Abstract
The paper considers the effect of various perturbations on the values of thrust-impulse characteristics of an aerospaceplane ramjet operating on a cryogenic hydrocarbon fuel. An engineering method has been developed to determine variations in the output characteristics of the engine depending on the trajectory and working process parameters, the properties of the fuel. A summary table of the influence coefficients is presented. These coefficients determine the value and sign of thrust and specific impulse caused by certain perturbations. The calculations showed that the excess oxidant ratio has the greatest effect on the ramjet thrust-impulse response, which allows performing deep control of the workflow by changing the ratio of oxidant and fuel in the engine combustion chamber. High sensitivity of the output characteristics to a change in the trajectory parameters is indicated. Recommendations on the selecting characteristics of the crui-sing flight and increasing the range of workflow controlling are offered.
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