A detail analysis was presented for attitude control design of new-generation launch vehicles. First, rigid body dynamics models and fluid sloshing dynamics models were developed based on Newton-Euler equations, and then elastic dynamics models which suggest a potential for interaction between attitude control and the structural dynamics of the vehicle, was investigated based on finite element method. According to dynamic models, attitude control system was designed. Toward the end, the method to reduce aerodynamics loads and fault tolerance design was aimed. In order to enhance the reliability of launch vehicle, fault-tolerant reconfiguration system was designed, and servo system fault influence on attitude control system was considered. Accelerometer feedback was used to reduce the aerodynamic lateral loads caused by in-flight atmospheric. All the results derived form above research are well suit for attitude control design of new-generation launch vehicles.
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