Title :
Research on Attitude Law of Mass Moment Missile
Author :
Guo, Qing ; Yang, Ming ; Wang, Songyan
Author_Institution :
Control & Simulation Centre, Harbin Inst. of Technol.
Abstract :
An attitude control law based on fuzzy logic is presented for the mass moment missile in intra-atmospheric space. After constructing the model of the attitudinal movement with three -axial stabilization, the fuzzy rule tables corresponding to the moving mass position in respective axial are constituted. According to analysis of the relation between angular acceleration and searching condition, three moving mass positions are regulated in phase. Simultaneously the proportional differential (PD) parameters are offline revised using genetic algorithm according to the specific performance index. Simulation results show that the system stabilization can be satisfied to realize efficiently attitude adjustment for missile
Keywords :
PD control; attitude control; fuzzy control; genetic algorithms; missile control; stability; angular acceleration; attitude control; attitude law; fuzzy logic; genetic algorithm; mass moment missile; performance index; proportional differential parameters; searching condition; Aerodynamics; Attitude control; Control systems; Earth; Fuzzy logic; Genetic algorithms; Missiles; Space technology; Temperature control; Weight control; Fuzzy Rule Table; Mass Moment Missile; Moving Mass Position; Proportional Differential (PD) Parameter; Searching Condition;
Conference_Titel :
Mechatronics and Automation, Proceedings of the 2006 IEEE International Conference on
Conference_Location :
Luoyang, Henan
Print_ISBN :
1-4244-0465-7
Electronic_ISBN :
1-4244-0466-5
DOI :
10.1109/ICMA.2006.257514
