A new proof for stability of delta operator simple adaptive control is presented in terms of a set of Linear Matrix Inequalities (LMIs). The paper shows how to design a feedforward gain to satisfy the LMIs over a polytope of loss of control effectiveness failures. The MATLAB Robust Control Toolbox is used to find the feedforward gain with the smallest norm that satisfies the LMIs. Examples are ...

Aircraft dynamics are in general nonlinear, time varying, and uncertain. A control system (classical control systems) designed for a flight condition, may not provide the desired stability and performance characteristics in case of deviation from the equilibrium point. There are numerous studies regarding flight control in the literature. One of them is fuzzy flight control system. In this stud...

This paper has maintained review and conclusion work upon the research and state of development of Man-Machine-Environment System Engineering (MMESE) technology applied in the aircraft design domain of China. The research development discussed involves: Preliminary design of MMESE of aircraft, environment control and Life-support system design of aircraft, and, the environment simulate of aircr...

The paper is devoted to approaches designing aircraft control systems based on the robust approach. Such a research of great importance for operated in conditions accompanied by perturbations. structural synthesis chosen as main tool problem solving. mathematical descriptions both deterministic and stochastic are considered. Dryden filter models represented. state-space approach used. H-infinit...

The role of feedback control in the solution of aircraft stability and control problems is discussed. It is argued that this role is becoming more and more important and is a key to meeting performance objectives for new aircraft. .4s a consequence, the control engineer must develop control laws for applications with many, sometimes conflicting, control objectives and stringent safety requireme...

Measurement of aircraft attitude is a necessary step for the autonomous control of the aircraft. Autonomous aircraft are useful for a range of military and civilian purposes. A method of very low computational complexity is presented that allows the pitch and roll angles of an aircraft to be measured onboard an unmanned aircraft from real-time video of the horizon. This method can be used for m...

This work considers the task of accurate in-air localization for multiple unmanned or autonomous aerial vehicles flying in close formation. The paper describes our experimental setup using two small UAVs and the details of the localization algorithm. The algorithm was implemented on two low-cost, electric powered, remote control aircraft with wing spans of approximately 2 meters. Our control so...

Today many aircraft control systems and process control industries are employing classical controller such as Proportional Integral Derivative Controller (PID) to improve the system characteristics and dynamic performance. To improve the stability analysis and system performance of an aircraft, PID controller is employed in this paper. The safety of flight envelope can be improved by tuning par...

This paper recalls a non-linear constructive method, based on controlling cascades of conic-systems as it applies to the control of quad-rotor aircraft. Such a method relied on the physical model of the system to construct highperformance, modest sampling period (Ts = .02 s) and lowcomplexity digital-controllers. The control of fixed-wing aircraft, however is not nearly a straight forward task ...