Study of Application of Electromechanical Actuators to Deploy Control Surfaces According to More Electrical Aircraft Concept
Study of Application of Electromechanical Actuators to Deploy Control Surfaces According to More Electrical Aircraft Concept

Author: Guillem Batlle i Capa

Publisher:

Published: 2020

Total Pages:

ISBN-13:

DOWNLOAD EBOOK

Transportation represents a 20% of green-house effect gases emissions worldwide. There is a trend to move towards greener powered systems, such as electric ones. More Electric Aircraft (MEA) is a new concept into the aircraft industry which is trying to increase the usage of electrically powered systems in aeroplanes. This project reviews the available technologies for MEA in special regard to flight control surfaces actuators. Conventional hydraulic actuators in aircraft systems are low efficient and require high maintenance tasks and a heavy infrastructure. Powered-by-wire systems are being broadly applied into aeroplanes to improve the maintainability, reliability and also manoeuvrability of the next generation of aeroplanes. Throughout the project different fields involved in the effective development of new electromechanical actuators are inspected. First, the generation and power conversion of electric power into a plane. Second, the technologies concerning the building block of an electromechanical actuator in three main aspects: electric layout, mechanical layout and potential failures. Third, the monitoring devices and redundant architecture that would satisfy the continued airworthiness regulations. Finally, a mock-up for simulating and demonstrating purposes is designed and the most proper pattern nowadays for an electromechanical actuator for flight control surfaces is presented together with further work of MEA for the successful implementation of electromechanical actuators into the next generation of aircraft.

Electro-Mechanical Actuators for the More Electric Aircraft
Electro-Mechanical Actuators for the More Electric Aircraft

Author: Mirko Mazzoleni

Publisher: Springer Nature

Published: 2021-01-19

Total Pages: 256

ISBN-13: 3030617998

DOWNLOAD EBOOK

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.

Electro-Mechanical Actuators for the More Electric Aircraft
Electro-Mechanical Actuators for the More Electric Aircraft

Author: Mirko Mazzoleni

Publisher:

Published: 2021

Total Pages: 0

ISBN-13: 9783030618001

DOWNLOAD EBOOK

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.

Electro-Mechanical Actuators for Safety-Critical Aerospace Applications
Electro-Mechanical Actuators for Safety-Critical Aerospace Applications

Author: Gianpietro Di Rito

Publisher: Mdpi AG

Published: 2023-06-12

Total Pages: 0

ISBN-13: 9783036579337

DOWNLOAD EBOOK

Aircraft electrification is one of the most important and strategic initiatives currently supporting the innovation of the aviation industry. This manifests in the well-known more-electric aircraft concept (with the ultimate aim of achieving the all-electric long-term target), which aims to gradually replace onboard systems based on mechanical, hydraulic, or pneumatic power sources with electrically powered ones to reduce the weight and costs, optimize energy, and increase the eco-compatibility and reliability of future aircrafts. A key technological enabler for pursuing these challenging objectives is electro-mechanical actuation. The applicability of electro-mechanical actuators (EMAs) in aerospace has been proved in terms of dynamic performances, but it still entails several concerns in terms of reliability/safety and operation in a harsh environment. In civil aircrafts, EMAs are often avoided for safety-critical functions (flight controls, brakes, landing gears, and nose wheel steering), essentially because the statistical database on the components' fault modes is poor. This Special Issue is thus focused on advancements and innovations in the design, modelling/simulation, architectural definition, reliability/safety analysis, control, condition-monitoring, and experimental testing of EMAs developed for safety-critical aerospace applications. The research papers included in this Special Issue will undoubtedly contribute to progress towards the objective of more electric flights.

Thermal Management of Electromechanical Actuation System for Aircraft Primary Flight Control Surfaces
Thermal Management of Electromechanical Actuation System for Aircraft Primary Flight Control Surfaces

Author: Zachary A. Lammers

Publisher:

Published: 2014

Total Pages: 271

ISBN-13:

DOWNLOAD EBOOK

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.

Aerospace Actuators 3
Aerospace Actuators 3

Author: Jean-Charles Maré

Publisher: John Wiley & Sons

Published: 2018-01-19

Total Pages: 228

ISBN-13: 111950550X

DOWNLOAD EBOOK

This book is the third in a series dedicated to aerospace actuators. It uses the contributions of the first two volumes to conduct case studies on actuation for flight controls, landing gear and engines. The actuation systems are seen in several aspects: signal and power architectures, generation and distribution of hydraulic or mechanical power, control and reliability, and evolution towards more electrical systems. The first three chapters are dedicated to the European commercial airplanes that marked their era: Caravelle, Concorde, Airbus A320 and Airbus A380. The final chapter deals with the flight controls of the Boeing V-22 and AgustaWestland AW609 tiltrotor aircraft. These address concerns that also apply to electromechanical actuators, which should be fitted on more electrical aircraft in the future. The topics covered in this series of books constitute a significant source of information for individuals and engineers from a variety of disciplines, seeking to learn more about aerospace actuation systems and components.

Electromechanical Actuation Feasibility Study
Electromechanical Actuation Feasibility Study

Author:

Publisher:

Published: 1976

Total Pages: 190

ISBN-13:

DOWNLOAD EBOOK

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.