Three-dimensional omnidirectional real-time prediction guidance method

Abstract

The invention relates to the technical field of anti-missile, and discloses a three-dimensional omnidirectional real-time prediction guidance method. The method comprises the steps of: establishing auniform acceleration kinematics model of a three-dimensional incoming missile and a defense missile, using a current motion state of the incoming missile and the defense missile according to the kinematics model as an input calculation prediction interception point position at every moment, using the defense missile to take the prediction interception point position as a target at every moment, designing a guidance law according to a way of intercepting a stationary target, and calculating prediction guidance demand overload of the defense missile. The three-dimensional omnidirectional real-time prediction guidance method uses a predictive idea to design the guidance law, converts an original high-speed moving and maneuvering incoming target into an equivalent predictive intercepting target with low-speed motion. Compared with a traditional guidance law, facing a large azimuth incoming target at close range, the three-dimensional omnidirectional real-time prediction guidance method reduces off-target, the interception accuracy is improved, the robustness to the target uncertainty maneuver is enhanced, the intercept range is wider, and the interception time is shorter.

Description

technical field [0001] The invention relates to the field of anti-missile technology, in particular to a three-dimensional omnidirectional real-time predictive guidance method, which is suitable for guidance and control of aerospace vehicles. Background technique [0002] In missile defense missions, guidance technology is a key link in the success of interception. The current mainstream guidance law research mainly includes the classical guidance method represented by proportional guidance law and the modern guidance method based on modern control theory. The current missile interception guidance law has the following problems: [0003] First, when dealing with high-speed and maneuvering targets, the traditional guidance method has a large amount of misses and low accuracy. [0004] Second, the traditional guidance method usually requires the defense missile to point to the target area when launching, and if the incoming missile strikes from the side or a large azimuth an...

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Problems solved by technology

[0003] First, when dealing with high-speed and maneuvering targets, the traditional guidance method has a large amount of misses and low precision

[0004] Second, the traditional guidance method usually requires the defense missile to point to the target area when launching, and if the incoming missile strikes from the side or a large azimuth angle at a short distance, and the defense missile has to be launched in a fixed direction, the line-of-sight angular velocity of the defense missile is relatively slow. Large, the required interception overload will exceed the allowable overload of its own performance, so it is difficult to meet the short-range omnidirectional defense

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