基于Backstepping和扰动观测器的导引律

Abstract

Abstract:

This paper proposes a new guidance law which takes into consideration the guidance in cases of target maneuvers and autopilot dynamics and makes use of the disturbance observer (DOB) technology and the backstepping method. The guidance loop including the autopilot dynamics is divided into an outer loop and an inner loop. Target maneuvers and the cross coupling term of the pitch plane and the yaw plane are regarded as outer loop disturbances, while the autopilot parameter uncertainties are regarded as inner loop disturbances. The disturbance estimations derived by the disturbance observers are employed as feed-forward compensations to restrain the influence of target maneuver and autopilot dynamics on guidance performance, and they are also used to realize the decoupling of the two planes. A guidance law is designed to enable the actual acceleration of the missile to track the virtual control of the outer loop. Simulation results show that the proposed algorithm can achieve the goal of guidance effectively even when considering autopilot dynamics and highly maneuvering targets.

Key words: backstepping, disturbance observer, target maneuver, autopilot dynamics, 3D guidance law

CLC Number:

V488.13

ZHANG Jinpeng, YAN Jiejing, LI Shihua, LUO Sheng. A Guidance Law Design Based on Disturbance Observer and Backstepping[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(12): 2291-2300.

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A Guidance Law Design Based on Disturbance Observer and Backstepping

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