Thermal Management Of Electromechanical Actuation System For Aircraft Primary Flight Control Surfaces
DOWNLOAD
Download Thermal Management Of Electromechanical Actuation System For Aircraft Primary Flight Control Surfaces PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Thermal Management Of Electromechanical Actuation System For Aircraft Primary Flight Control Surfaces book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
Thermal Management Of Electromechanical Actuation System For Aircraft Primary Flight Control Surfaces
DOWNLOAD
Author : Zachary A. Lammers
language : en
Publisher:
Release Date : 2014
Thermal Management Of Electromechanical Actuation System For Aircraft Primary Flight Control Surfaces written by Zachary A. Lammers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2014 with Actuators categories.
Electromechanical Actuation Systems (EMAS) are a key component in the More Electric Aircraft (MEA). EMAS operate on a "power on demand" basis reducing energy consumption typically required by hydraulic systems to maintain hydraulic pressure. Additionally, EMAS reduce system weight; lessening system maintenance and operating costs. EMAS convert electrical energy to mechanical energy via an electric rotary machine combined with a rotary to linear or rotary to rotary conversion mechanism. Electrical energy required to complete useful mechanical output depends on the efficiency of the system. Therefore, it is important to characterize electrical and thermal loads associated with an EMAS for primary flight control surfaces, such as an aileron. Electric power draw and thermal management are among the most important parameters of research in electromehcanical actuation for a primary flight control (PFC) surface. The aim of this thesis was to build an experimental EMAS system and methodology to analyze EMAS performance against realistic duty cycles and mission environments. Thermal energy in addition to the rate of change of temperature and temperature difference for temperature sensitive components was used to determine the most thermally malignant profiles and potential thermal design points. It was found that transient missions of an EMAS presented the greatest electric demand of the aircraft electric power supply system, and holding presented the greatest thermal stress of the EMAS, where the EMAS operated at 0% efficiency and all electric power was converted to heat.
Laboratory Test Set Up To Evaluate Electromechanical Actuation System For Aircraft Flight Control
DOWNLOAD
Author : Street A. Barnett
language : en
Publisher:
Release Date : 2015
Laboratory Test Set Up To Evaluate Electromechanical Actuation System For Aircraft Flight Control written by Street A. Barnett and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015 with Actuators categories.
A laboratory apparatus and data acquisition system were constructed for evaluating aircraft flight control actuators under simulated mission profiles. A MTS hydraulic load frame was used to simulate a control surface's aero load. A NI based DAQ system was used to record the motor controller's DC bus voltage at a high rate, actuator's position, load, and temperatures. The DC bus rms voltage, current, and power, and regenerative power were recorded by a Newton's 4th power analyzer. Key performance characteristics tests such as frequency response, step response, reversal, backlash, and holding with a Danahar EC5 actuator were carried out to verify this laboratory setup.The continuous frequency sweeping test revealed that the EMA reached the speed limit first, then the current limit, and finally the temperature limit. When the actuator's electronics reached the thermal limit, the actuator controller drastically reduced its power. This caused drastic magnitude attenuation and phase lagging. Continuous frequency sweeping proved to be a useful test to evaluate the EMA's characteristics. The lab tests showed that holding presents the most significant challenge to the thermal management of an EMA system. To reduce the thermal gradient within the motor, a half rotation back forth at 0.01 Hz sinusoidal disturbance was imposed during holding to evenly engage the motor's three phases. This resulted in an 81% temperature variation reduction among the three windings. Although this small motion disturbance is effective in reducing the motor and motor drive's thermal gradient, it is not known if such a disturbance is feasible in practice.The step response and reversal test showed that when an EMA reverses direction or suddenly decelerates, a significant spike of regenerative power occurred. This regenerative power could present itself as a thermal challenge to an aircraft flight control EMA system.Using the MTS hydraulic load frame to simulate a dynamic aero load of a flight control surface in synchronization with position movement of an actuator proved to be a challenge. A double loop control scheme has been derived which compensates the time delay difference between the load frame and the actuator. It is our hope that this control strategy, once fully implemented, will enable more accurate dynamic load control in simulating an EMA's mission profile for performance evaluation.
