Electric Control Surface Actuator Design Optimization and Allocation for the More Electric Aircraft

Chakraborty, Imon; Trawick, David; Jackson, David W.; Mavris, Dimitri N.

doi:10.2514/6.2013-4283

Cited by 26 publications

(12 citation statements)

References 17 publications

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“…Item 3, the constrained optimization of the actuator design, will form the focus of the second paper of this pair. 19 Finally, Item 4 is a study of the allocation of optimized actuator types (either EHA or EMA) to the aircraft control surfaces, which is significant since the primary and secondary flight control systems of a modern commercial aircraft consist of a large number of control surfaces, and it is quite possible that a MEA of the future may use both EHA and EMA design types for flight control actuation. Clearly then, the design of the flight control system of such an aircraft will involve not only the optimal design of the EHA and EMA units used, but also their optimal allocation to control surfaces.…”

Section: The Proposed Approachmentioning

confidence: 99%

Development of a Sizing and Analysis Tool for Electrohydrostatic and Electromechanical Actuators for the More Electric Aircraft

Chakraborty

Jackson

Trawick

et al. 2013

2013 Aviation Technology, Integration, and Operations Conference

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This work documents the development of a MATLAB/Simulink based methodology for the sizing, simulation, analysis, and optimization of electric actuators for the primary and secondary control surfaces of a More Electric Aircraft. For a given aircraft and control surface configuration, the control surface flight loads are first evaluated taking into account their aerodynamic characteristics and the critical flight conditions relevant to each. With this information, the performance of a given actuator design can be analyzed via a simulation of the actuator and thermal dynamics. Conversely, for a given objective function and constraint set, the actuator design can be optimized through the solution of a constrained optimization problem. This work focuses on the development of the flight load estimation capability, the modeling and simulation environment, and the weight estimation method, while a separate work describes the actuator optimization problem and a study of actuator-to-surface allocation. While applicable to a wide variety of aircraft, the current work analyzes electrohydrostatic and electromechanical actuators using the Boeing 737-800 aircraft as a test case.

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Section: The Proposed Approachmentioning

confidence: 99%

Development of a Sizing and Analysis Tool for Electrohydrostatic and Electromechanical Actuators for the More Electric Aircraft

Chakraborty

Jackson

Trawick

et al. 2013

2013 Aviation Technology, Integration, and Operations Conference

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“…Recently, with the progress made in electric motor control and technology, the development of more electric aircraft control (MEAC) strategies have emerged. The main goal of this approach is arguably to reduce the the weight, complexity, and redundancy to cope with failure rates dictated by hydraulic components [1]. Designers have had to rethink the aircraft internal systems layout, limiting hydraulic components where possible and optimising layout of the new systems.…”

Section: Project Motivationmentioning

confidence: 99%

“…Of course, off-the-bench actuator data can be used to generate sizing databases and get estimates of actuator sizing by data interpolation, or using scaling methods. Rapid sizing tools with appropriate levels of accuracy have been developed in the past, specifically for EHA and EMA systems [1,[6][7][8]. Munjulury et al [6] proposed their method to scale EHA and EMA used as control surface actuators based on physical mathematical models for hydraulic components and scaling laws for the electric actuator components.…”

Section: Project Motivationmentioning

confidence: 99%

Size Estimation Tools for Conventional Actuator System Prototyping in Aerospace

Dussart

Lone

O'Rourke

2019

AIAA Scitech 2019 Forum

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Predicting the size of an actuator capable of reaching given performance requirements is a critical step for any systems design. Thus, to help in the prototyping and early development stages of such devices, simple mathematical models were developed, which can be used with little knowledge in actuation system design. Based on physical phenomenons at the heart of the actuation mechanism, these models can be used to estimate diameter and length, and therefore volume and weight of conventional actuators as a function of performance requirements. Models include linear hydraulic pistons and electric motors, divided into radial and axial flux machines. Off-the-shelf actuators and more aerospace specific products were used to validate and assess the accuracy of the models over a wide range of force and torque requirements. Simple sizing examples for aerospace actuation systems are also given as use-cases of the different tools. A discussion on model applicability, for various aircraft scales and applications concludes the paper.

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“…Nowak [14] has focused on presenting an algorithm of the optimization of the dynamic parameters of an electromagnetic linear actuator operating in error-actuated control system. Other contributions in design optimization of electromechanical actuators include [15][16][17][18][19][20][21].…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of Solenoid Actuated Butterfly Valves Dynamically Coupled in Series

Naseradinmousavi

2015

Volume 4A: Dynamics, Vibration, and Control

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In this effort, we present novel nonlinear modeling of two solenoid actuated butterfly valves subject to a sudden contraction and then develop an optimal configuration in the presence of highly coupled nonlinear dynamics. The valves are used in the so-called “Smart Systems” to be employed in a wide range of applications including bioengineering, medicine, and engineering fields. Typically, tens of the actuated valves are instantaneously operating to regulate the amount of flow and also to avoid probable catastrophic disasters which have been observed in the practice. We focus on minimizing the amount of energy used in the system as one of the most critical design criteria to yield an efficient operation. We optimize the actuation subsystems interacting with the highly nonlinear flow loads in order to minimize a lumped amount of energy consumed. The contribution of this work is to include coupled nonlinearities of electromechanical valve systems to optimize the actuation units. Stochastic, heuristic, and gradient based algorithms are utilized in seeking the optimal design of two configurations of solenoid actuated valves. The results indicate that substantial amount of energy can be saved by an intelligent design that helps select parameters carefully but also uses flow torques to augment the closing efforts.

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Electric Control Surface Actuator Design Optimization and Allocation for the More Electric Aircraft

Cited by 26 publications

References 17 publications

Development of a Sizing and Analysis Tool for Electrohydrostatic and Electromechanical Actuators for the More Electric Aircraft

Development of a Sizing and Analysis Tool for Electrohydrostatic and Electromechanical Actuators for the More Electric Aircraft

Size Estimation Tools for Conventional Actuator System Prototyping in Aerospace

Optimal Design of Solenoid Actuated Butterfly Valves Dynamically Coupled in Series

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