Synthesis of the mixture formation scheme of the thruster with high-energy gaseous fuel components based on reference solutions

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The designing of controlling thrusters primarily relying on experimental data contains the most part of time and capital inputs of propulsion engineering. Therefore, the reference solutions method capable of reducing number of experiments is an acceptable way of solving the problem. The purpose of this work was to devise an algorithm for determining the point of design factor space which answers the optimal efficiency of fuel chemical energy conversion within the thruster combustion chamber. The algorithm was based on definition of effective power by the energy and mass characteristics, resource, and reliability. In addition, different types of gas fuel components were examined instead of fluid fuels. As a result, the reference solutions were used instead the optimal solutions for interfacing between the factor space grid points and the design objective functions with the sufficient accuracy for optimal solutions search. Determination of the combustion chamber geometry is realized at the number of stages to compliance with the requirements of efficiency and thermal conditions for the basic circuit. The circuit provides high quality of operating process with the trivial losses 8...9% of consumable complex number. It also provides satisfactory thermal conditions through the engaging duration typical for thrusters with high level of launching reliability.

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Rocket engine, thruster, combustion chamber, factor space, operating characteristics, reference solution

Короткий адрес: https://sciup.org/148312574

IDR: 148312574

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