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The primary objective of Reusable Launch Vehicle mission is to evaluate autonomous navigation, guidance and control schemes under the environment of reentry from a high Mach number to touchdown. This necessitates the design of a controller such that the closed loop system remains stable for all possible plant perturbations and the response is admissible for every disturbance and command in the prescribed...
This paper deals with the attitude stabilization problem of highly aerodynamically unstable launch vehicle during atmospheric phase. The autopilot design is characterized by classical requirements such as Aero Margin (AM), Gain Margin GM), and Phase Margin (PM) as well as time-domain constraints on the response of angle of attack to a worst-case wind profile. These robustness requirements are difficult...