Add to ORKGIn this paper, we use SOS (sum of squares) programming approaches to analyze the stability and robustness properties of the controlled pitch axis (6 state system) of a nonlinear model of an aircraft. The controller is a LTI dynamic inversion based control law designed for the short period dynamics of the aircraft. The closed loop system is tested for its robustness to uncertainty in the location of center of gravity along the body x-axis. Results in the form of stability regions about a trim point are computed and verified using simulations
The current practice to validate flight control laws relies on applying linear analysis tools to ass...
A nonlinear flight controller is developed using dynamic inversion principles. The nonlinearities in...
In this paper we demonstrate the use of Approximate Dynamic Programming for the design of a pitch co...
In this paper, we use SOS (sum of squares) programming approaches to analyze the stability and robus...
Analysis of stability of the pitch axis of an aircraft has been a well studied problem. Historically...
Adaptive control has the potential to improve the performance and reliability of aircraft. However, ...
In this paper, we develop algorithms for the computational analysis of stability and robust performa...
A control analysis and design framework is proposed for systems subject to paramet-ric uncertainty. ...
Under review for publication in the Journal of Guidance, Control, and Dynamics.In lieu of extensive ...
The pitching movement of an aircraft is very important to ensure passengers are intrinsically safe a...
Summary. The current practice to validate flight control laws relies on applying linear analysis too...
In this paper we demonstrate how the recently developed sum of squares techniques can be used to ana...
This output describes an approach based on geometrical and optimisation principles that resulted in ...
Applications in many engineering fields require nonlinear modelling and control. However, for nonlin...
This thesis deals with high angle of attack behaviour of a generic delta wing model aircraft. A high...
The current practice to validate flight control laws relies on applying linear analysis tools to ass...
A nonlinear flight controller is developed using dynamic inversion principles. The nonlinearities in...
In this paper we demonstrate the use of Approximate Dynamic Programming for the design of a pitch co...
In this paper, we use SOS (sum of squares) programming approaches to analyze the stability and robus...
Analysis of stability of the pitch axis of an aircraft has been a well studied problem. Historically...
Adaptive control has the potential to improve the performance and reliability of aircraft. However, ...
In this paper, we develop algorithms for the computational analysis of stability and robust performa...
A control analysis and design framework is proposed for systems subject to paramet-ric uncertainty. ...
Under review for publication in the Journal of Guidance, Control, and Dynamics.In lieu of extensive ...
The pitching movement of an aircraft is very important to ensure passengers are intrinsically safe a...
Summary. The current practice to validate flight control laws relies on applying linear analysis too...
In this paper we demonstrate how the recently developed sum of squares techniques can be used to ana...
This output describes an approach based on geometrical and optimisation principles that resulted in ...
Applications in many engineering fields require nonlinear modelling and control. However, for nonlin...
This thesis deals with high angle of attack behaviour of a generic delta wing model aircraft. A high...
The current practice to validate flight control laws relies on applying linear analysis tools to ass...
A nonlinear flight controller is developed using dynamic inversion principles. The nonlinearities in...
In this paper we demonstrate the use of Approximate Dynamic Programming for the design of a pitch co...