Physical systems such as air vehicles are inherently nonlinear and complex. A complete treatment of air vehicle from design, modeling, analysis, and simulation until control design for vehicle autonomy demands, therefore, application of tools from nonlinear dynamics and control theories. Blending dynamical systems theory and nonlinear control techniques provides a unique and physically intuitive methodology for developing control algorithms for various complex tasks. Our recent works on highly nonlinear aircraft models have led to the development of a generic simulation platform for guidance, control, and navigation of six degree-of-freedom (dof) air vehicles in a completely nonlinear framework. An overview of the nonlinear framework involved in the development of the unique platform and its applications to maneuvering and waypoint navigation of two vehicle models are presented in the paper. © 2019 IEEE.

Nandan Kumar Sinha

Department of Aerospace Engineering

Air navigation

Blending

Control theory

Degrees of freedom (mechanics)

Dynamical systems

Maneuverability

SIMULATION PLATFORM

Control design

ITS applications

NON-LINEAR AIRCRAFT MODELS

Nonlinear control technique

NONLINEAR DYNAMICS AND CONTROLS

Physical systems

Six degree-of-freedom

VEHICLE AUTONOMY

Aircraft control

IIT Madras is a public technical and research university located in Chennai, Tamil Nadu. Founded in 1959, it is recognised as an Institute of National Importance.

IIT Madras has been ranked as the top engineering institute in India for four years in a row by the National Institutional Ranking Framework of the MHRD

It currently offers undergraduate, postgraduate and research degrees across 16 disciplines in Engineering, Sciences, Humanities and Management. About 596 faculty belonging to science and engineering departments and centres of the Institute are engaged in teaching, research and industrial consultancy.

IIT Madras

Integrated Nonlinear System Framework for Air Vehicle Autonomy Design and Validation

2019 5th Indian Control Conference, ICC 2019 - Proceedings

Tools based on the bifurcation and continuation method have been found to be extremely useful for studying multiparameter nonlinear dynamical systems under state and parameter-constrained conditions. Because of inherent limitations of the existing methodologies, however, application of continuation techniques to certain types of problems has remained cumbersome and even computationally challenging. This paper provides an alternate direct approach in MATLAB® using its continuation subroutine MATCONT to extend the capabilities of continuation techniques in an attempt to accommodate a wide variety of constrained dynamics problems. Published results in the literature are first reproduced for validation of the proposed approach. A control problem of scheduling gains for the longitudinal flight dynamics of an aircraft is next presented to show usefulness of the proposed methodology, followed by solutions to an aircraft conceptual design problem involving wing morphing with eigenvalue constraints, with the difficulties of the selected problems increasing in that order.

Fulltext

Journal of Aircraft

Direct methodology for constrained system analysis with applications to aircraft dynamics

In this paper, bifurcation analysis-based methodology is used in conjunction with a sliding-mode-based control algorithm to construct and simulate maneuvers for a nonlinear, 6 degree-of-freedom, F-18 high-alpha research vehicle aircraft model. Three different types of maneuvers, namely, a minimum-radius level turn, velocity vector roll, and spin recovery to a level flight condition, are attempted to demonstrate the usefulness of the proposed approach. The procedure involves constructing the desired maneuvers using constrained bifurcation analysis-based methodology. The results obtained from bifurcation analysis provide the reference inputs for the sliding mode controller to switch the aircraft between desired flight conditions. Robustness of the sliding mode controller is also examined by introducing uncertainties in aerodynamic parameters. Closed-loop simulation results are later presented to show the effectiveness of the proposed technique. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc.

Journal of Guidance, Control, and Dynamics

Aircraft maneuver design using bifurcation analysis and sliding mode control techniques

Advanced Flight Dynamics with Elements of Flight Control

Elementary Flight Dynamics with an Introduction to Bifurcation and Continuation Methods

Handbook of Marine Craft Hydrodynamics and Motion Control

Journal	Data powered by Typeset2019 5th Indian Control Conference, ICC 2019 - Proceedings
Publisher	Data powered by TypesetInstitute of Electrical and Electronics Engineers Inc.
Open Access	No