Sliding Mode Integrated Missile Guidance and Control
A novel method for the integrated guidance and control of a missile, called Sliding Mode Integrated Guidance and Control (SMIGC), is derived. In this formulation, the guidance and control systems are developed together and implemented in a single loop. One benefit of this “integrated” approach is that beneficial synergies between the guidance and control subsystems can be exploited. The design process can also be significantly reduced since only one control architecture must be designed. SMIGC makes use of the finite-time reaching phase of the sliding mode technique to ensure that a desired constraint, the Predicted Impact Point (PIP) heading error, is achieved in a finite time. Furthermore, the robustness of sliding mode to uncertainties is combined with a novel method for accounting for target acceleration to yield acceptable miss distances against maneuvering targets. An interesting and desirable aspect of the controller is that it does not require full information about the target acceleration. Further, to fully understand the effects of target acceleration on the problem, an in-depth target acceleration uncertainty analysis is performed. The effectiveness of the SMIGC approach is demonstrated through a series of simulations with a 6-DOF nonlinear missile model that includes all aerodynamic effects against maneuvering targets. Representative numerical results show that against agile targets, SMIGC obtains a high Hit-to-Kill accuracy consistently with reasonable fin deflections. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
N. Harl et al., "Sliding Mode Integrated Missile Guidance and Control," AIAA Guidance, Navigation, and Control Conference, American Institute of Aeronautics and Astronautics (AIAA), Jan 2010.
The definitive version is available at https://doi.org/10.2514/6.2010-7741
AIAA Guidance, Navigation, and Control Conference (2010, Toronto, ON)
Mechanical and Aerospace Engineering
Article - Conference proceedings
© 2010 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.