Searched for: contributor%3A%22Chu%2C+Q.P.+%28mentor%29%22
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Ferrier, Y.L. (author)
This paper presents a novel active gust load alleviation approach within a multi-objective flight control framework developed by NASA for a flexible wing aircraft. The aircraft model is based on the NASA Generic Transport Model (GTM). The wing structures incorporate an aerodynamic control surface known as the Variable Camber Continuous Trailing...
master thesis 2017
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Van der Sman, E.S. (author)
Maintaining stable flight during high turbulence intensities is challenging for fixed-wing micro air vehicles. Two methods have been identified to improve the disturbance rejection performance of the MAV: incremental nonlinear dynamic inversion and phase-advanced pitch probes. Incremental nonlinear dynamic inversion uses the angular acceleration...
master thesis 2016
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Uzumcu, S. (author)
An Apache AH-64D simulation model designed by Boeing and McDonnell Douglas, is used to improve the handling qualities of this helicopter to level 1 during both good and degraded visual environments for the full helicopter flight envelope. This project results from the design phase of a follow-up project with the goal of extending an Incremental...
master thesis 2016
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van Ekeren, W. (author)
In the context of fault-tolerant flight control (FTFC), various types of incremental nonlinear control methods have been previously proposed that should overcome important challenges that are imposed by the use of nonlinear, model-based flight control systems. This work presents an analysis, design and implementation of promising incremental...
master thesis 2016
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van 't Veld, R.C. (author)
Incremental Nonlinear Dynamic Inversion (INDI) is a variation on Nonlinear Dynamic Inversion (NDI) retaining the high-performance advantages of NDI, while increasing controller robustness to model uncertainties and decreasing the dependency on the vehicle model. After a successful flight test with a multirotor Micro Aerial Vehicle (MAV), the...
master thesis 2016
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Schallig, S.A.V. (author)
Future space platforms, such as next-generation Earth imaging and missile-tracking satellites, require rapid rotational maneuverability. Currently, most European satellites use reaction wheels as momentum exchange device for their Attitude Control System. However, reaction wheels do not produce enough torque to meet the high slew rate...
master thesis 2016
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Van Baelen, D. (author)
Simulator control loading systems are used to replicate the forces felt on the control devices. In the actual vehicle, the control system is a passive system whereas the simulator requires an actuator. The actuator imposes the forces on the control device which results in an active system. As this actuator has an inherent time delay, the energy...
master thesis 2016
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Tal, E.A. (author)
Recent developments in airframe design include the increasing application of modern lightweight materials. Airframe designs based on composite materials are able to provide sufficient structural strength at lower mass, but often have decreased structural rigidity. Flight vehicles with relatively flexible structures exhibit more prominent...
master thesis 2015
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Van Gils, P. (author)
This thesis deals with the development of Adaptive Incremental Backstepping control laws for a high-performance aircraft model (F-16), in order to make the airplane robustly seek references in roll rate and angle of attack at a constant airspeed while minimizing sideslip. An Incremental Backstepping scheme that relies on estimates of the angular...
master thesis 2015
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Tang, S.H. (author)
A worldwide civil aviation accident survey for the period of 2002 till 2011, conducted by the CAA-UK shows that in this time period nearly 40% of all the aircraft accidents involved loss of control. Despite the fatal outcomes, reconfigurable flight control might have been able to recover the aircraft by efficiently utilizing the remaining...
master thesis 2014
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Govindarajan, N. (author)
This dissertation presents an optimal control framework to determine a collection of open-loop command signals, that mathematically guarantees operation of a dynamical system within prescribed state constraints. The framework is applied to estimate real-time command margins for aircraft control systems so that, safe operation within the flight...
master thesis 2012
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Kers, M. (author)
master thesis 2012
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Koschorke, J.F.R. (author)
The sensor-based approach of Incremental Backstepping is applied to flight control law design in this research project. It allows the usage of the same control law on different types of aircraft without the need for redesign. Apart from full state availability, the derivation of Incremental Backstepping assumes instantaneous control action. Due...
master thesis 2012
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Mendes, A.S. (author)
The development of systems that allow unmanned aerial vehicles, known as UAVs, to perform tasks autonomously is a current trend in aerospace research. The specific aim of this thesis is to study and achieve vision-based automatic landing of a quadrotor UAV on a floating platform, a known target that possesses oscillatory behavior. The research...
master thesis 2012
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Acquatella, B.P.J. (author)
In order to meet requirements in terms of robustness, stability, and performance for future generations of advanced attitude control systems, a sensor-based approach using Incremental Backstepping control is developed and proposed in this thesis. Assuming full state availability and fast control action, the resulting time-scale separation...
master thesis 2011
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Fragoso Trigo, G. (author)
In the context of the initiative Formation for Atmospheric Science and Technology demonstration (FAST), this dissertation describes the design and comparison of several nonlinear attitude controllers for TU Delft’s micro-satellite. The control requirements include robustness against model uncertainties and disturbances. To this end, Backstepping...
master thesis 2011
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Simplicio, P. (author)
Due to the inherent instabilities and nonlinearities of rotorcraft dynamics, its changing properties during flight and the difficulties to predict its aerodynamics with high levels of fidelity, helicopter flight control requires strategies that allow to cope with the nonlinearities of the model and assure robustness in the presence of...
master thesis 2011
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Hummelink, B.A. (author)
Today, there is an increase in the use of Unmanned Aerial Vehicles (UAV's), for applications that can be considered dull, dirty or dangerous when compared to those applications of conventional aircraft or helicopters. To further increase the use of UAV's, their navigation filters must be robust and reliable. The trend in current autopilot...
master thesis 2011
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Grotens, R. (author)
Nonlinear Dynamic Inversion (NDI) is a promising method for Fault Tolerant Flight Control. The NDI algorithm cancels out the aircraft dynamics based on a dynamic aircraft model such that the closed loop system behaves linearly. The aircraft model is estimated online, which allows it to accommodate changes in the aircraft configurations and...
master thesis 2010
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Verveld, M.J. (author)
This work addresses the problem of indoor state estimation for autonomous flying vehicles with an optic flow approach. The paper discusses a sensor configuration using six optic flow sensors of the computer mouse type augmented by a three-axis accelerometer to estimate velocity, rotation, attitude and viewing distances. It is shown that the...
master thesis 2009
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