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