Tailless Aircraft Control Allocation
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| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1997 |
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This paper presents a flight controller for a tail-less aircraft with a large suite of conventional and unconventional control effectors. The controller structure is modular to take advantages of individual technologies from the areas of plant parameter estimation, control allocation, and robust feedback control. Linear models generated off-line provide plant parameter estimates for control. Dynamic inversion control provides direct satisfaction of flying qualities requirements in the presence of uncertainties. The focus of this paper, however, is control allocation. Control allocation is posed as constrained parameter optimization to minimize an objective that is a function of the control surface deflections. The control law is decomposed into a sequence of prioritized partitions, and additional optimization variables scale the control partitions to provide optimal command limiting which prevent actuator saturation. Analysis shows that appropriate prioritization of dynamic inversion control laws provides graceful command and loop response degradation for unachievable commands. Preliminary simulation results show that command variable response remains decoupled for unachievable commands while other command limiting methods may result in unacceptable coupled response.
| Author | : Wayne Durham |
| Publisher | : John Wiley & Sons |
| Total Pages | : 308 |
| Release | : 2017-01-17 |
| Genre | : Technology & Engineering |
| ISBN | : 1118827791 |
Aircraft Control Allocation Wayne Durham, Virginia Polytechnic Institute and State University, USA Kenneth A. Bordignon, Embry-Riddle Aeronautical University, USA Roger Beck, Dynamic Concepts, Inc., USA An authoritative work on aircraft control allocation by its pioneers Aircraft Control Allocation addresses the problem of allocating supposed redundant flight controls. It provides introductory material on flight dynamics and control to provide the context, and then describes in detail the geometry of the problem. The book includes a large section on solution methods, including 'Banks' method', a previously unpublished procedure. Generalized inverses are also discussed at length. There is an introductory section on linear programming solutions, as well as an extensive and comprehensive appendix dedicated to linear programming formulations and solutions. Discrete-time, or frame-wise allocation, is presented, including rate-limiting, nonlinear data, and preferred solutions. Key features: Written by pioneers in the field of control allocation. Comprehensive explanation and discussion of the major control allocation solution methods. Extensive treatment of linear programming solutions to control allocation. A companion web site contains the code of a MATLAB/Simulink flight simulation with modules that incorporate all of the major solution methods. Includes examples based on actual aircraft. The book is a vital reference for researchers and practitioners working in aircraft control, as well as graduate students in aerospace engineering.
| Author | : Ethem Hakan Orhan |
| Publisher | : |
| Total Pages | : 147 |
| Release | : 2020 |
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| ISBN | : |
Attempts to completely remove the tails from aircraft can be dated back to the early days of modern aviation. A number of stability and control problems arising from the unique characteristics of the configuration resulted in poor handling qualities and some dangerous flight characteristics in the early designs. Lately, this configuration is becoming widespread again and the current state-of-the-art of fly-by-wire technology and modern control design techniques enable design of tailless aircraft which are safe to fly. In this thesis, a study on the application of modern robust control design techniques on a tailless UAV is presented. A nonlinear mathematical model for the aircraft is constructed and control laws are synthesized using μ-synthesis approach. Three different scheduling methods are investigated for the control laws: ad-hoc linear interpolation, synthesis using simplified linear parameter varying models and stability preserving interpolation. A control allocation module is implemented to distribute the controller commands into highly coupled control effectors in real time. Two different allocation approaches are investigated: Cascaded Generalized Inverses and Weighted Least Squares. Effector limits and failure conditions are taken into account in an efficient way in allocation. A simulation study is performed using the nonlinear aircraft model, control laws, and control allocation models for various maneuvers and control effector failure cases.
| Author | : James F. Buffington |
| Publisher | : |
| Total Pages | : 154 |
| Release | : 1999-06-01 |
| Genre | : |
| ISBN | : 9781423539599 |
A modular flight control system is developed for a tailless fighter aircraft with innovative control effectors. Dynamic inversion control synthesis is used to develop a full envelope flight control law. Minor dynamic inversion command variable revisions are required due to the tailless nature of the configuration studied to achieve nominal stability and performance. Structured singular value and simulation analysis shows that robust stability is achieved and robust performance is slightly deficient due to modeling errors. A multi- branch linear programming based method is developed and used for allocation of redundant limited control effectors.
| Author | : James Buffington |
| Publisher | : |
| Total Pages | : 152 |
| Release | : 1999-06-01 |
| Genre | : |
| ISBN | : 9781423539490 |
A modular flight control system is developed for a tailless fighter aircraft with innovative control effectors. Dynamic inversion control synthesis is used to develop a full envelope flight control law, Minor dynamic inversion command variable revisions are required due to the tailless nature of the configuration studied to achieve nominal stability and performance. Structured singular value and simulation analysis shows that robust stability is achieved and robust performance is slightly deficient due to modeling errors. A multi- branch linear programming-based method is developed and used for allocation of redundant limited control effectors.
