Guidance method, device and aircraft for multi-aircraft anti-intercept coordinated strike

Abstract

The present disclosure provides a multi-aircraft anti-intercept coordinated strike guidance method, device and aircraft. In the method of the present disclosure, the state data of the attacking aircraft, the intercepting aircraft and the target object are obtained respectively, wherein the state data includes: position information, speed and acceleration, and the guidance law of the attacking aircraft is obtained according to the state data and the three-body differential strategy model, Among them, the three-body differential game model is built by reducing the order of the combat linear kinematics and dynamics model according to the zero-control miss amount, and established according to the reduced order of the combat linear kinematics and dynamics model and the time multiplier, and the time multiplier is introduced. The terminal time is unified for all reduced-order models, and the global performance index is established. Based on the differential game theory, the saddle point solution is obtained, which is the optimal guidance law for the tripartite. In this way, the multi-aircraft penetration missile group interception operation is realized, so that the multi-aircraft can avoid the interception of the intercepting aircraft with the maximum maneuverability, and accurately strike the target object.

Description

technical field [0001] The present disclosure relates to the field of aerospace technology, and in particular to a guidance method, device and aircraft for multi-aircraft anti-intercept coordinated strike. Background technique [0002] Guidance is the technology and method to guide and control the aircraft to fly to the target object or predetermined orbit according to a certain law. [0003] The traditional guidance methods are all aimed at the two-body attack problem of the attacking aircraft hitting the target object. From the perspective of optimality, the optimally controlled guidance law can give the optimal solution when the terminal conditions are satisfied under a given linear model. , the model is that some nonlinear control or ballistic planning guidance laws can complete the guidance in the case of nonlinearity. [0004] When the attacking aircraft hits the target object, there will be intercepting aircraft based on various anti-missile systems to intercept the ...

AI Technical Summary

Problems solved by technology

The guidance law obtained by the above-mentioned two-party modeling method only for the attacking aircraft and the target object cannot meet the situation of three-party combat, so the accuracy of the obtained guidance law is not high

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