A combined guidance target interception method and system

Abstract

The invention relates to a combined guidance target interception method and system. The method includes: determining the acceleration of the true proportional guidance law TPN guidance command; determining the acceleration of the pure proportional guidance law PPN guidance command within the range of capture conditions in the instantaneous rotation plane of the line of sight; The acceleration of the combined guidance command is determined according to the acceleration of the TPN guidance command and the acceleration of the PPN guidance command; and the interceptor is controlled to intercept the target according to the acceleration of the combined guidance command. The technical solution disclosed in the present invention combines the advantages of PPN guidance and TPN guidance, and has a small amount of calculation. The combined guidance law is less dependent on measurement information and target estimation information, has strong robustness, and shortens the time required for interception. The projectile line of sight can achieve rapid convergence, the interception trajectory is stable in the later stage, the interception requires less energy, and the target can be quickly intercepted in the adjacent 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...

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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

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