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Diagonally dominant backstepping autopilot for aircraft with unknown actuator failures and severe winds

Published online by Cambridge University Press:  27 January 2016

S. Ismail ,
A. A. Pashilkar ,
R. Ayyagari  and
N. Sundararajan
S. Ismail
Affiliation:
National Aerospace Laboratories, Bangalore, India
A. A. Pashilkar*
Affiliation:
National Aerospace Laboratories, Bangalore, India
R. Ayyagari
Affiliation:
National Institute of Technology, Tiruchirappalli, India
N. Sundararajan
Affiliation:
Nanyang Technological University, Singapore
*
[email protected]
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Abstract

A novel formulation of the flight dynamic equations is presented that permits a rapid solution for the design of trajectory following autopilots for nonlinear aircraft dynamic models. A robust autopilot control structure is developed based on the combination of the good features of the nonlinear dynamic inversion (NDI) method, integrator backstepping method, time scale separation and control allocation methods. The aircraft equations of motion are formulated in suitable variables so that the matrices involved in the block backstepping control design method are diagonally dominant. This allows us to use a linear controller structure for a trajectory following autopilot for the nonlinear aircraft model using the well known loop by loop controller design approach. The resulting autopilot for the fixed-wing rigid-body aircraft with a cascaded structure is referred to as the diagonally dominant backstepping (DDBS) controller. The method is illustrated here for an aircraft auto-landing problem under unknown actuator failures and severe winds. The requirement of state and control surface limiting is also addressed in the context of the design of the DDBS controller.

Type
Research Article
Information
The Aeronautical Journal , Volume 118 , Issue 1207 , September 2014 , pp. 1009 - 1038
Copyright
Copyright © Royal Aeronautical Society 2014 

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