Browse Topic: Flight control actuators

Items (95)
Find
Actuators, Linear Mechanical, General Specification GuideARP5812 (Current)1/9/2025
This SAE Aerospace Recommended Practice (ARP) establishes design, manufacturing performance and test requirements for linear mechanical actuators intended to be used for linear motion applications in response to manual or automatic power control system inputs. It is applicable, but not confined to, ball screws, sliding contact screws, roller screws, helical splines, rack and pinion assemblies, and skewed roller actuators. It is a reference for preparing detail specifications for mechanical actuators compatible and applicable to military or commercial aircraft systems.
A-6B3 Electro-Mechanical Actuation Committee
Flight Control Actuators - Dynamic Seals, Collection of Duty Cycle DataARP4895B (Current)12/18/2024
This SAE Aerospace Recommended Practice (ARP) provides an algorithm aimed to analyze flight control surface actuator movements with the objective to generate duty cycle data applicable to hydraulic actuator dynamic seals.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Descriptions of Systems Integration Test Rigs (Iron Birds) for Aerospace ApplicationsAIR5992 (Current)4/26/2023
This Aerospace Information Report (AIR) provides information on systems integration rigs, commonly referred to as “Iron Birds” for aerospace applications. a It includes background historical information including descriptions of Iron Birds produced to date, important component elements and selection rationale, hydraulic system design and operational modes and illustrates the design approaches to be considered. b It provides illustrations of the various systems that should be considered for Iron Bird testing in the development phase and utilization during the production program. c It includes recommendations for simulation, component development tests, system integration and lessons learned.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Aircraft Flight Control Actuation System Failure-Detection MethodsAIR5273A (Current)12/16/2022
This SAE Aerospace Information Report (AIR) provides descriptions of aircraft flight control actuation system failure-detection methods. The fault-detection methods are those used for ground and in-flight detection of failures in electrohydraulic actuation systems for primary flight controls.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Aerospace-Interface Definition for Mechanical Actuation SubsystemsARP5311 (Current)1/1/2022
This SAE Aerospace Recommended Practice (ARP) defines all the relevant issues that affect the generation of an Interface Control Document for Mechanical Actuation Sub-Systems. It is intended to provide to all parties involved with the generation of Mechanical Actuation Sub-Systems, a definition of documentation, drawings, reports and design parameters required to assure a successful development of mechanical actuation sub-systems for Aerospace-Military and Commercial applications.
A-6B3 Electro-Mechanical Actuation Committee
Recommended Guidelines for the Specifications of Motor Control Electronics for Electrically Powered ActuatorsARP7490 (Current)11/16/2021
This SAE Aerospace Recommended Practice (ARP) provides guidelines for the creation of specifications for the Motor Control Electronics (MCE) that are used for operating electrically powered actuators including: Electromechanical Actuators (EMAs) Electrohydrostatic Actuators (EHAs) Electric Back-Up Hydraulic Actuators (EBHAs)
A-6B2 Electrohydrostatic Actuation Committee
Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS1290C (Current)2/12/2021
This SAE Aerospace Standard (AS) provides a system of graphic symbols and line codings that are intended primarily for usage in hydraulic and pneumatic system schematic diagrams for all types of aircraft.
A-6 Aerospace Actuation, Control and Fluid Power Systems
High-Performance, Piezoelectric, Hybrid Synthetic Jet ActuatorsTBMG-361813/1/2020
NASA Langley Research Center has invented three serial high-performance, piezoelectric, hybrid synthetic jet actuators to provide active flow control for current and future wing-borne vehicles in subsonic, transonic, and supersonic flow. Effective active flow control results in reduced vehicle drag and the prevention of events that can lead to catastrophic loss.
