Download or read book Modular Control Law Design for the Innovative Control Effectors ICE Tailless Fighter Aircraft Configuration 101 3 written by James F. Buffington and published by . This book was released on 1999-06-01 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Modular Control Design for the Innovative Control Effectors ICE Tailless Fighter Aircraft Configuration 101 3 written by James Buffington and published by . This book was released on 1999-06-01 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aircraft Control Allocation written by Wayne Durham and published by John Wiley & Sons. This book was released on 2017-01-17 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book The Control Handbook written by William S. Levine and published by CRC Press. This book was released on 2018-10-08 with total page 944 pages. Available in PDF, EPUB and Kindle. Book excerpt: At publication, The Control Handbook immediately became the definitive resource that engineers working with modern control systems required. Among its many accolades, that first edition was cited by the AAP as the Best Engineering Handbook of 1996. Now, 15 years later, William Levine has once again compiled the most comprehensive and authoritative resource on control engineering. He has fully reorganized the text to reflect the technical advances achieved since the last edition and has expanded its contents to include the multidisciplinary perspective that is making control engineering a critical component in so many fields. Now expanded from one to three volumes, The Control Handbook, Second Edition organizes cutting-edge contributions from more than 200 leading experts. The second volume, Control System Applications, includes 35 entirely new applications organized by subject area. Covering the design and use of control systems, this volume includes applications for: Automobiles, including PEM fuel cells Aerospace Industrial control of machines and processes Biomedical uses, including robotic surgery and drug discovery and development Electronics and communication networks Other applications are included in a section that reflects the multidisciplinary nature of control system work. These include applications for the construction of financial portfolios, earthquake response control for civil structures, quantum estimation and control, and the modeling and control of air conditioning and refrigeration systems. As with the first edition, the new edition not only stands as a record of accomplishment in control engineering but provides researchers with the means to make further advances. Progressively organized, the other two volumes in the set include: Control System Fundamentals Control System Advanced Methods

Download or read book The Control Handbook three volume set written by William S. Levine and published by CRC Press. This book was released on 2018-10-08 with total page 3526 pages. Available in PDF, EPUB and Kindle. Book excerpt: At publication, The Control Handbook immediately became the definitive resource that engineers working with modern control systems required. Among its many accolades, that first edition was cited by the AAP as the Best Engineering Handbook of 1996. Now, 15 years later, William Levine has once again compiled the most comprehensive and authoritative resource on control engineering. He has fully reorganized the text to reflect the technical advances achieved since the last edition and has expanded its contents to include the multidisciplinary perspective that is making control engineering a critical component in so many fields. Now expanded from one to three volumes, The Control Handbook, Second Edition brilliantly organizes cutting-edge contributions from more than 200 leading experts representing every corner of the globe. They cover everything from basic closed-loop systems to multi-agent adaptive systems and from the control of electric motors to the control of complex networks. Progressively organized, the three volume set includes: Control System Fundamentals Control System Applications Control System Advanced Methods Any practicing engineer, student, or researcher working in fields as diverse as electronics, aeronautics, or biomedicine will find this handbook to be a time-saving resource filled with invaluable formulas, models, methods, and innovative thinking. In fact, any physicist, biologist, mathematician, or researcher in any number of fields developing or improving products and systems will find the answers and ideas they need. As with the first edition, the new edition not only stands as a record of accomplishment in control engineering but provides researchers with the means to make further advances.

Download or read book Application of Sliding Mode Methods to the Design of Reconfigurable Flight Control Systems written by Scott R. Wells and published by . This book was released on 2002 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Dynamic Inversion based Adaptive reconfigurable Control of the X 33 on Ascent written by David B. Doman and published by . This book was released on 2002 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: A quaternion-based attitude control system is developed for the X-33 in the ascent flight phase. A nonlinear control law commands body-axis rotation rates that align the angular velocity vector with an Euler axis defining the axis of rotation that will rotate the body-axis system into a desired-axis system. The magnitudes of the commanded body rates are determined by the magnitude of the rotation error. The commanded body rates form the input to a dynamic inversion-based adaptive/reconfigurable control law. The indirect adaptive control portion of the control law uses online system identification to estimate the current control effectiveness matrix to update a control allocation module. The control allocation nominally operates in a minimum deflection mode; however, if a fault is detected, it can operate in a null-space injection mode that excites and decorrelates the effectors without degrading the vehicle response to enable online system identification. The overall 5 stem is designed to provide fault and damage tolerance for the X-33 on ascent.

