Stability Analysis of a Missile Control System with a Dynamic Inversion Controller-Reference-Cited by-同舟云学术

Stability Analysis of a Missile Control System with a Dynamic Inversion Controller

Published:1998-05 Issue:3 Volume:21 Page:508-515
ISSN:0731-5090
Container-title:Journal of Guidance, Control, and Dynamics
language:en
Short-container-title:Journal of Guidance, Control, and Dynamics

Author:

Schumacher Corey¹,Khargonekar Pramod P.²

Affiliation:

1. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433-7531

2. University of Michigan, Ann Arbor, Michigan 48109-2122

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.4266

Reference13 articles.

1. Nonlinear control law with application to high angle-of-attack flight

2. Nonlinear inversion flight control for a supermaneuverable aircraft

3. Schumacher, D. A. “Tactical Missile Autopilot Design Using Nonlinear Control,” Ph.D. Thesis, Dept. of Aerospace Engineering,Univ. of Michigan, Ann Arbor, MI,1994.

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