摘要：AbstractStabilization of structural dynamic modes has utmost importance in the attitude control design of a launch vehicle. The flexibility stabilization problem becomes exceedingly grave when the vehicle engineering constraints impose restrictions on the available locations to mount the rate gyros. This paper discusses the flexibility stabilization challenge encountered during the attitude control design with two rate gyros located in the lower half (negative mode-slope region of first significant bending mode) of an aerodynamically unstable launch vehicle. Two novel options viz. a mode flipping based compensation technique and a generalized blending based virtual sensor placement technique were explored to tackle this issue. The relative merits and demerits of these approaches are discussed.
