This paper proposed an improved method on the basis of the extended proportional guidance law. The method solved the weak observability problem of system sate in guided missile attacking maneuvering target. It is simple in form and easy for engineering implementation. This paper set up relative motion model and the observability theory indexes. The improved propotional guidance law is simulated using the MATLAB language. The simulation results show that the method is reasonable, effective and improving the observability.

This paper presents a project of missile guidance system based on the strapdown guidance technology. The project is composed of strapdown seeker and inertial measurement unit. The integrated guidance and control technology have been adopted. The project raise accuracy of missiles on the premise that the low cost should be guaranteed. According to simulation experiment, this paper proves the feasiblity of the scheme, and it has good ballistic missile.

This paper mainly talks about the Covariance Analysis Describing Equation Technique (CADET), which is used for the improved proportional guidance law. Firstly, the principle of this method is introduced. Secondly, the related conclusion and validation of Gaussian assumption is analyzed. Thirdly, an improved augmented proportional navigation guidance law (APNG) is analyzed by this method. Finally, the higher guidance accuracy of this improved APNG is demonstrated by stimulated experiments.

To determine the action angle of is the important topics on Trajectory Correction technology.The pulse force action angle and residual impact point deviation were theoretically analyzed on the basis of traditional control strategy of pulse jets. It has been found that there may be a large residual impact point deviation when the correction ability is different. An optimization strategy for the pulse force action angle control was presented, and the method was verified by the 6-degrees of freedom trajectory simulation.

Trajectory correction projectiles significantly improved shooting accuracy of conventional ammunition.This paper designed an impact point prediction algorithm based on perturbation theory, and proposed trajectory correction scheme based on the impact point prediction algorithm. Based on perturbation theory, getting samples by solving ideal trajectory and typical disturbed trajectory, and solving the coefficients of the prediction model by regression.The 6-degrees of freedom trajectory simulation shows that adopting this correction guidance law, the standard error of the longitudinal falling points of projectiles reduced significantly.