Performance Improvement Of Embedded Electric Actuators By Means Of A Thermal Management Optimisation
DOWNLOAD
Author : Francesco De Giorgi
language : en
Publisher:
Release Date : 2021
Performance Improvement Of Embedded Electric Actuators By Means Of A Thermal Management Optimisation written by Francesco De Giorgi and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2021 with categories.
Thermal management issue is one of the remaining barriers to the use of electrical actuators for primary flight control applications, as their performance and especially their reliability is highly dependent on the operating temperature. Until now, hydraulic technologies have allowed excess heat to be evacuated through the hydraulic network. The problem was relocated and heat exchangers were used to cool the hydraulic fluid. The increasing electrification of aircraft pushes toward the suppression of the hydraulic network and, as a result, the hydraulic fluid will not be available as a convenient means of transporting and dissipating the heat generated by the actuators. New thermal management solutions for dealing with the component heat load at a local level are needed. Several studies have looked specifically to this purpose, which provided efficient potential solutions for the thermal management of electrical flight actuators. This thesis mainly focuses on a topic that has not yet been fully explored in the literature, which concerns the optimal design and coupling of such solutions with the actuator system. In fact, if these solutions are optimally integrated during the preliminary design phase of the actuator, they can provide not only an improvement in the performance of the actuation system, but also the development of a lighter and more compact system, leading to considerable advantages at aircraft level. The objective of this thesis is to provide effective methods and tools suited for the preliminary design of electrical actuators, with a particular attention to the thermal management. The first part of the thesis concerns the identification of potential thermal management solutions. Thermal management systems such as plate fin heat exchanger, heat pipes, thermal straps and phase change materials are investigated. The second part of the thesis regards the implementation of a procedure to optimally preliminary design the coupled system composed by the actuator and its associated thermal management device. Firstly, estimation models are generated in order to estimate the dimensions and performance of cooling devices and actuator components. To this purpose, a new methodology for obtaining simpler and lighter surrogate models is proposed. Subsequently the preliminary design procedure is defined via a Multidisciplinary System Design Optimization with a view focused on the mass minimization and thermal constraints satisfaction. Two different approaches for sizing the actuation system are proposed. The first approach consists of performing the preliminary design on the basis of static specifications extrapolated from the mission profile. This approach allows a rapid estimation of the actuator dimensions and performance, but does not guarantee optimal thermal dynamics over the entire flight duration. The second approach, more expensive from a computational point of view, consists in integrating the mission profile in the preliminary design, thus allowing the realisation of a system which ensures an optimal thermal dynamic along the mission profile. Based on the case study of an Airbus A320 and referring to an electro-mechanical actuator, the proposed approaches are applied here to conduct the preliminary design for the whole set of primary flight control surfaces: Aileron, Rudder and Elevator. A quantitative comparison of the most suitable thermal management concepts is made for each of these applications.
Electromechanical Actuation Feasibility Study
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1976
Electromechanical Actuation Feasibility Study written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with categories.
An alternate to hydraulic actuation of primary flight control surfaces is desirable. Electromechanical actuation of primary flight controls is feasible and practical using the most recent advances in the state-of-the-art in magnetic materials for high-performance servomotors, high-current-capacity transistor switches for motor power control, and digital microprocessors for servo and redundancy management logic. Electromechanical actuation is consistent with current, proven, fly-by-wire technology and with the developing power-by- wire techniques. The control surface performance requirements and methods of analysis are presented for direct drive electromechanical power servos. Trade studies were conducted to evaluate the aircraft power source and distribution options; actuator motor and controller options; and geared rotary hinge actuator configuration options. A weight comparison is given between the hydraulic actuation system for the F-100 and the electromechanical system studied. Reliability assessments and redundancy management considerations also are included. A preliminary design of the electromechanical actuation system and test plan are presented. These data were developed using a selected baseline problem statement which was derived from existing hydraulic actuator specifications.
A System Look At Electromechanical Actuation For Primary Flight Control
DOWNLOAD
Author : E. A. Lomonova
language : en
Publisher:
Release Date : 1995
A System Look At Electromechanical Actuation For Primary Flight Control written by E. A. Lomonova and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1995 with categories.
