To decrease the effect slope of aiming line error of radome on the guidance control system of missile, the design of guidance controller was served as the parameter optimization, and optimization model was set up.
Based on the above, the limitations set by the radome error upon the design of the guidance controller are analyzed, and boundary conditions are obtained.
Guidance controller design for the (nonlinear and time varying) model of a real missile shows that it is very difficult to design satisfactory guidance controllers when the boundary conditions are not satisfied.
In this paper,the stability of a kind of missile guidance system is analyzed,and the effect of the perturbation of radome slope A on the stability is investigated. Based on this research,this paper presents a robust guidance controller design method.
To overcome the disadvantage of existing guidance controller, a kind of miniaturizing, power saving and high performance alternative is urgently in need.
In this paper,authors recount the short distance hitting top guidance law,the hardwareand software design of the guidance controller,the connection with YHF2 Simulation Computer in theSemi-physical simulation.
It then sends this path to the vehicle guidance controller and feeds back the cost of the path to the task planner.
例句来源
In this paper,authors recount the short distance hitting top guidance law,the hardwareand software design of the guidance controller,the connection with YHF2 Simulation Computer in theSemi-physical simulation.The accuracy and speed of A/D converter,fixed point arithmetic,floatingpoint arithmetic,the isolation and anti-interference when connecting with YHF2 Simulation Computerhave been discussed in detail.
The stability of a kind of missile guidance system is analyzed, and the effect of perturbation of radome boresight error slope A on the stability is investigated. A conclusion can be drawn strictly that the effect of radome error on missile performance degradation only relates to the perturbation of radome boresight error slope A , the numerator of coupled loop transfer function and the pitch turning time constant. Based on the above, the limitations set by the radome error upon the design of...
In this paper,the stability of a kind of missile guidance system is analyzed,and the effect of the perturbation of radome slope A on the stability is investigated.Based on this research,this paper presents a robust guidance controller design method.Simulation results show that guidance controllers designed by using this method have satisfactory robustness performance.The presented method has been applied to the control system design of certain type of missile and has given ...