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Optimization of Gas Generator Liquid Rocket Engine using an Advanced Mass Model |
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PP: 17-20 |
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Author(s) |
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Afreen Abbas,
Muhammad Adnan,
Muhammad Azam,
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Abstract |
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| The conceptual design of Liquid rocket engine includes both performance and weight estimate considering mission
requirements and constraints. In this study a design optimization strategy has been employed to obtain a suitable design for liquid
rocket engine with gas generator cycles. Multi-objective optimization technique was used to maximize specific impulse and thrust
to weight ratio by varying O/F and expansion ratio for a given chamber pressure. First the performance parameters are calculated
followed by its mass estimation. In next step, FMINCON optimization technique is employed to get the best design. Two different mass
estimation techniques are used in this study to find one which is more suitable for this purpose. First technique is based on an Empirical
relation whereas second technique involves detailed calculation for every element with respect to a reference engine.
Results obtained show the compromise between the engine performance and thrust to weight requirements. The methodology developed
in this article is beneficial in preliminary phase of system design to meet optimized performance and thrust to weight requirements.
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