Abstract
The maneuvering of an aircraft requires design
and implementation of advance control techniques for both
longitudinal and lateral motion. The main objective of this
paper is to design an optimal controller for aircraft dynamics
in terms of quadratic performance index. The problem
formulation is carried out using different control techniques
like linear quadratic regulator (LQR) and linear matrix
inequalities (LMI). The controller design process begins with
obtaining appropriate mathematical model for aircraft
dynamics. The model is obtained using first principle
approach and linearized using small perturbation theory. Open
loop analysis is carried out for model using MATLAB and
results are obtained in step responses. The model response is
compared with LQR and LMI based results.The simulation
results reveal the effectiveness of these control techniques
applied and ensure stability of aircraft dynamics. Longitudinal
model of aircraft is used for analysis and aircraft used as
reference is Cessna 310.
Abdur Rasheed. (2017) LQR and LMI Based Optimal Control Design for Aircraft, Journal of Space Technology , Volume 7, Issue 1.
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