Download or read book Advances in Guidance Navigation and Control written by Liang Yan and published by Springer Nature. This book was released on 2023-02-10 with total page 7455 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book features the latest theoretical results and techniques in the field of guidance, navigation, and control (GNC) of vehicles and aircrafts. It covers a wide range of topics, including but not limited to, intelligent computing communication and control; new methods of navigation, estimation and tracking; control of multiple moving objects; manned and autonomous unmanned systems; guidance, navigation and control of miniature aircraft; and sensor systems for guidance, navigation and control etc. Presenting recent advances in the form of illustrations, tables, and text, it also provides detailed information of a number of the studies, to offer readers insights for their own research. In addition, the book addresses fundamental concepts and studies in the development of GNC, making it a valuable resource for both beginners and researchers wanting to further their understanding of guidance, navigation, and control.

Download or read book Innovative Control Effectors ICE written by E. L. Roetman and published by . This book was released on 1996 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a joint U.S. Air Force. U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. Land-based and carrier-based configurations were analyzed to determine the flying qualities, performance, and aircraft-level integration impacts of the innovative controls. Six control concepts were evaluated for their potential to provide sufficient lateral-directional control power to a highly maneuverable tailless fighter. They were: (1) split ailerons; (2) movable chine strakes; (3) seamless leading and trailing edge flaps; (4) pneumatic forebody devices; (5) wing leading edge blowing; (6) wing mounted yaw vanes. After a preliminary screening, only the first two and a new concept, variable dihedral horizontal tails were chosen for further investigation. Detailed evaluations of the three selected controllers against baseline fighter configurations with vertical tails included low-speed, high-speed, and high AOA flying qualities performance, structural weight and subsystem integration impacts, signature performance, and carrier suitability impacts. The variable dihedral horizontal tail was evaluated as the best all-round control effector of those investigated. The split aileron and movable chine strake were ranked 2nd and 3rd, respectively.

Download or read book Quantitative Feedback Theory written by Constantine H. Houpis and published by CRC Press. This book was released on 2018-10-03 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt: The first edition of Quantitative Feedback Theory gained enormous popularity by successfully bridging the gap between theory and real-world engineering practice. Avoiding mathematical theorems, lemmas, proofs, and correlaries, it boiled down to the essential elements of quantitative feedback theory (QFT) necessary to readily analyze, develop, and implement robust control systems. Thoroughly updated and expanded, Quantitative Feedback Theory: Fundamentals and Applications, Second Edition continues to provide a platform for intelligent decision making and design based on knowledge of the characteristics and operating scenario of the plant. Beginning with the fundamentals, the authors build a background in analog and discrete-time multiple-input-single-output (MISO) and multiple-input-multiple-output (MIMO) feedback control systems along with the fundamentals of the QFT technique. The remainder of the book links these concepts to practical applications. Among the many enhancements to this edition are a new section on large wind turbine control system, four new chapters, and five new appendices. The new chapters cover non-diagonal compensator design for MIMO systems, QFT design involving Smith predictors for time delay systems with uncertainty, weighting matrices and control authority, and QFT design techniques applied to real-world industrial systems. Quantitative Feedback Theory: Fundamentals and Applications, Second Edition includes new and revised examples and end-of-chapter problems and offers a companion CD that supplies MIMO QFT computer-aided design (CAD) software. It is the perfect guide to effectively and intuitively implementing QFT control.

Download or read book Control Law Synthesis for Lockheed Martin s Innovative Control Effectors Aircraft Concept written by Cameron James Segard and published by . This book was released on 2019 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis documents a conventional and modern flight control system design process carried out on a tailless aircraft Simulink model with innovative control effectors provided by Lockheed Martin. To set scope and design requirements a performance analysis was carried out to categorize the aircraft. Evaluation of open-loop dynamics reveled modal instabilities as well as state and control coupling. Flight condition dependent pole migration mapping reveled large changes in the aircraft’s static stability. Leading to the development of a four channel proportional-integral- derivative (PID) stability and control augmentation system (SCAS) controlling pitch-rate, roll-rate, side-slip angle, and airspeed states. PID gains are scheduled via iterative constrained optimization throughout the linearized flight envelope generating a full flight envelope flight control system. The linear quadratic (LQ) servo design method provides optimal control allocation at every linearized flight condition, controlling angle of attack, roll angle, side-slip angle, and airspeed states. LQ controlled states were modified to be equivalent to the PID control system for real time handling qualities (HQ) evaluation. Both control systems required gain scaling to prevent state resonance and control saturation during nonlinear 6-degree-of-freedom (6DOF) real-time simulation. Either method achieved stable augmented control of the innovative control effectors (ICE) aircraft throughout the flight envelope. The HQ’s for the control methods are satisfactory for conventional aerobatics but became dissimilar for sustained super-maneuverability flight conditions.

