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- W2016000331 abstract "The optimum mission performance is addressed, and a simple, robust, multivariable ight-guidance law for following the prescribed optimum trajectory of an airbreathing, single-stage-to-orbit launch vehicle is proposed. Discussion focuses on the critical scramjet-powered phase of ight for a hydrogen-fueled vehicle. The performance analysis,basedonenergy-statearguments,suggests that,whereas stationkeeping andorbitalmaneuverswill clearly require rocket propulsion, low-Earth-orbital energy can be achieved with scramjet propulsion. The feedback guidance law for trajectory following is also synthesized using total-energy concepts, along with an approach consistent with quantitative feedback theory. The open-loop system in the guidance analysis is multivariable, unstable, andnonminimumphase. Furthermore, the vehicle characteristics lead to signi cant interactions between the inputs and responses. The guidance law developed relies on an integrated ightand propulsion-control inner loop to stabilize the attitude dynamics and regulate the engine performance. It is shown that this hierarchical integrated synthesis technique yields simple, classical-looking compensation that robustly stabilizes the system and delivers very good performance." @default.
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- W2016000331 date "1997-11-01" @default.
- W2016000331 modified "2023-09-25" @default.
- W2016000331 title "Optimum Mission Performance and Multivariable Flight Guidance for Airbreathing Launch Vehicles" @default.
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- W2016000331 doi "https://doi.org/10.2514/2.4171" @default.
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