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| Publisher | : |
| Total Pages | : 0 |
| Release | : 2000 |
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The objective of the project was to develop and analyze methods for control in the presence of actuator saturation. Algorithms were investigated for control allocation, that is, for the problem of distributing control requirements among redundant actuators. A new implementation of the direct allocation method of Durham was proposed. The direct allocation method was chosen because it utilized all of the attainable moment set. A special representation of the moment set in spherical coordinates was considered to speed-up the real- time computations and two rapid search methods were developed and successfully implemented. The direct allocation method was also extended to systems that had previously been excluded, namely those for which subsets of three actuator commands produce linearly dependent moments. Testing of the algorithms was performed using simulation models of a military transport aircraft and of a tailless aircraft.
| Author | : Guillaume J. J. Ducard |
| Publisher | : Springer Science & Business Media |
| Total Pages | : 268 |
| Release | : 2009-05-14 |
| Genre | : Technology & Engineering |
| ISBN | : 1848825617 |
This book offers a complete overview of fault-tolerant flight control techniques. Discussion covers the necessary equations for the modeling of small UAVs, a complete system based on extended Kalman filters, and a nonlinear flight control and guidance system.
| Author | : Karl Nickel |
| Publisher | : Hodder Education |
| Total Pages | : 520 |
| Release | : 1994 |
| Genre | : Business & Economics |
| ISBN | : |
Discusses the range of tailless designs, from hanggliders to the US 'Stealth Bomber', and includes a detailed look at particularly significant designs. The authors' own experience in this field allows them to explain and illustrate the topic in a way that appeal to the enthusiast and satisfies the professional aerodynamicist.
| Author | : Mirza Tariq Hamayun |
| Publisher | : Springer |
| Total Pages | : 208 |
| Release | : 2016-04-29 |
| Genre | : Technology & Engineering |
| ISBN | : 3319322389 |
The key attribute of a Fault Tolerant Control (FTC) system is its ability to maintain overall system stability and acceptable performance in the face of faults and failures within the feedback system. In this book Integral Sliding Mode (ISM) Control Allocation (CA) schemes for FTC are described, which have the potential to maintain close to nominal fault-free performance (for the entire system response), in the face of actuator faults and even complete failures of certain actuators. Broadly an ISM controller based around a model of the plant with the aim of creating a nonlinear fault tolerant feedback controller whose closed-loop performance is established during the design process. The second approach involves retro-fitting an ISM scheme to an existing feedback controller to introduce fault tolerance. This may be advantageous from an industrial perspective, because fault tolerance can be introduced without changing the existing control loops. A high fidelity benchmark model of a large transport aircraft is used to demonstrate the efficacy of the FTC schemes. In particular a scheme based on an LPV representation has been implemented and tested on a motion flight simulator.
| Author | : Scott R. Wells |
| Publisher | : |
| Total Pages | : 624 |
| Release | : 2002 |
| Genre | : Technology & Engineering |
| ISBN | : |
Observer-based sliding mode control is investigated for application to aircraft reconfigurable flight control. An overview of reconfigurable flight control is given, including a review of the current state-of-the-art within the subdisciplines of fault detection parameter identification, adaptive control schemes, and dynamic control allocation. Of the adaptive control methods reviewed, sliding mode control (SMC) appears promising due its property of invariance to matched uncertainty. An overview of SMC is given and its properties are demonstrated. Sliding mode methods, however, are difficult to implement because unmodeled parasitic dynamics cause immediate and severe instability. This presents a challenge for all practical applications with limited bandwidth actuators. One method to deal with parasitic dynamics is the use of an asymptotic observer. Observer-based SMC is investigated, and a method for selecting observer gains is offered. An additional method for shaping the feedback loop using a filter is also developed. It is shown that this SMC prefilter is equivalent to a form of model reference hedging. A complete design procedure is given which takes advantage of the sliding mode boundary layer to recast the SMC as a linear control law. Frequency domain loop shaping is then used to design the sliding manifold. Finally, three aircraft applications are demonstrated. An F-18/HARV is used to demonstrate SISO and MIMO designs. The third application is a linear six degree-of-freedom advanced tailless fighter model. The observer-based SMC is seen to provide excellent tracking with superior robustness to parameter changes and actuator failures.
