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Reusable Rocket Engine Intelligent Control System Framework Design, Phase 2

机译:可重复使用的火箭发动机智能控制系统框架设计,第2阶段

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摘要

Elements of an advanced functional framework for reusable rocket enginepropulsion system control are presented for the Space Shuttle Main Engine (SSME) demonstration case. Functional elements of the baseline functional framework are defined in detail. The SSME failure modes are evaluated and specific failure modes identified for inclusion in the advanced functional framework diagnostic system. Active control of the SSME start transient is investigated, leading to the identification of a promising approach to mitigating start transient excursions. Key elements of the functional framework are simulated and demonstration cases are provided. Finally, the advanced function framework for control of reusable rocket engines is presented.

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