design conditions for a rocket motor with a 6.5 cm internal cylindrical combustion chamber diameter and the nine element coaxial injector system. The influence of the variation of chamber pressure and mixture ratio also the characteristic length, contraction ratio, and the ratio of the injector orifice area discussed in examples as a function of the position of stability limit in the operating performance map, and also as a function of the oscillatory frequency and amplitude. Experimental results were interpreted with a suitable time lag model. The appearance of chugging may be explained by a critical time lag which occurs between the instant of injection of any propellant element into the combustion chamber and the instant of conversion of its into burned gases, depending on the paramerers of the rocket motor. The results are summarized and discussed.
- Combustion and Ignition
- Rocket Engines