Download or read book Reconfigurable Flight Control System for a STOL Aircraft Using Quantitative Feedback Theory written by Bruce T. Clough (1LT, USAF.) and published by . This book was released on 1985 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reconfigurable Flight Control System for a STOL Short Take Off and Landing Aircraft Using Quantitative Feedback Theory written by Bruce T. Clough and published by . This book was released on 1984 with total page 223 pages. Available in PDF, EPUB and Kindle. Book excerpt: Future aircraft may incorporate many control surfaces to meet stringent performance and aerodynamic efficiency requirements. These many surfaces increase the survivability of the aircraft by providing redundant control in the event of surface failures. The design of a flight control system that automatically redistributes control authority among the remaining surfaces in the event of failure is a significant challenge. A control law sufficiently robust to encompass the dynamic uncertainty, as well as surface failures, is desired. Quantitative Feedback Theory (QFT) developed by Dr. Isaac Horowitz promises to yield robustness without identification. QFT inherently includes uncertainty and control system failures within the design procedure. One a priori designs for acceptable system responses with uncertainty and failures, making QFT well suited for designing aircraft flight control systems. This thesis uses QFT in the design of a flight control system for a future Air Force Short-Take-Off-and Landing (STOL) experimental aircraft. The aircraft has additional control surfaces not found on current aircraft. Hence it provides an excellent platform for demonstrating reconfigurable flight control system design.
Download or read book Flight Control System Reconfiguration Design Using Quantitative Feedback Theory written by P. B. Arnold and published by . This book was released on 1984 with total page 253 pages. Available in PDF, EPUB and Kindle. Book excerpt: Quantitative theory is used to develop control laws for the AFTI/F-16 with a reconfigurable flight control system. Compensators are synthesized to control pitch rate and roll rate through individually controlled elevators and flaperons. Robust control of these variables is required over a larger portion of the flight envelope despite flight control surface failures. Linearized aerodynamic data are used to develop the aircraft model in state-variable format. The longitudinal and lateral-directional equations are coupled in the control matrix. Individual control of the elevators and flaperons is obtained by dividing the dimensionalized control derivatives for a control surface pair in half and assigning each surface of the pair one-half of the total derivative value. The system with individually controlled surfaces represents a four input-two output system which is transformed into an equivalent two input-two output system for each control surface configuration and flight condition. Quantitative feedback theory is then applied to the equivalent systems. Originator-supplied keywords included: Inherent Reconfiguration; Loop Transmission; Flight control Systems; Quantitative Feedback Theory; Control Systems; Computer Programs; Theses.
Download or read book Quantitative Feedback Theory written by Constantine H. Houpis and published by CRC Press. This book was released on 1999-08-27 with total page 435 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the interface between the technical literature's theoretical results and the problems that practising engineers face - and that engineering students will face - every day on the job. It demonstrates the extensive applications of quantitative feedback theory and seeks to bridge the gap between theory and practice. The book contains a user's manual and QFT design program on CD-ROM, to provide faster, easier access to design applications.
Download or read book Robust and Reconfigurable Flight Control System Design written by Wichai Siwakosit and published by . This book was released on 2001 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Digital Rate Controller for the Control Reconfigurable Combat Aircraft Design Using Quantitative Feedback Theory written by Kurt N. Neumann and published by . This book was released on 1988 with total page 149 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this thesis is to develop a digital controller using Quantitative Feedback Theory for a fighter aircraft with unstable, nonminimum phase dynamics that meets performance specifications despite surface failures. Aircraft design trends for highly maneuverable fighter aircraft are relaxing stability requirements in order to increase performance in the transonic and supersonic regions. However, as a result, the aircraft is statically unstable in the subsonic region which makes the flight control system critical to flight safety. The conventional approach to the flight safety problem is to provide multiple redundancy throughout the fight control system. However, QFT provides an alternative to excessive hardware. The three controlled states are the pitch, roll, and yaw rates. A weighting matrix is derived which linearly combines the nine control surfaces into three control inputs. The plant is converted to a certain plane using the Hoffman algorithm. Three constant gain controllers and three prefilters are designed for a single flight condition of 0.9 Mach and 30000 ft altitude. The controllers and prefilters are transformed to the z plane for simulation purposes. The design is simulated with healthy plant and 24 combinations of surface failures. Keywords: Control theory, Multivariate control. (KR).
