Nonlinear Simulation Framework Based on Bifurcation Analysis for Controlled Airship Maneuvering
07 Jan 2019-
About: The article was published on 2019-01-07. It has received 1 citations till now. The article focuses on the topics: Nonlinear system.
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TL;DR: An adaptive horizontal trajectory control method for stratospheric airships in uncertain wind field using Q-learning algorithm and a cerebellar model articulation controller neural network is designed to optimize the action strategy for each state.
22 citations
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08 Apr 2011
TL;DR: In this article, the authors present a survey of the latest tools for analysis and design of advanced guidance, navigation and control systems and present new material on underwater vehicles and surface vessels.
Abstract: The technology of hydrodynamic modeling and marine craft motion control systems has progressed greatly in recent years. This timely survey includes the latest tools for analysis and design of advanced guidance, navigation and control systems and presents new material on underwater vehicles and surface vessels. Each section presents numerous case studies and applications, providing a practical understanding of how model-based motion control systems are designed.
1,389 citations
TL;DR: A new approach based on a new method called the reaching law method, and complemented by a sliding-mode equivalence technique, facilitate the design of the system dynamics in all three modes of a VSC system including the sliding, reaching, and steady-state modes.
Abstract: A new approach for the design of variable structure control (VSC) of nonlinear systems is presented. It is based on a new method called the reaching law method, and is complemented by a sliding-mode equivalence technique. They facilitate the design of the system dynamics in all three modes of a VSC system including the sliding, reaching, and steady-state modes. Invariance and robustness properties are discussed. The approach is applied to a robot manipulator to demonstrate its effectiveness. >
1,165 citations
TL;DR: In this paper, the authors examined optimal ascent trajectories that use wind energy to achieve minimum-time and minimum-energy flights in a 3D point-mass model of a Stratospheric Airship.
Abstract: Stratospheric airships are lighter-than-air vehicles that have the potential to provide an extremely-long-duration airborne presence at altitudes of 18―22 km. In this paper, we examine optimal ascent trajectories that use wind energy to achieve minimum-time and minimum-energy flights. The airship is represented by a three-dimensional point-mass model, and the equations of motion include aerodynamic lift and drag, vectored thrust, added mass effects, and accelerations due to mass-flow rate, wind rates, and Earth rotation. A representative wind profile is developed based on historical meteorological data and measurements. Trajectory optimization is performed by first defining an optimal control problem with both terminal and path constraints, then using direct collocation to develop an approximate nonlinear parameter optimization problem of finite dimension. Optimal ascent trajectories are determined using SNOPT for a variety of upwind, downwind, and crosswind launch locations. Results of extensive optimization solutions illustrate definitive patterns in the ascent path for minimum-time flights across varying launch locations and show that significant energy savings can be realized with minimum-energy flights, compared with minimum-time flights, given small increases in flight time. In addition, the effects of time-varying mass and Earth rotation are found to be comparable with the effects of wind rate, and they are used in the optimal solutions.
59 citations
08 Jan 2007
TL;DR: The state-of-the-art in the use of bifurcation and continuation methods for the analysis of aircraft trim and stability with a few illustrative examples are described.
Abstract: The bifurcation and continuation methodology has evolved over the last two decades into a powerful tool for the analysis of trim and stability problems in aircraft flight dynamics. Over the years, bifurcation methods have been employed to deal with a variety of problems in aircraft dynamics, such as predicting high angle of attack behavior, especially spin, and studying instabilities in rolling maneuvers. The bifurcation methodology has served as a tool for the design of flight control systems, and is promising to be a useful tool in the aircraft design, simulation, testing, and evaluation process. In the present paper, we describe the state-of-the-art in the use of bifurcation and continuation methods for the analysis of aircraft trim and stability with a few illustrative examples. Both the standard and extended bifurcation analysis procedures are discussed and typical results for instabilities in high-α flight and in inertia-coupled roll maneuvers are shown. This is followed by several problems in nonlinear flight dynamics where bifurcation and continuation methods have been fruitfully applied to yield effective solutions. Finally, the use of bifurcation theory to arrive at analytical instability criteria is demonstrated for the aircraft roll coupling and wing rock problems. 76 references have been cited in the text.
57 citations
TL;DR: In this paper, a discontinuous control law is derived that accomplishes asymptotic decoupled output trajectory-following in the presence of uncertainty in the system, based on variable-structure system theory.
Abstract: The question of control of a class of nonlinear systems that can be decoupled by state-variable feedback is considered. Based on variable-structure system theory, a discontinuous control law is derived that accomplishes asymptotic decoupled output trajectory-following in the presence of uncertainty in the system. In the closed-loop system, the trajectories are attracted toward a chosen hypersurface in the state space and then slide along it. During the sliding phase the motion is insensitive to parameter variations. Based on this result, a control law for asymptotically decoupled control of roll angle, angle of attack, and sideslip in rapid, nonlinear maneuvers is derived. Simulation results are presented to show that large, simultaneous lateral and longitudinal maneuvers can be performed in spite of uncertainty in the stability derivatives. >
47 citations