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Author: J. E. Rinde Publisher: ISBN: Category : Languages : en Pages : 188
Book Description
The objective of this study and investigation was to develop dual fault corrective capability for increased reliability by applying redundancy at the element level in flight control actuation components. Studies were performed to determine the functional and operational requirements for a flight control actuator capable of operating after two failures. A survey of presently used actuator mechanizations and failure correction techniques was made to categorize them along functional lines and to establish six possible dual fault correcting actuator (DFCA) configurations. An operational and failure analysis of the six DFCA configurations was made to determine their fault corrective capability relative size, cost and potential reliability. From this analysis, the Triplex Actuator with Electronic Model and Logic and the Quadruplex Actuator with Hydraulic Logic were selected for detail design development. These designs have one active actuator which controls the output and two operating standby actuators that can be locked-in to drive the output, with undegraded performance, when a failure occurs. Detail mechanical, hydraulic and electrical design was performed to obtain the two tentative actuator designs. A detail analysis and computer simulation of the system equations was performed to determine transients due to failures. An overall relative comparison of a single system, single fault and the two DFCA designs, indicates that the Triplex Actuator achieves dual fault corrective capability with a minimum increase in weight, size, power and complexity.
Author: J. E. Rinde Publisher: ISBN: Category : Languages : en Pages : 188
Book Description
The objective of this study and investigation was to develop dual fault corrective capability for increased reliability by applying redundancy at the element level in flight control actuation components. Studies were performed to determine the functional and operational requirements for a flight control actuator capable of operating after two failures. A survey of presently used actuator mechanizations and failure correction techniques was made to categorize them along functional lines and to establish six possible dual fault correcting actuator (DFCA) configurations. An operational and failure analysis of the six DFCA configurations was made to determine their fault corrective capability relative size, cost and potential reliability. From this analysis, the Triplex Actuator with Electronic Model and Logic and the Quadruplex Actuator with Hydraulic Logic were selected for detail design development. These designs have one active actuator which controls the output and two operating standby actuators that can be locked-in to drive the output, with undegraded performance, when a failure occurs. Detail mechanical, hydraulic and electrical design was performed to obtain the two tentative actuator designs. A detail analysis and computer simulation of the system equations was performed to determine transients due to failures. An overall relative comparison of a single system, single fault and the two DFCA designs, indicates that the Triplex Actuator achieves dual fault corrective capability with a minimum increase in weight, size, power and complexity.
Author: C. Hajiyev Publisher: Springer Science & Business Media ISBN: 1441991662 Category : Technology & Engineering Languages : en Pages : 361
Book Description
The problem of fault diagnosis and reconfigurable control is a new and actually developing field of science and engineering. The subject becomes more interesting since there is an increasing demand for the navigation and control systems of aerospace vehicles, automated actuators etc. to be more safe and reliable. Nowadays, the problems of fault detection and isolation and reconfigurable control attract the attention the scientists in the world. The subject is emphasized in the recent international congresses such as IF AC World Congresses (San Francisco-1996, Beijing-1999, and Barcelona-2002) and lMEKO World Congresses (Tampere-1997, Osaka-1999, Vienna-2000), and also in the international conferences on fault diagnosis such as SAFEPROCESS Conferences (Hull-1997, Budapest-2000). The presented methods in the book are based on linear and nonlinear dynamic mathematical models of the systems. Technical objects and systems stated by these models are very large, and include various control systems, actuators, sensors, computer systems, communication systems, and mechanical, hydraulic, pneumatic, electrical and electronic devices. The analytical fault diagnosis techniques of these objects have been developed for several decades. Many of those techniques are based on the use of the results of modem control theory. This is natural, because it is known that fault diagnosis process in control systems is considered as a part of general control process. xxii In organization of fault diagnosis of control systems, the use of the concepts and methods of modem control theory including concepts of state space, modeling, controllability, observability, estimation, identification, and filtering is very efficient.
