In this paper, the three-dimensional terminal guidance problem of a missile intercepting a maneuvering target is studied. Augmented proportional navigation (PN) guidance laws based on Lyapunov stability theory are presented. Augmented terms are target accelerations such that proposed guidance laws have the ability to track the target maneuver. But, target accelerations cannot be accurately obtained in practice. To solve this problem, the nonlinear disturbance observer (NDOB) technology is introduced to estimate target accelerations. Estimated target accelerations will be employed as compensation terms in the proposed augmented PN guidance laws. Composite guidance laws combining augmented PN guidance laws with NDOB are proposed. Finally, simulation comparison results are provided to demonstrate the effectiveness of the presented guidance laws.
Guidance laws based on Lyapunov theory and DOB for three-dimensional missile-target interception
2014-08-01
152354 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Finite-time guidance laws for three-dimensional missile-target interception
Online Contents | 2016
|Finite-time guidance laws for three-dimensional missile-target interception
SAGE Publications | 2016
|Lyapunov-Based Nonlinear Missile Guidance
AIAA | 2004
|