Multi-missile cooperative engagement guidance method based on model predictive control technique

Abstract

The invention discloses a multi-missile cooperative engagement guidance method based on a model predictive control technique. Through the adoption of the multi-missile cooperative engagement guidance method, the cooperative engagement problem of missiles is converted into a theoretical trajectory tracking problem on the premise of considering the variable missile speed; the estimation of the residual flight time is avoided; the accuracy and the realizability are improved; meanwhile, the model prediction control technique is adopted, so that an ideal trajectory can be quickly and accurately tracked in the presence of external interference and angle attack and amplitude limit.

Description

technical field [0001] The invention relates to the field of guidance technology, in particular to a multi-missile cooperative combat guidance method based on model predictive control technology. Background technique [0002] With the advancement of science and technology, the missile defense system is being gradually improved, and the penetration capability of missiles is seriously threatened. The saturation attack of multiple missiles on the target is an important means to improve the missile's battlefield survivability and strike ability, and it is attracting more and more attention. Therefore, under the premise of considering the actual situation of the battlefield, it is of great significance to study the cooperative guidance method that can make multiple missiles reach the target at the same time and has attack time constraints. [0003] At present, when the existing technology solves the problem of coordinated guidance technology for multiple missiles to reach the ta...

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Problems solved by technology

[0004] 1. It is generally assumed that the speed of the missile is a constant value. However, in the actual process, it is difficult to ensure that the speed of the missile is a constant value. The speed of the missile will change due to changes in thrust, flight altitude or external disturbances.

[0005] 2. The problem of estimating the remaining flight time of the missile

In the actual flight process, it is difficult to accurately estimate the remaining flight time of the missile, especially when the speed of the missile changes with time, the accurate estimation of the remaining flight time becomes more difficult

[0006] 3. During the flight of the missile, it is often subject to various disturbances such as random wind, but the existing technology is more concerned with the coordinated guidance under ideal conditions

[0007] 4. The deflection of the rudder surface of the missile is limited, that is, the input of the missile control system has nonlinear saturation, which leads to the limitation of the variation of the angle of attack

However, prior art does not consider

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