An investigation has been made to determine the controllability of a large launch vehicle with limited thrust vectoring which permits the aerodynamic upset¬ting moment due to winds to exceed temporarily the control moment. The analysis was restricted to the pitch plane and included time-varying coefficients and lon¬gitudinal translation, normal translation, rigid-body pitch, and thrust-vectoring angle as degrees of freedom. A simple closed-loop control system utilizing atti¬tude and attitude-rate feedback was employed. The vehicle was flown vertically through 1-percent and 5-percent synthetic wind profiles on an analog computer.nThe results are presented as time histories of attitude angle and angle of attack and as plots of attitude angle against limit thrust-vectoring angle with the attitude gain and attitude-rate gain as parameters.
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