Aerospace - Impulse Testing of Hydraulic ComponentsARP1383C (Current)2/24/2020
This SAE Aerospace Recommended Practice (ARP) defines impulse test procedures that are recommended for hydraulic components.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Aerospace Fluid Power - FAA Regulatory History - Transport Airplane Hydraulic SystemsAIR5696A (Current)9/3/2019
This SAE Aerospace Information Report (AIR) contains regulatory and guidance information related to transport airplane hydraulic systems. It contains certain Civil Air Regulations (CAR) and Federal Aviation Regulations (formerly referred to as FARs) from Title 14 Code of Federal Regulations (CFR) in their current version as well as the historical versions. This gives the reader an ability to assemble certain CAR/CFR parts as they existed at any date in the past (referred to as a Regulatory Basis). A certain amount of preamble explanatory material is included, which led to the regulatory rule changes (Amendments to the CFR).
A-6A1 Commercial Aircraft Committee
Information on Electric BrakesAIR5937 (Current)2/15/2019
This SAE Aerospace Information Report (AIR) describes the design, operation, and attributes of electrical braking systems for both military and commercial aircraft. At this time, the document focuses only on brakes utilizing electromechanical actuators (EMAs), as that is the present state of the art. As such, the discussions herein assume that EMAs can simply replace the hydraulic actuation portion of typical brake system leaving things such as the wheel and heat sink unchanged. Furthermore, the document provides detail information from the perspective of brake system design and operation. The document also addresses failure modes, certification issues, and past development efforts. Details on the design and control of electric motors, gear train design, ball or roller screw selection are available in the reference documents and elsewhere, but are outside the scope of this document. Other all-electric technologies such as piezoelectric actuation or more exotic methods of applying drag to a rotating wheel may be included at a later time. Important: Electric braking systems for aircraft are at the early stages of production implementation. There are also a variety of control schemes that may be used to provide acceptable EMA performance. As a result, many of the details involved in the design of electric brake systems are proprietary or competition sensitive to the brake system OEMs. This AIR attempts to provide a basic technical overview of electric brakes without compromising any particular manufacturer's intellectual property concerns.
A-5A Wheels, Brakes and Skid Controls Committee
Vehicle Management Systems - Flight Control Function, Design, Installation and Test of Piloted Military Aircraft, General Specification ForAS94900A (Current)8/13/2018
This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Description of Actuation Systems for Aircraft With Fly-By-Wire Flight Control SystemsAIR4253B (Current)7/24/2018
This SAE Aerospace Information Report (AIR) provides design information of various contemporary aircraft fly-by-wire (FBW) flight control actuation systems that may be useful in the design of future systems for similar applications. It is primarily applicable to manned aircraft. It presents the basic characteristics, hardware descriptions, redundancy concepts, functional schematics, and discussions of the servo controls, failure monitoring, and fault tolerance. All existing FBW actuation systems are not described herein; however, those most representing the latest designs are included. While this AIR is intended as a reference source of information for aircraft actuation system designs, the exclusion or omission of any other appropriate actuation system or subsystem should not limit consideration of their use on future aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Framework for Modelling and Simulation of Multi-Physics Aircraft Systems with Distributed Electronic Controllers2017-01-21159/19/2017
Multi-physics interactions between structural, electrical, thermal, or hydraulic components and the high level of system integration, characteristic of new aircraft designs, is increasing the complexity of both design and verification processes. Therefore the availability of tools, supporting integrated modelling, simulation, optimization and testing across all stages of aircraft design remains a critical challenge. This paper presents some results of the project MISSION (Modelling and Simulation Tools for Systems Integration on Aircraft). It is a collaborative task being developed under the European Union Clean Sky 2 Program, which is a public-private partnership bringing together aeronautics industrial leaders and public research organizations based in Europe. The first levels of integration of different models and tools proposed in the MISSION framework will be presented, along with simulation results. The paper will highlight the workflow to perform the various stages of virtual testing and the proposed way to exchange artifacts within the modelling and analysis framework. The considered system under test is an electromechanical flight control actuator together with the related control logic. The plant system is natively a physical model based on MODELICA and the causal control system is natively a MATLAB/Simulink model. These models are used in different PC-based simulation platforms, in order to perform virtual tests of different maturity levels of the embedded system by Model-in-the-Loop (with ESI ITI SimulationX and MATLAB/Simulink), Software-in-the-Loop (with dSPACE VEOS) and Virtual-Processor-in-the-Loop (with ALES DESYRE). The alignment of the simulation results demonstrates the successful model based integration. In addition, some tool specific results and metrics are presented.