Download or read book Flight Control System Reconfiguration Design Using Quantitative Feedback Theory written by Phillip B. Arnold (MAJ, USAF.) and published by . This book was released on 1984 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Reconfigurable Flight Control Designs with Application to the X 33 Vehicle written by John J. Burken and published by . This book was released on 1999 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two methods for control system reconfiguration have been investigated. The first method is a robust servomechanism control approach (optimal tracking problem) that is a generalization of the classical proportional-plus-integral control to multiple input-multiple output systems. The second method is a control-allocation approach based on a quadratic programming formulation. A globally convergent fixed-point iteration algorithm has been developed to make onboard implementation of this method feasible. These methods have been applied to reconfigurable entry flight control design for the X-33 vehicle. Examples presented demonstrate simultaneous tracking of angle-of-attack and roll angle commands during failures of the right body flap actuator. Although simulations demonstrate success of the first method in most cases, the control-allocation method appears to provide uniformly better performance in all cases.
Download or read book A Digital Rate Controller for the Control Reconfigurable Combat Aircraft Designed Using Quantitative Feedback Theory written by Kurt N. Neumann (CAPT, USAF.) and published by . This book was released on 1988 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reconfigurable Flight Control System for Fighter Aircraft Using Mpc written by Bilal Siddiqui and published by LAP Lambert Academic Publishing. This book was released on 2012 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this work we studied Reconfigurable Flight Control Systems to achieve acceptable performance of a fighter aircraft, even in the event of wing damage to the aircraft at low speeds and high angle of attack, which is typical of many combat maneuvers. Equations of motion for the damaged aircraft were derived, which helped in building simulators. A new methodology for numerical prediction of aerodynamics of damaged aircraft was proposed and implemented. A baseline control system for undamaged aircraft was developed, and finally a reconfigurable flight control scheme was implemented to keep the aircraft flyable even after the damage. In this study we proposed a hybrid reconfigurable flight control system (RFCS) which was a fusion of active and passive techniques. We derived equations of motion for the damaged aircraft. The new approach to derivation lends insight into possible simplification in building simulators for damaged aircraft. A new methodology for better prediction of damaged aircraft aerodynamics. Fixed gain controller was found to be inadequate for controlling the damaged aircraft. For alleviating this a novel reconfigurable scheme based on MPC is evaluated.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Robust Digital Flight Control System for an Unmanned Research Vehicle Using Discrete Quantitative Feedback Theory written by and published by . This book was released on 1991 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis describes application of digital multiple-input multiple- output (MIMO) Quantitative Feedback Theory (QFT) technique to the design of a three axis rate controller for the Lambda Unmanned Research Vehicle. The resulting robust controller performs well throughout the flight envelope without gain scheduling. It results from research done at the Air Force Institute of Technology. The Lambda URV was designed by the Control Systems Development Branch of the Wright Laboratory at Wright-Patterson AFB, OH for flight testing aircraft control hardware and software. The flight control system is built using a small perturbation linear model developed from flight test data. The actuators, also modelled from aircraft test data, are second order in roll and pitch and first order in yaw. Nineteen separate plants are used to represent the flight envelope of the aircraft resulting from variations in speed, altitude, center of gravity location, and weight. The sample rate is 50 Hertz. The pitch channel is decoupled from the lateral-directional resulting in a single-input single-output (SISO) system for the pitch channel and a two-by-two MIMO system for the lateral-directional channel. The design employs the Nichols Chart and is accomplished in the w'-domain.
Download or read book Design of Integrated Flight propulsion Control Loaws of a STOL Aircraft During Approach and Landing Using Quantitative Feedback Theory written by Barry S. Migyanko (2LT, USAF.) and published by . This book was released on 1986 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Robust Multivariable Flight Control written by Richard J. Adams and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 175 pages. Available in PDF, EPUB and Kindle. Book excerpt: Manual flight control system design for fighter aircraft is one of the most demanding problems in automatic control. Fighter aircraft dynamics generally have highly coupled uncertain and nonlinear dynamics. Multivariable control design techniques offer a solution to this problem. Robust Multivariable Flight Control provides the background, theory and examples for full envelope manual flight control system design. It gives a versatile framework for the application of advanced multivariable control theory to aircraft control problems. Two design case studies are presented for the manual flight control of lateral/directional axes of the VISTA-F-16 test vehicle and an F-18 trust vectoring system. They demonstrate the interplay between theory and the physical features of the systems.
Download or read book Proceedings of the 1989 American Control Conference written by and published by . This book was released on 1989 with total page 1036 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reconfigurable Intelligent Control System for Aircraft Flight Control written by Mingshe Zhou and published by . This book was released on 1998 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
