Combined guidance target interception method and system

Abstract

The invention relates to a combined guidance target interception method and system. The method comprises the following steps: determining a true proportional navigation TPN guidance command acceleration; determining a pure proportional navigation PPN guidance command acceleration in a capture condition range in a line-of-sight instantaneous-rotation plane; determining a combined guidance command acceleration according to the TPN guidance command acceleration and the PPN guidance command acceleration; and controlling an interception missile to intercept a target according to the combined guidance command acceleration. According to the technical scheme, the advantages of PPN guidance and TPN guidance are combined, the calculated amount is small, the dependence degree of the combined guidance on measurement information and target estimation information is low, the robustness is high, the time needed for interception is shortened, the missile and target line-of-sight can achieve rapid convergence, the trajectory in the later period of interception is stable, energy needed for interception is small, and rapid interception of the target can be realized in the near space.

Description

technical field [0001] The invention relates to the technical field of target interception, in particular to a combined guidance target interception method and system. Background technique [0002] For the interception of hypersonic targets in near space, it is necessary to achieve zero miss interception of the target. The existing interception methods include the pure proportional guidance law PPN based on differential geometric guidance to intercept the target and the true proportional guidance based on the line of sight rotation plane. Attraction TPN intercepts the target. [0003] The pure proportional guidance law PPN based on differential geometric guidance intercepts the target: the acceleration of the guidance command is perpendicular to the velocity direction of the interceptor, which can realize the rapid convergence of the line of sight of the projectile, and is designed for interceptor missiles that are greatly affected by aerodynamic forces in the atmosphere. T...

AI Technical Summary

Problems solved by technology

[0003] The pure proportional guidance law PPN based on differential geometric guidance intercepts the target: the acceleration of the guidance command is perpendicular to the velocity direction of the interceptor, which can realize the rapid convergence of the line of sight of the projectile, and is designed for interceptor missiles that are greatly affected by aerodynamic forces in the atmosphere. The flying airspace of the intercepted target subject to technical research is the adjacent space, and the atmosphere in the adjacent space is thin. Compared with the lower atmosphere, the interceptor bomb is less affected by aerodynamic forces; and the parameter e required for the guidance command r 、e θ 、e ω , All rely on the accuracy of the filtering algorithm, the guidance performance is closely related to the information obtained by filtering, and the error and time delay are difficult to eliminate, which is not conducive to engineering realization

[0004] The target is intercepted based on the true proportional guidance law TPN in the line of sight rotation plane: the acceleration of the guidance command is perpendicular to the direction of the line of sight, the convergence speed of the projectile line of sight is slow, the overload is required in the later stage of interception, the ballistic trajectory is obviously curved, and the probability of missing the target is relatively high

Images