Interception guidance method and related device considering speed time variation and target maneuver

By establishing a three-dimensional guidance model based on time-varying velocity and target maneuvering, constructing a time-varying navigation ratio proportional guidance law, and adding a vertical acceleration component, the interception accuracy and stability issues under the influence of time-varying velocity and target maneuvering in existing technologies are solved, enabling high-precision missile interception in complex environments.

CN120141234BActive Publication Date: 2026-02-13BEIHANG UNIV +1
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Patent Information

Application Number
CN202510564109.6
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-04-30
Publication Date
2026-02-13
Estimated Expiration
2045-04-30

AI Technical Summary

Technical Problem

Existing guidance technologies fail to effectively consider the impact of time-varying velocity and target maneuvering on interception accuracy and stability. In particular, under conditions of large initial lead angle error and no velocity advantage, the interceptor's guidance analysis relies on target acceleration information and lacks comprehensiveness.

Method used

By acquiring the maneuvering parameters of the missile and the target, a three-dimensional guidance model is established under time-varying velocity and target maneuvering conditions. A time-varying navigation ratio proportional guidance law is constructed, and a vertical acceleration component is added to generate an improved augmented proportional guidance law. The missile's normal acceleration is decomposed into the pitch and yaw planes, and attitude control commands are generated based on the transformation between the inertial coordinate system and the velocity coordinate system to adjust the missile's flight trajectory in real time.

Benefits of technology

It improves the interception accuracy and stability of missiles in complex maneuvering environments, ensuring that missiles maintain a stable flight attitude during flight and achieve continuous tracking and precise interception of targets.

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Abstract

The application discloses an interception guidance method and related device considering speed time variation and target maneuvering, relates to the technical field of missile guidance, and comprises the following steps: acquiring missile maneuvering parameters and target maneuvering parameters; establishing a three-dimensional guidance model under the condition of speed time variation and target maneuvering according to the missile maneuvering parameters and the target maneuvering parameters; constructing a time-varying navigation ratio proportional guidance law based on the three-dimensional guidance model; increasing a vertical acceleration component on the basis of the time-varying navigation ratio proportional guidance law to generate an improved augmented proportional guidance law; decomposing a missile normal acceleration vector in a missile total acceleration vector to a pitch plane and a yaw plane, and generating an attitude control instruction based on the conversion between an inertial coordinate system and a speed coordinate system; and adjusting the attitude control instruction based on the real-time updated missile time-varying navigation ratio, the missile normal acceleration vector and the target maneuvering parameters to intercept the target. The application can effectively improve the interception precision and stability of the missile in a complex maneuvering environment.
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