Prognostics And Health Management Guidelines For Electro Mechanical Actuators
DOWNLOAD
Author : HM-1 Integrated Vehicle Health Management Committee
language : en
Publisher:
Release Date : 2020
Prognostics And Health Management Guidelines For Electro Mechanical Actuators written by HM-1 Integrated Vehicle Health Management Committee and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2020 with categories.
Reducing the power consumptionand hence, the fuel burnis a major target for the next generation of aircraft, and electrical actuation is perceived as a technological area able to provide power saving. Electrical actuation can in fact contribute to the reduction of the non-propulsive power because electro-mechanical actuators, when compared to the conventional hydraulic actuators, rely on a form of power subjected to lower distribution losses and in general can lead to a weight savings at the aircraft level if the required power remains under a break-over point. Moreover, electro-mechanical actuators (EMAs) present higher reliability and maintainability with a lower life-cycle cost.Two critical issues with electrically powered actuation are the temperature rise in the electric motor windings and in the power electronics, and the sensitivity to certain single point of failures that can lead to mechanical seizures, that has so far thwarted the use of EMAs for safety-critical applications. In order to address the issue of a possible actuator seizure, many research and development activities have been performed to identify ways of making an electro-mechanical actuator jam-free or jam-tolerant, since this would allow more flexibility in defining the overall architecture of the flight control system. Although interesting and ingenious design solutions have been proposed, they all have so far resulted in complex mechanical designs that on one hand allow the actuator to operate after a jam of an internal component, but on the other hand bring about increased weight, volume, and cost, and a reliability reduction due to the much larger number of parts.With primary flight control actuators being some of the more safety-critical components of an aircraft, an undetected actuator failure can lead to serious consequences. Furthermore, failures that are not flight safety critical can still have negative consequences ranging from flight disruptions to unscheduled and costly maintenance.The development of an effective and reliable PHM system for EMAs is thus seen as a possible way to contribute to the acceptance of EMAs as primary flight control actuators in commercial aircraft, for an effective PHM system will feature appropriate diagnostic functions to detect anomalous behavior, and prognostic capabilities indicating when an incipient fault develops and estimating how, under continuing usage, the fault will eventually become a failure. Providing EMAs with a PHM capability will entail positive results in different areas: Progressively improve the EMA robustness; PHM algorithms can initially provide indication of the onset of a fault, while more sophisticated reasoning functions can then assess the remaining useful life and contribute to the safety of flight. Minimize the unscheduled maintenance events, thereby increasing the EMA availability. Facilitate maintenance operations and troubleshooting. Simplify the supply chain.It is important to note that a more extensive use of EMAs facilitated by PHM algorithms must be associated to all design provisions necessary to attain mandatory safety requirements. Electro-mechanical actuators (EMAs) are used in different aerospace applications performing functions with different degrees of criticality, and a trend exists to progressively replace hydraulic actuators with EMAs for most flight-critical applications. This carries along a growing interest in providing EMAs with a prognostics and health management (PHM) system allowing effective diagnostics, prognostics, and recovery actions. Early fault detection is needed in flight-critical applications to allow enough time for contingency management in order to avoid the occurrence of safety-critical situations.The development of an EMA PHM system is a challenging task since EMAs are complex systems made up by electronic, electrical, and mechanical subsystems, and are typically under-instrumented. This implies that a fault in an EMA component may have effects on other parts of the actuator, which makes it difficult to successfully identify and isolate the fault, especially when only a limited number of signals is available.The purpose of this document is to provide the guidelines of the technological approach for developing a PHM system for EMAs with particular reference to their possible use as primary flight control actuators. It provides a basic description of the physics of the most common degradation processes, a reliability assessment, and a discussion on the signals, with the associated data processing, required to build up an effective health monitoring system.
Aircraft Thermal Management
DOWNLOAD
Author : Mark Ahlers
language : en
Publisher: SAE International
Release Date : 2016-05-02
Aircraft Thermal Management written by Mark Ahlers and has been published by SAE International this book supported file pdf, txt, epub, kindle and other format this book has been release on 2016-05-02 with Technology & Engineering categories.
