Abstract
In the article is given methodical approach of determining and confirming of main traction force characteristics of different purpose missiles solid fuel engines. The probability of failure-free operation at the define functionality time is proposed as basis reliability rate, which is calculated with taking into account the structural functional scheme of solid fuel engines which are under research. This approach allows to taking into account the construction peculiarities of engines components parts and elements and interconnection between them. In the article also given interconnection between speed of guided missiles at the end of active flying trajectory and traction force impulse of their solid fuel engines which are defining from tests results.
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