Modeling and Simulation Research of Missile with Morphing Wings
With respect to a kind of missile with morphing wings, six-degree-of-freedom dynamics mathematical model including morphing wing dynamic was established using momentum principle, and guidance system model was presented, at the same time the whole attitude control system for missile with morphing wings was designed based on variable structure control theory. In order to prove the correctness of the validity of the altitude control strategy, under the environment of MATLAB6.5/ SIMUL1NK, the six-degree-of-freedom digital simulation system was studied and developed for the kind of missile with morphing wings. Finally simulation about non-maneuverable target and the snake-shape maneuverable target were conducted; the results validate the strong maneuverability and intercepting capability of the supersonic missile with morphing wings, and show the designed control method was effective to the attitude control system.
variable structure control nonlinear simulation model morphing wing
Guo Jian-guo Zhou Jun
Institute of Precision Guidance and Control Northwestern Polytechnical University Xian,China
国际会议
南京
英文
280-283
2010-08-26（万方平台首次上网日期，不代表论文的发表时间）