Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 512
Book Description
Digital Flight Control Actuation System Study
Author: A Study of Digitally Controlled Flight Control Actuation
Author: Howard H. BelmontPublisher:
ISBN:
Category : Actuators
Languages : en
Pages : 164
Book Description
This report describes a study of flight control actuation system with an objective to determine the degree of digitalization possible between the digital flight control processor and the control surface. A typical analog actuation system is defined as a reference for comparison with five alternates, each mechanized with increasing amounts of digital equipment. The report provides a basis for determining the direction of digital actuation systems. It verifies that distributed actuation systems are now feasible and promise enhanced performance, reliability, and cost reductions.
Research and Development of Aircraft Control Actuation Systems
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.
Aircraft Flight Control Actuation System Design
Author: Eugene T. RaymondPublisher:
ISBN: 9781560913764
Category : Technology & Engineering
Languages : en
Pages : 270
Book Description
Advanced Flight Control Actuation Systems and Their Interface with Digital Commands
Author: Society of Automotive Engineers, IncPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Flight Control Systems
Author: Roger PrattPublisher: 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)
Preliminary System Design Study for a Digital Fly-by-wire Flight Control System for an F-8C Aircraft
Author: C. L. SeacordPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 228
Book Description
The design of a fly-by-wire control system having a mission failure probability of less than one millionth failures per flight hour is examined. Emphasis was placed on developing actuator configurations that would improve the system performance, and consideration of the practical aspects of sensor/computer and computer/actuator interface implementation. Five basic configurations were defined as appropriate candidates for the F-8C research aircraft. Options on the basic configurations were included to cover variations in flight sensors, redundancy levels, data transmission techniques, processor input/output methods, and servo actuator arrangements. The study results can be applied to fly by wire systems for transport aircraft in general and the space shuttle.
Digital Flight Control Research
Author: J. E. PotterPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 220
Book Description
The results of studies which were undertaken to contribute to the design of digital flight control systems, particularly for transport aircraft are presented. In addition to the overall design considerations for a digital flight control system, the following topics are discussed in detail: (1) aircraft attitude reference system design, (2) the digital computer configuration, (3) the design of a typical digital autopilot for transport aircraft, and (4) a hybrid flight simulator.
Analysis of a Digital Flight Control System
Author: Robert Charles RoseA Feasibility Study of Self-learning Adaptive Flight Control for High Performance Aircraft
Author: Stephen G. HoppePublisher:
ISBN:
Category : Automatic pilot (Airplanes)
Languages : en
Pages : 258
Book Description
A study of the feasibility of a self-learning adaptive system for the flight control of high performance aircraft has been performed. A flight control system was developed for the investigation of the stability augmentation of the longitudinal axis of the F101B aircraft using self-learning adaptive control. The learning adaptive controller developed employs a three-loop concept. The innermost loop comprises a linear feedback control system in which a set of control gains is adjusted by a second (adaptive) loop employing a parameter identifier and a trainable function generator (automation). The automation provides the correct values of feedback gain in response to patterns derived from the identified aircraft parameters. The third loop (the learning loop) measures control system performance, and continually retrains the automation to improve the performance. Experiments were performed with a digital simulation of the aircraft and the learning adaptive control system. Results of the experiments indicate that learning adaptive control is feasible. However, a number of significant technical problems must be overcome prior to the use of such a control system in tactical aircraft. Studies of sensitivity must be performed to assess the effect of small perturbations in the identification parameters on system performance. Extended studies of property extraction from the identified parameters is required, and means for further simplifying the control structure is of importance in a real system. (Author).