I. Introduction With the increase in demand and capacity, Air Traffic Management (ATM) will face further challenges to keep delay considerably low while increasing safety standards at a cheaper cost. When addressing t...
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I. Introduction With the increase in demand and capacity, Air Traffic Management (ATM) will face further challenges to keep delay considerably low while increasing safety standards at a cheaper cost. When addressing these challenges imposed by future ATM programs (SESAR, NextGen), controllers will need sophisticated decision support tools to deal with upcoming traffic flows in an efficient way. As it was pointed out in the Performance Review Report 2010 , [12], 5 % of all flights in Europe are held on the ground to manage en-route congestion, resulting in more than 50 % of all delay minutes within the system. In the future, air navigation service providers (ANSPs) will need to deliver more capacity, in a cheaper, safer, and environmental-friendlier way. This goal will not be achieved without the aid of sophisticated and automated tools that will assist the human air traffic controller (ATCO). One of the air traffic management fields that can contribute to provide to future capacity is separation management . In the context of this paper, separation management is the task of separating aircraft in an allocated airspace volume as efficiently as possible. The aim of this paper is to present the application of optimal control theory in a central- ized approach to separation management, where we use information of the current traffic situation in a sector to derive an optimal control problem. The solution of this control problem consecutively provide conflict-free trajectories for all users within the regarded airspace. Solutions are obtained by using a direct method that is composed of multiple shooting discretization and a sequential quadratic programming (SQP) method to solve the resulting nonlinear optimization problem.
This paper presents a robust predictive control method with uncertainty quantification for problems, such as online aircraft flutter suppression. The proposed approach begins by identifying the multistep output predic...
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This paper presents a robust predictive control method with uncertainty quantification for problems, such as online aircraft flutter suppression. The proposed approach begins by identifying the multistep output prediction matrices under various test conditions from online time-domain input/output data. Singular value decomposition is then used to characterize and quantify the parameter uncertainties of the prediction matrices. The predicted response error due to parameter uncertainties is integrated into the predictivecontrol design process for robustness. The proposed method provides an innovative and efficient way to incorporate the quantified uncertainty in predictivecontrol design with a linear process. The proposed approach is demonstrated by application to the Benchmark Active controls Technology wind-tunnel model.
This paper describes autonomous unmanned aerial vehicle (UAV) guidance technologies developed and demonstrated in a flight test sponsored by the DARPA Software Enabled control program. The flight experiment took place...
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This paper describes autonomous unmanned aerial vehicle (UAV) guidance technologies developed and demonstrated in a flight test sponsored by the DARPA Software Enabled control program. The flight experiment took place in June 2004 using a Boeing UAV testbed and demonstrated important autonomy capabilities enabled by a receding horizon guidance controller and fault detection filter. The receding horizon controller (RHC) design process is presented in detail as well as demonstration scenarios which were designed to exercise and evaluate the primary functionalities;of the control system. Simulation results of the key capabilities are shown and compared with recorded flight data for evaluation purposes. Hardware-in-the-loop simulations and other high-fidelity test run results illustrate secondary capabilities such as controller reconfiguration due to actuator fault and maneuvering limit enforcement using output constraints in the receding horizon approach.
The nonlinear control theories based upon the model predictivecontrol and the nonlinear inverse control are used to develop four-dimensional guidance controllers, the conversion of the primary trajectory being assume...
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The nonlinear control theories based upon the model predictivecontrol and the nonlinear inverse control are used to develop four-dimensional guidance controllers, the conversion of the primary trajectory being assumed by a specific solution to the inverse kinematics problem, The control task is simplified by using the forced singular perturbation theory, overall system dynamics being separated into the fast and slow reduced-order systems and separately controlled. The algorithm performances are evaluated in the case of a conventional transport aircraft that tracks a four-dimensional trajectory defined by flight levels, waypoints, and an estimated time of arrival. The predictivecontrol and dynamic inversion are compared as basic algorithms for the fast-dynamics control in view of establishing performances and limits.
This paper discusses aircraft terrain-following flight control law development based on a new nonlinear optimal predictive control method, The control law minimizes the predicted difference between the actual trajecto...
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This paper discusses aircraft terrain-following flight control law development based on a new nonlinear optimal predictive control method, The control law minimizes the predicted difference between the actual trajectory and a smooth open-loop reference trajectory that satisfies the aircraft dynamic model, A fixed point algorithm is used to compute sequentially the tracking control commands from the implicit control law, Globally asymptotically stable tracking of the reference trajectory is proved in the absence of control saturation, and the influences of the controller parameters on the tracking dynamics are identified. Numerical simulations are presented for a supersonic fighter aircraft model over a standard test terrain, These simulations include the effects of initial condition errors, aerodynamic modeling inaccuracies, and vertical wind disturbances.
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