An Optimal Predictive Guidance Method for Air Combat Three-Body Confrontation Using Golden Section Search

Abstract

The invention relates to the field of aerospace technology, and discloses an optimal prediction and guidance method for air combat three-body confrontation using golden section search, including: establishing a kinematics model for air combat three-body confrontation against three warring parties, and selecting optimization indicators according to the real-time motion states of the three warring parties Function, using the golden section method to optimize the solution to obtain the optimal remaining interception time, integrate the motion state of the incoming missile to the remaining interception time and select it as a virtual target point, and use the proportional guidance law to guide the defensive missile with the virtual target point as the target. Based on the idea of ​​prediction, this method considers the coupled state of the aircraft in the air combat three-body confrontation scene in the design of the guidance law, selects the future relative distance as the optimization index, and optimizes the nonlinear coupling motion model. The designed guidance law effectively improves the defense The probability of missile interception reduces the amount of misses, and the required guidance overload is smaller than that of traditional guidance laws, which enables low-performance defensive missiles to complete the interception of high-speed and high-mobility incoming missiles.

Description

technical field [0001] The invention relates to the field of anti-missile technology, in particular to an optimal predictive guidance method for air combat three-body confrontation using golden section search, which is suitable for guidance and control of aerospace vehicles. Background technique [0002] The three-body confrontation problem in air combat is composed of aircraft, incoming missiles, and defensive missiles. The incoming missiles target the aircraft for guided attacks, and the aircraft needs to launch defensive missiles to guide and intercept the incoming missiles, so as to complete self-defense. Since this problem includes not only the interception and guidance of defensive missiles to incoming missiles, but also the coupling relationship between aircraft and maneuvers to avoid incoming missiles, the design of defensive guidance laws is very difficult, and has attracted extensive attention at home and abroad in recent years. [0003] In the traditional guidance...

AI Technical Summary

Problems solved by technology

[0003] In the traditional guidance law research, the guidance law is mainly designed for one-to-one situations, but in the three-body confrontation scenario of air combat, the relative speed of the defensive missile and the incoming missile is relatively high. The coupling relationship, the amount of misses caused by guidance is large, the accuracy is low, the guidance demand overload is high, and the guidance energy consumption is also large

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