Multi-missile designated time cooperative interception terminal guidance method

By constructing a fixed-time neural network interference observer and a specified-time error model, a multi-missile specified-time cooperative interception terminal guidance method was designed, which solved the computational efficiency problem of multiple interceptor missiles in hypersonic target interception and achieved a highly efficient interception effect.

CN121007466BActive Publication Date: 2026-06-09HARBIN INST OF TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-10-15
Publication Date
2026-06-09

AI Technical Summary

Technical Problem

Existing technologies for intercepting hypersonic targets suffer from computational efficiency issues in the guidance law design of multiple interceptor missiles, and their interception capability is insufficient under short interception time windows and limited overload constraints, making it difficult to effectively improve the interception probability.

Method used

A fixed-time neural network jamming observer is used to estimate the target's maneuverability and velocity changes. Based on a specified time error model, a specified-time cooperative interception guidance law is designed to construct a guidance model for intercepting maneuvering targets. The expression for the estimated remaining flight time is derived, and a specified-time interception guidance law for hypersonic targets is designed.

Benefits of technology

It effectively solves the computational efficiency problem in the guidance law design of multiple interceptor missiles coordinating to intercept hypersonic targets within a specified time, and achieves precise interception of hypersonic targets within a specified time.

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Abstract

The present application relates to the field of guidance method, disclose a plurality of missile specified time cooperative interception terminal guidance method, including the following steps, the guidance model of intercepting maneuvering target is constructed, the expression of the estimated remaining flight time is derived according to the guidance model of intercepting maneuvering target, the specified attack time error is defined according to the estimated remaining flight time expression, the expression of the first derivative of the estimated remaining flight time is derived according to the specified attack time error, the specified attack time error is derived and estimated by using fixed time neural network disturbance observer, the hypersonic target specified time interception guidance law is designed, the specified time interception of the hypersonic target is realized based on the proposed fixed time neural network disturbance observer and the specified time interception guidance law, the method of the present application effectively solves the problem of the calculation efficiency of the guidance law design of the specified time cooperative interception of the hypersonic target by multiple interception missiles.
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Citation Information

Patent Citations

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  • Self-adaptive appointed attack time guidance method and device for striking maneuvering target, medium and product

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