Abstract
1. Abstract This paper deals with performance test results of a new solid composite propellant based on GAP and Hydrazinium Nitroformate (HNF). This propellant delivers about 3,5% 9,3% higher performance (c*) than the best existing composite solid rocket propellant. Characteristics of ingredients and propellant formulations are presented together with the test results which demonstrate the increased performance compared to conventional high-performance propellants based on Ammonium Perchlorate (AP). The test equipment is being described as well as estimates of losses which occur in the test motor. This allows to estimate the expected performance in full-size rocket motors.
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