A method for the realization of a dual thrust program for a hybrid rocket engine similar to that of a solid propellant engine is discussed. In this case two concentric propellant charges of different burning rate were installed in the combustion chamber. The inner propellant has a high burning rate, the outer a low. The necessary relationships are derived using the basic hybrid propulsion equations. Two possibilities for control of the mixing ratio of both thrust stages are represented. It is shown that an optimal operation may be obtained in a simple manner.
Realization of a Dual Thrust Program for Hybrid Engines Zur Realisierung Eines Doppelschubprogrammes bei Hybridtriebwerken
1974
12 pages
Report
Keine Angabe
Englisch
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