摘要
研究了大气层内旋转导弹的变质心轨道控制问题.建立了内部带有2个可移动质量块的系统运动方程,应用线性系统理论论证了轨道控制的必要性,提出了制导控制中导航比的选取原则.结合旋转弹变质心制导控制系统的运行特性设计了系统的制导控制律,计算滑块的命令位置来产生期望的系统质心偏移,达到改变导弹飞行弹道的目的.典型弹道的非线性仿真证明了该控制器可有效控制旋转弹的飞行轨道.
The ability of a moving-mass trajectory control system to control an aerospace spinning vehicle was investigated. The nonlinear motion equations of the system with two internal moving elements were established. By applying the linear control system theory, the necessity to the vehicle of the guidance controller was proved, as well as the selected principle by which the navigation coefficients were calculated, was presented. With the characteristics of the moving mass trajectory control system for the spinning vehicle, the navigation control algorithm was presented to position the internal masses independently in order to deliver a desired mass center of system, and the modest flight path corrections were generated. A nonlinear simulation of a typical mission profile demonstrates the ability of the controller to control trajectory of the spinning vehicle effectively.
出处
《弹道学报》
EI
CSCD
北大核心
2006年第2期1-4,共4页
Journal of Ballistics
基金
国家自然科学基金项目(60434010)
关键词
非线性控制系统
制导控制
飞行轨道
仿真
nonlinear control system
navigation control
trajectory
simulation
