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Author: Publisher: ISBN: Category : Languages : en Pages : 178
Book Description
This report describes the design and test of a multipurpose actuation test rig to be used for loaded evaluation of actuation systems with rotary outputs and/or integrated as part of wing structure. It also describes a hydromechanical flutter damping module for an F-4 stabilator actuator. The module incorporates design improvements based on previous test results. Laboratory tests results on the improved module are presented. Development and test results of a linear force motor based upon a moving magnet concept, and the measured performance characteristics of the concept over a range of parameter variations are presented. A method of force enhancement for direct drive force motors and the corresponding test results applied to a moving coil force motor are described. The concept is based upon applying a limited time duration pulse to the force motor in order to increase the force output when required. The logic technique used to initiate the pulse application is presented. Applying a digital computer as a controller for an analog electrohydraulic control system requires consideration of the interface used. The effect of a pulse width modulation interface on the life of analog electrohydraulic hardware is presented. There is a potential for reducing the pumping capacity of an aircraft's flight control hydraulic system by using accumulators to store hydraulic energy. The results of a study using this approach and an F-16 simulation are presented. Keywords: Digital interface; Energy storage; Flight control hydraulics; Force enhancement, Flutter suppression.
Author: Publisher: ISBN: Category : Languages : en Pages : 178
Book Description
This report describes the design and test of a multipurpose actuation test rig to be used for loaded evaluation of actuation systems with rotary outputs and/or integrated as part of wing structure. It also describes a hydromechanical flutter damping module for an F-4 stabilator actuator. The module incorporates design improvements based on previous test results. Laboratory tests results on the improved module are presented. Development and test results of a linear force motor based upon a moving magnet concept, and the measured performance characteristics of the concept over a range of parameter variations are presented. A method of force enhancement for direct drive force motors and the corresponding test results applied to a moving coil force motor are described. The concept is based upon applying a limited time duration pulse to the force motor in order to increase the force output when required. The logic technique used to initiate the pulse application is presented. Applying a digital computer as a controller for an analog electrohydraulic control system requires consideration of the interface used. The effect of a pulse width modulation interface on the life of analog electrohydraulic hardware is presented. There is a potential for reducing the pumping capacity of an aircraft's flight control hydraulic system by using accumulators to store hydraulic energy. The results of a study using this approach and an F-16 simulation are presented. Keywords: Digital interface; Energy storage; Flight control hydraulics; Force enhancement, Flutter suppression.
Author: Gavin D. Jenney Publisher: ISBN: Category : Languages : en Pages : 202
Book Description
This report presents the results of the following three research and development activities: the design, fabrication and test of a multi-channel flight control system hybrid simulator; the analysis and application of a flutter damping technique for hydraulically actuated slab type control surfaces; and the experimental testing of Mil-H-83282 hydraulic fluid in a pumping system at elevated temperature.
Author: Gavin D. Jenney Publisher: ISBN: Category : Languages : en Pages : 216
Book Description
This report describes the design and test evaluation of a direct drive fly-by-wire redundant control system. Also included in the report is the evaluation testing of a fly-by-wire tandem actuator mechanization developed by Parker-Hannifin Aerospace Hydraulics Division, Irvine California. The direct drive system is based on using moving coil force motors to position a hydraulic control valve without hydraulic amplification. The system is designed as a single fail operate system which will accept one input or component failure and continue to operate with acceptable performance. The test results verified that the failure modes and performance met the design goals. The system incorporates component dispersion techniques to allow single hit survivability. The direct drive mechanization offers adequate performance with minimum complexity as a fly-by-wire control system. The Parker-Hannifin actuator mechanization is a two fail operate configuration using an integrated secondary actuator with both force and position summing. The test results document the operational characteristics of the design. (Author).
Author: Gavin D. Jenney Publisher: ISBN: Category : Languages : en Pages : 401
Book Description
This report describes the test evaluation of two Fly-By-Wire development demonstrators submitted to the Air Force for evaluation. The demonstrators were submitted to the Air Force under contract by Grumman Aerospace Corporation, Bethpage, New York. One demonstrator was a force sharing mechanization constructed for Grumman Aircraft by Bertea Corporation of Irvine, California. The other demonstrator was an active-on-line mechanization constructed for Grumman Aerospace Corporation by National Waterlift Corporation of Kalamazoo, Michigan. For the evaluation, the demonstrators were set up with specific performance characteristics which had been used for previous tests performed on other FBW mechanizations. Except where special testing was warranted to investigate potentially unique characteristics of a particular system, the same test procedures were used for both demonstration systems. The report describes the systems evaluated, the test procedures and presents the test results obtained. (Author).