Author: D. Hogan Publisher: ISBN: Category : Languages : en Pages : 167
Book Description
The objective of this program was to develop means to improve the reliability of flight control nonelectronic components with a minimum weight penalty. A survey of the published field failure data was accomplished and the flight control servo actuator was selected as the component for detailed study. A number of approaches to the mechanical were evaluated and the principle of Hammock netting was selected as the best means of providing redundancy at the element level in this class of actuators. A breadboard model incorporating four specially designed single stage servo valves and a non-redundant ram was designed and evaluated under normal conditions and with simulated faults. With the ram at rest, a hardover fault in one valve causes a transient ram excursion of about 2 percent of full travel. A valve failure to null reduces the actuator bandwidth to about 50 percent of the degraded bandwidth. The design will tolerate one fault in any valve and 40 percent of the combinations of two faulted valves. (Author).
Author: Jessica Davies Publisher: ISBN: Category : Languages : en Pages :
Book Description
The High Redundancy Actuator (HRA) project investigates a novel approach to fault tolerant actuation, which uses a high number of small actuation elements, assembled in series and parallel in order to form a single intrinsically fault tolerant actuator. Element faults affect the maximum capability of the overall actuator, but through control techniques, the required performance can be maintained. This allows higher levels of reliability to be attained in exchange for less over-dimensioning in comparison to conventional redundancy techniques. In addition, the combination of both serial and parallel elements provides intrinsic accommodation of both lock-up and loose faults. Research to date has concentrated on HRAs based on electromechanical technology, of relatively low order, controlled through passive Fault Tolerant Control (FTC) methods. The objective of this thesis is to expand upon this work. HRA configurations of higher order, formed from electromagnetic actuators are considered. An element model for a moving coil actuator is derived from first principles and verified experimentally. This element model is then used to form high-order, non-linear HRA models for simulation, and reduced-order representations for control design. A simple, passive FTC law is designed for the HRA configurations, the results of which are compared to a decentralised, active FTC approach applied through a framework based upon multi-agent concepts. The results indicate that limited fault tolerance can be achieved through simple passive control, however, performance degradation occurs, and requirements are not met under theoretically tolerable fault levels. Active FTC offers substantial performance improvements, meeting the requirements of the system under the vast majority of theoretically tolerable fault scenarios. However, these improvements are made at the cost of increased system complexity and a reliance on fault detection. Fault Detection (FD) and health monitoring of the HRA is explored. A simple rule-based FD method, for use within the active FTC, is described and simulated. An interacting multiple model FD method is also examined, which is more suitable for health monitoring in a centralised control scheme. Both of these methods provide the required level of fault information for their respective purposes. However, they achieve this through the introduction of complexity. The rule-based method increases system complexity, requiring high levels of instrumentation, and conversely the interacting multiple model approach involves complexity of design and computation. Finally, the development of a software demonstrator is described. Experimental rigs at the current project phase are restricted to relatively low numbers of elements for practical reasons such as cost, space and technological limitations. Hence, a software demonstrator has been developed in Matlab/Simulink which provides a visual representation of HRAs with larger numbers of elements, and varied configuration for further demonstration of this concept.
Author: Lunlong Zhong Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
The objective of this thesis is to optimize the use of redundant actuators for a transportation aircraft once some actuators failure occurs during the flight. Here, the fault tolerant ability resulting from the redundant actuators is mainly considered. Different classical concepts and methods related to a fault tolerant flight control channel are first reviewed and new concepts useful for the required analysis are introduced. The problem which is tackled here is to develop a design methodology for fault tolerant flight control in the case of a partial actuator failure which will allow the aircraft to continue safely the intended maneuver. A two stages control approach is proposed and applied to both the remaining maneuverability evaluation and a fault tolerant control structure design. In the first case, an offline handling qualities assessment method based on Model Predictive Control is proposed. In the second case, a fault tolerant control structure based on Nonlinear Inverse Control and online actuator reassignment is developed. In both cases, a Linear Quadratic (LQ) programming problem is formulated and different failure cases are considered when an aircraft performs a classical maneuver. Three numerical solvers are studied and applied to the offline and online solutions of the resulting LQ problems.
Author: J. E. Rinde
Author: J. E. Rinde
Author: Defense Documentation Center (U.S.)
Author: 
Author: C. Hajiyev
Author: 
Author: 
Author: D. Hogan
Author: Jessica Davies
Author: 
Author: Lunlong Zhong