FIELD: engines and pumps.
SUBSTANCE: proposed method consists in producing additional source of combustion products and determining minimum pressure that ensures stable operation of adjustable solid propellant rocket engine. Additional source of combustion products is created by introducing simulating charge into model engine combustion chamber. Aforesaid charge features low pressure sensitivity of combustion rate, degressive combustion surface that ensures degressive pattern of "pressure-time" diagram, combustion product temperature equal to that of rocket solid propellant and exponent in combustion rate law satisfying the conditions protected by this invention. Aforesaid "pressure-time" diagram allows determining, from the start of pulsed combustion operation, the minimum pressure limit of stable operation of above mentioned engine.
EFFECT: higher accuracy of determination.
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