Author: Gavin D. Jenney Publisher: ISBN: Category : Languages : en Pages : 211
Book Description
This report describes the development of a flutter suppression actuator technique and the wind tunnel evaluation of that technique. The report also describes the flightworthiness testing of a direct drive Fly-By-Wire flight control system applied to the aileron axis of an F-4 aircraft. Also included is an evaluation of an angular rate sensing augmentation actuator supplied to the Air Force for evaluation. Presented in the material are the test results of all three experimental evaluations. Further testing of the flutter suppression is recommended to clarify an anomoly in the results of the testing. The direct drive control system passed its environmental testing used to establish flight worthiness. The rate sensing actuator operated as designed.
Author: Roger Pratt Publisher: IET ISBN: 9780852967669 Category : Technology & Engineering Languages : en Pages : 416
Book Description
Annotation 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: Publisher: ISBN: Category : Languages : en Pages : 30
Book Description
A state-of-the-art computational facility for aircraft flight control design, evaluation, and integration called CONDUIT (Control Designer's Unified Interface) has been developed. This paper describes the CONDUIT tool and case study applications to complex rotary- and fixed- wing fly-by-wire flight control problems. Control system analysis and design optimization methods are presented, including definition of design specifications and system models within CONDUIT, and the multi-objective function optimization (CONSOL-OPTCAD) used to tune the selected design parameters. Design examples are based on flight test programs for which extensive data are available for validation. CONDUIT is used to analyze baseline control laws against pertinent military handling qualities and control system specifications. In both case studies, CONDUIT successfully exploits trade-offs between forward loop and feedback dynamics to significantly improve the expected handling qualities and minimize the required actuator authority. The CONDUIT system provides a new environment for integrated control system analysis and design, and has potential for significantly reducing the time and cost of control system flight test optimization.
Author: Mirko Mazzoleni Publisher: Springer Nature ISBN: 3030617998 Category : Technology & Engineering Languages : en Pages : 256
Book Description
This book presents recent results on fault diagnosis and condition monitoring of airborne electromechanical actuators, illustrating both algorithmic and hardware design solutions to enhance the reliability of onboard more electric aircraft. The book begins with an introduction to the current trends in the development of electrically powered actuation systems for aerospace applications. Practical examples are proposed to help present approaches to reliability, availability, maintainability and safety analysis of airborne equipment. The terminology and main strategies for fault diagnosis and condition monitoring are then reviewed. The core of the book focuses on the presentation of relevant case studies of fault diagnosis and monitoring design for airborne electromechanical actuators, using different techniques. The last part of the book is devoted to a summary of lessons learned and practical suggestions for the design of fault diagnosis solutions of complex airborne systems. The book is written with the idea of providing practical guidelines on the development of fault diagnosis and monitoring algorithms for airborne electromechanical actuators. It will be of interest to practitioners in aerospace, mechanical, electronic, reliability and systems engineering, as well as researchers and postgraduates interested in dynamical systems, automatic control and safety-critical systems. Advances in Industrial Control reports and encourages the transfer of technology in control engineering. The rapid development of control technology has an impact on all areas of the control discipline. The series offers an opportunity for researchers to present an extended exposition of new work in all aspects of industrial control.
Author: Vernon R Schmitt Publisher: SAE International ISBN: 0768064651 Category : Technology & Engineering Languages : en Pages : 134
Book Description
Fly-by-wire in aircraft flight control design is more than adding a simple wire -- it is a sophisticated system that changes the way aircraft are designed and the way they fly. Prepared and written by experts who directed or staffed fly-by-wire research and development programs, this book includes explanations of the system's design and application, providing both the "how" and the "why" of this remarkable technology. Chapters include: Introduction Background of Fly-by-Wire Required Programs The Survivable Flight Control System (SFCS) Program Technology Transition and Application
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Author: 
Author: Gavin D. Jenney
Author: Gavin D. Jenney
Author: Gavin D. Jenney
Author: Gavin D. Jenney
Author: Roger Pratt
Author: Eugene T. Raymond
Author: 
Author: Mirko Mazzoleni
Author: Vernon R Schmitt