Aircraft thermal management (ATM) is increasingly important to the design and operation of commercial and military aircraft due to rising heat loads from expanded electronic functionality, electric systems architectures, and the greater temperature sensitivity of composite materials compared to metallic structures. It also impacts engine fuel consumption associated with removing waste heat from an aircraft. More recently the advent of more electric architectures on aircraft, such as the Boeing 787, has led to increased interest in the development of more efficient ATM architectures by the commercial airplane manufacturers. The ten papers contained in this book describe aircraft thermal management system architectures designed to minimize airplane performance impacts which could be applied to commercial or military aircraft. Additional information on Aircraft Thermal Management System Architectures is available from SAE AIR 5744 issued by the AC-9 Aircraft Environmental System Committee and the SAE book Aircraft Thermal Management Integrated Analysis (PT-178). SAE AIR 5744 defines the discipline of aircraft thermal management system engineering while Aircraft Thermal Management Integrated Analysis discusses approaches to computer simulation of the simultaneous operation of all systems affecting thermal management on an aircraft.
An Introduction To Aircraft Thermal Management
DOWNLOAD
Author : Mark Ahlers
language : en
Publisher: SAE International
Release Date : 2019-04-14
An Introduction To Aircraft Thermal Management written by Mark Ahlers and has been published by SAE International this book supported file pdf, txt, epub, kindle and other format this book has been release on 2019-04-14 with Technology & Engineering categories.
Aircraft Thermal Management (ATM)focuses on how to manage heat in an aircraft to meet the temperature requirements for passengers and vehicle. This primarily involves removing heat and protecting equipment, systems, and structure from heat sources that could raise their temperature beyond design limits. Crew and passengers must be neither too hot nor too cold during airplane operations. Thus, maintaining thermal comport is critically important, and not a trivial operation. Written by Mark F. Ahlers, a retired Boeing Technical Fellow and its first Thermal Marshal, An Introduction to Aircraft Thermal Management is the ultimate source of knowledge concerning: Temperature and thermal related requirements Airplane-generated heat sources External heat sources Aircraft heat sinks Fire and Failures Environmental control systems Thermal design Analytical modeling Analytical software Testing Military aircraft thermal management Fully illustrated and amply referenced, An Introduction to Aircraft Thermal Management provides a very balanced approach between theory and practice, best practices and technical insights. It is a must-have reference for both young engineers starting in the filed and for seasoned professionals willing to re-sharpen their skills.
Aircraft Control Allocation
DOWNLOAD
Author : Wayne Durham
language : en
Publisher: John Wiley & Sons
Release Date : 2017-01-17
Aircraft Control Allocation written by Wayne Durham and has been published by John Wiley & Sons this book supported file pdf, txt, epub, kindle and other format this book has been release on 2017-01-17 with Technology & Engineering categories.
Aircraft Control Allocation Wayne Durham, Virginia Polytechnic Institute and State University, USA Kenneth A. Bordignon, Embry-Riddle Aeronautical University, USA Roger Beck, Dynamic Concepts, Inc., USA An authoritative work on aircraft control allocation by its pioneers Aircraft Control Allocation addresses the problem of allocating supposed redundant flight controls. It provides introductory material on flight dynamics and control to provide the context, and then describes in detail the geometry of the problem. The book includes a large section on solution methods, including 'Banks' method', a previously unpublished procedure. Generalized inverses are also discussed at length. There is an introductory section on linear programming solutions, as well as an extensive and comprehensive appendix dedicated to linear programming formulations and solutions. Discrete-time, or frame-wise allocation, is presented, including rate-limiting, nonlinear data, and preferred solutions. Key features: Written by pioneers in the field of control allocation. Comprehensive explanation and discussion of the major control allocation solution methods. Extensive treatment of linear programming solutions to control allocation. A companion web site contains the code of a MATLAB/Simulink flight simulation with modules that incorporate all of the major solution methods. Includes examples based on actual aircraft. The book is a vital reference for researchers and practitioners working in aircraft control, as well as graduate students in aerospace engineering.
A Study Of Digitally Controlled Flight Control Actuation
DOWNLOAD
Author : Howard H. Belmont
language : en
Publisher:
Release Date : 1983
A Study Of Digitally Controlled Flight Control Actuation written by Howard H. Belmont and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with Actuators categories.
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.