A Flight Control System Design with Handling Qualities Constraints Using Quantitative Feedback Theory
Author: R. A. Hess
Publisher:
Published: 1994
Total Pages:
ISBN-13:
DOWNLOAD EBOOKRead and Download eBook Full
Author: R. A. Hess
Publisher:
Published: 1994
Total Pages:
ISBN-13:
DOWNLOAD EBOOKAuthor: Constantine H. Houpis
Publisher:
Published: 1987
Total Pages: 220
ISBN-13:
DOWNLOAD EBOOKAuthor: Roger Pratt
Publisher: IET
Published: 2000
Total Pages: 416
ISBN-13: 9780852967669
DOWNLOAD EBOOKAnnotation Bridging the gap between academic research and real-world applications, this reference on modern flight control methods for fixed-wing aircraft deals with fundamentals of flight control systems design, then concentrates on applications based on the modern control methods used in the latest aircraft. The book is written for practicing engineers who are new to the aviation industry, postgraduate students in strategic or applied research, and advanced undergraduates. Some knowledge of classical control is assumed. Pratt is a member of IEEE and is UK Member for AIAA's Technical Committee on Guidance, Navigation and Control. Annotation c. Book News, Inc., Portland, OR (booknews.com)
Author: Phillip B. Arnold (MAJ, USAF.)
Publisher:
Published: 1984
Total Pages:
ISBN-13:
DOWNLOAD EBOOKAuthor: M B Tischler
Publisher: CRC Press
Published: 1996-06-28
Total Pages: 450
ISBN-13: 9780748404797
DOWNLOAD EBOOKThis book provides a single comprehensive resource that reviews many of the current aircraft flight control programmes from the perspective of experienced practitioners directly involved in the projects. Each chapter discusses a specific aircraft flight programme covering the control system design considerations, control law architecture, simulation and analysis, flight test optimization and handling qualities evaluations. The programmes described have widely exploited modern interdisciplinary tools and techniques and the discussions include extensive flight test results. Many important `lessons learned' are included from the experience gained when design methods and requirements were tested and optimized in actual flight demonstration.
Author:
Publisher:
Published: 1985
Total Pages: 94
ISBN-13:
DOWNLOAD EBOOKA study was conducted to design an experimental flight test program for the Total In-Flight Simulator CTIFS) directed toward the interface between flying qualities requirements and flight control system design criteria. The eventual goal is to provide an interpretation or translation of flying qualities requirements for use by the flight control system designer. Specifically, an angle of attack and pitch rate command system matrix involving both short term and long term dynamics are specified for evaluation. A major objective of the research was to demonstrate that flying qualities criteria and flight control system configuration or architecture can be independent. Finally, additional configurations are proposed to evaluate the efficacy of dynamic decoupling.
Author: Christopher Simon Beaverstock
Publisher:
Published: 2012
Total Pages:
ISBN-13:
DOWNLOAD EBOOKA closely integrated Flight Control System (FCS) design is fundamental to the successful develop- ment of modern aircraft. The FCS must provide adequate control authority to the pilot operator, along with a robust systems design that provides sufficient reliability and performance to ensure ad- equate handling qualities throughout the operational flight envelope. Using feedback controllers, the static and dynamic characteristics can be augmented, ultimately to improve the performance. In- cluding feedback control into the conceptual design process can in many cases improve not only the static and dynamic performance, but the operational efficiency. Essentially, the stability requirements are relaxed, where the additional parameters supplied by the controller are used to recover the lost performance. Furthermore, this is bounded by the performance of the command-actuation system. Parameters such as rate and maximum actuation output limit the systems designs performance, as well as the system dynamics which modifies the response. This thesis considers the task of integrating classical control and systems design under a single design framework. It is shown that by expanding the design space parameters, the overall aircraft perfor- mance and efficiency can be improved. The intended application of these methods is for integration into the conceptual design phase, where commitment of resources is normally at its greatest. Prin- ciples of this thesis are embodied in the FCS design environment Flight Control Systems Designer Toolkit (FCSDT), a sub-component of the Computerised Environment for Aircraft Synthesis and In- tegrated Optirnisation Methods (CEASIOM) software framework developed by Simulation of aircraft Stability And Control (SimSAC), an European Union (EU) funded Framework 6 Program, of which the author was a part of the development team. It is hypothesised that the FCS topology, systems architecture and control design are intrinsically linked, and that modifying these concurrently can lead to an improved design. This is demon- strated using data for a Boeing 747-100 published by National Aeronautics and Space Adminis- tration (NASA), selected due to the wealth of data and information available. Furthermore, with multiply-redundant surfaces and varying response and control power characteristics, provides a non- trivial example for FCS design. The NASA model was used to investigate static and dynamic per- formance across the operational ftight envelope. FCSDT was then used to explore the interaction between the topology and systems design whilst integrating feedback control. Results show the pos- sible performance benefits of. and the system limitations on. the control system design.
Author: P. B. Arnold
Publisher:
Published: 1984
Total Pages: 253
ISBN-13:
DOWNLOAD EBOOKQuantitative 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.
Author: Wichai Siwakosit
Publisher:
Published: 2001
Total Pages: 228
ISBN-13:
DOWNLOAD EBOOKAuthor: R. A. Hess
Publisher:
Published: 1992
Total Pages:
ISBN-13:
DOWNLOAD EBOOK