FIELD: rocket technics.
SUBSTANCE: invention relates to rocketry, namely to methods of solid rocket propellant new compositions characteristics determining, in particular for ramjet engines. During solid fuel unit pulse determining of armored sample of analyzed fuel is burnt in volume of gas and combustion products flow reactive force is measured. Fuel sample is placed in afterburner chamber model, gas dynamically similar to natural engine afterburner chamber, and blown by gas flow with parameters corresponding to natural engine solid fuel charge blowing. Part of sample surface is coated with armoring providing armored surface ignition delay for a time, making 10–50 % of analyzed fuel sample combustion duration without armoring.
EFFECT: invention increases reliability of solid fuel unit pulse measurement, as well as reducing duration and number of engine full-scale tests.
1 cl, 2 dwg
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