Control augmentation system for flight vehicles

Claim 1

In a flight control system including a control stick, a mechanical gain means, a hydraulic boost actuator, and a control augmentation system including a rate gyroscope having an output, a first feedback path having a gain K ql driven by said rate gyroscope output, a second feedback path having a gain K qs driven by said rate gyroscope output, a control stick position transducer having an output, a first feedforward path having a gain K.sub.δl driven by said control stick position transducer output, a second feedforward path having a gain K.sub.δs driven by said control stick position transducer output, a first summing means for summing the outputs of said first feedback path and said first feedforward path, a pseudo-integrator means including an output driven by the output of said first summing means, a second summing means for summing the output of said psuedo-integrator, said second feedback path and said second feedforward path, and a servo actuator means for receiving the output of said second summing means for augmenting the mechanical gain of said flight vehicle whereby control of flight vehicle angular velocities in proportion to control input and stabilization of flight vehicle attitude is effected, an automatic series trim system comprising: (a) a hydraulic servo actuator displacement sensor; (b) a bi-directional switch; (c) a trim motor, and (d) a stability compensation path with gain K; wherein said system measures said hydraulic actuator displacement, and through said bi-directional switch operates said trim motor, whereby said trim motor adds to the output of said servo actuator causing control surface and vehicle motion.