Download or read book Robust Flight Control of Rotorcraft written by Adam Daniel Pechner and published by . This book was released on 2010 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Control Surface Deflection Effects on the Innovative Control Effectors ICE 101 Design written by Gregory A. Addington and published by . This book was released on 2000 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static wind tunnel test of the Innovative Controls Effectors (ICE 101) conceptual aircraft configuration was conducted in the Air Force Research Laboratory's Vertical Wind Tunnel. This entry characterized the increments to the aerodynamic loading provided by the various control surfaces while using a more finely-resolved test matrix in angle of attack and sideslip than typically seen in wind tunnel testing. The purpose for obtaining these data was to determine the effect which control surface deflection had on critical state locations in preparation for the test of a second ICE model built with remotely- actuated control surfaces. (Critical states are discrete flight mechanical states where the aerodynamic response looses its analytic dependence on one or more state variables.) These data demonstrate that the aerodynamic increments are in many cases at minimum nonlinear functions of the surface deflection angle, and strongly suggest that some critical states do shift in angle of attack and/or sideslip with changing deflection angle.

Download or read book Fault Tolerant Optimal Trajectory Generation for Reusable Launch Vehicles written by Patrick J. Shaffer and published by . This book was released on 2006 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reconfigurable inner-loop control laws improve the fault tolerance of a vehicle to control effector failures; however, in order to preserve stability, the unfailed effectors may be deployed to off-nominal positions to compensate for undesirable perturbations caused by the failed effectors. The effectors acting under the influence of a reconfigurable control law can produce significant perturbations to the nominal forces produced by the wing and body and can also affect the range of flight conditions over which the vehicle can be controlled. Three degree-of-freedom (3 DOF) dynamical models used in trajectory optimization for aerospace vehicles typically include wing-body aerodynamic force effects but ignore the aerodynamic forces produced by the control surfaces. In this work, a method for including these trim effects as well as control induced trajectory constraints in a 3 DOF model is presented.

Download or read book Improving Control Allocation Accuracy for Nonlinear Aircraft Dynamics written by David B. Doman and published by . This book was released on 2002 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: The forces and moments produced by a vehicle's aerodynamic control surfaces are often nonlinear functions of control surface deflection. This phenomenon limits the accuracy of state-of-the-art control allocation algorithms since all of the approaches are based on the assumption that the control variable rates are linear functions of the surface deflections and that control variable rate increments are not produced for zero deflections. The errors introduced by this assumption are currently mitigated by the robustness resulting from feedback control laws. A method for improving the performance of the feedback control/control allocation system is presented that directly attacks the inaccuracies introduced by these linear assumptions.

Download or read book Innovative Control Effectors ICE Phase III written by Kenneth M. Dorsett and published by . This book was released on 1997 with total page 420 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the Phase 2 portion of a joint U.S. Air Force U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. The Phase 1 work consisted of effector performance prediction, vehicle integration assessment, and transition studies for numerous control effector concepts. The Phase 2 effort is an extension of the Phase 1 work and consists mainly of three wind tunnel tests to acquire more information about the aerodynamic performance of all moving wing tips (AMTs) and spoiler slot deflectors (SSDs). These tests clearly showed both the AMT and SSD can produce significant yaw control power and are strong control effector candidates for tailless fighters. Predicted vehicle dynamics from Phase 1 are compared with predictions developed utilizing the new aerodynamic data acquired in Phase 2.

Download or read book Model Predictive Control Synthesis for the Innovative Control Effector Tailless Fighter Aircraft written by Christopher Charles Proctor and published by . This book was released on 2019 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: A nonlinear model predictive control law was developed for the Lockheed Martin Innovative Control Effector tailless fighter aircraft to track way points. In general, aircraft are described by nonlinear dynamics that are dependent on the regime of flight. Additionally strict requirements on state and actuator constraints are common to all aircraft. Tailless aircraft are usually overdetermined systems, meaning solutions to control problems are not unique, and the system is non-affine. The proposed nonlinear control law considers those constraints during run-time, and solves the nonlinear control problem for a range of points within different flight regimes. The control law was developed using a computer simulation of the tailless fighter aircraft, and further simulation was used to validate the control law when applied to the aircraft. It was found that the controller was able to track reference step commands in altitude anywhere from sea level to 50,000 ft and remain stable. It is also shown that the single nonlinear controller is able to handle lateral translations at the same time as altitude commands, demonstrating its authority over the entire 6 degree of freedom system. The controller is not real time applicable but research indicates that it is possible to apply such a technique in real time. It was concluded that nonlinear model predictive control is a viable control synthesis technique for tailless fighter aircraft if real-time algorithms can be developed.