Terminal guidance method for maneuvering aircraft multi-terminal constraint backstepping sliding mode

Abstract

Provided is a terminal guidance method for maneuvering aircraft multi-terminal constraint backstepping sliding mode. The method comprises three main steps: step 1, analyzing terminal constraint of a terminal guidance problem and number; step 2, determining a sliding mode variable structure control order, designing a sliding variable quantity; step 3, and designing limited time backstepping, to obtain the guidance law of the whole system. The design basis of the method is the backstepping design of reaching in limited time, and the design of the terminal guidance law is a problem of reaching in a limited time. The backstepping design in variable structure control is a regression design method combining selection of a Lyapunov function and the design of a controller. Beginning from a minimum order differential equation of the system, the method designs in a stabilization manner layer by layer, and finally global stabilization is realized, so as to provide the control law of the whole system.

Description

technical field [0001] The invention belongs to the fields of aerospace technology and weapons, and relates to a multi-terminal constraint inversion sliding mode terminal guidance method for a mobile aircraft. Specifically, for the problem of terminal guidance of maneuvering aircraft, the guidance law obtained by this design method can enable the aircraft to meet various terminal constraints, such as terminal ballistic inclination constraints, normal overload constraints, etc., while reaching or hitting the target. Background technique [0002] When some maneuvering aircraft attack a fixed target, in addition to reducing the amount of misses, some special warheads expect to hit the target at a certain angle, so as to obtain better damage effects. For example, some re-entry maneuvering warheads need to fly in the direction of speed basically perpendicular to the ground in their terminal guidance section, so that the terminal guidance system can work normally. In addition, in...

AI Technical Summary

Problems solved by technology

Guidance law results are more complex when there are more terminal constraints to be considered

Moreover, the terminal normal overload constraint is seldom considered. The simulation results of some methods show that there may be a large normal acceleration at the end of the flight of the aircraft, and it is easy to have obvious misses in the case of uncertainty in the environment and related parameters.

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