Burgio, Gilberto, Mangeruca, Leonardo, Ferrari, Alberto, Carloni, Marco, Valdivia-Guerrero, Virgilio, Albiol-Tendillo, Laura, Govindaraju, Parithi, Gottschall, Marcel, Oelsner, Olaf, Reglitz, Sören, Stavesand, Jann-Eve, Himmler, Andreas, Yapi, Lionel
Terminology and Definitions for Aerospace Fluid Power, Actuation and Control TechnologiesARP4386D (Current)7/18/2017
This SAE Aerospace Recommended Practice (ARP) provides the technical terms and nomenclature, together with their definitions and abbreviations/acronyms that are used in aerospace fluid power, actuation and control systems. NOTE: ARP490 and ARP4493 are sources for definitions specifically for electrohydraulic servovalves.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Modelling and Simulation Tools for Systems Integration on AircraftTBMG-269926/1/2017
The provision of integrated modeling, simulation and optimization tools to effectively support all stages of aircraft design remains a critical challenge in the aerospace industry. While several breakthroughs have been achieved in this area, costly iterations are still often necessary to successfully design, develop, integrate, validate and verify the components and subsystems of modern aircraft. The high level of system integration that is characteristic of new aircraft designs is dramatically increasing the complexity of both design and verification – in particular for fault condition analysis and the implementation of defect-free software (Figure 1).
Modelling and Simulation Tools for Systems Integration on Aircraft17AERP06_036/1/2017
The provision of integrated modeling, simulation and optimization tools to effectively support all stages of aircraft design remains a critical challenge in the aerospace industry. While several breakthroughs have been achieved in this area, costly iterations are still often necessary to successfully design, develop, integrate, validate and verify the components and subsystems of modern aircraft. The high level of system integration that is characteristic of new aircraft designs is dramatically increasing the complexity of both design and verification - in particular for fault condition analysis and the implementation of defect-free software (Figure 1). Simultaneously, the multi-physics interactions between structural, electrical, thermal, and hydraulic components have become more significant as the systems become increasingly interconnected (e.g. the interaction among thermal load due to increased cabin electrical power usage, an electrically-powered environmental control system, and electrically powered flight control actuation).
Aerospace Fluid Power Electrohydrostatic Module, Design, Performance and Test RecommendationsARP6154 (Current)3/15/2017
This Aerospace Recommended Practice provides general requirements for Electrohydrostatic Module (EHM) that is used in Electrohydrostatic Actuator (EHA) for aerospace applications. This document includes design, performance and test (production and qualification) requirements.
A-6B2 Electrohydrostatic Actuation Committee
Aerospace Hydraulics and Actuation Lessons LearnedAIR4543/1A (Current)2/23/2017
This SAE Aerospace Information Report (AIR) contains Lessons Learned from aerospace actuation, control and fluid power systems technologies. The lessons were prepared by engineers from the aerospace industry and government services as part of the work of SAE Committee A-6, Aerospace Actuation, Control and Fluid Power Systems. Each lesson was presented to the appropriate A-6 technical panel. The technical topics are organized into five sections covering systems, actuation, hydraulic components, electrical components and miscellaneous, each further divided into subsections. The information topics are presented in a concise format of Problem, Issue, Solution and Lesson Learned, often with accompanying descriptive diagrams and illustrations for clarity and understanding.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Aerospace Hydraulics and Actuation Lessons LearnedAIR4543C (Current)2/9/2017
This SAE Aerospace Information Report (AIR) contains Lessons Learned from aerospace actuation, control and fluid power systems technologies. The lessons were prepared by engineers from the aerospace industry and government services as part of SAE Committee A-6, Aerospace Fluid Power, Actuation, and Control Technologies, and were presented to the A-6 during meetings held from 1989 through 1999. The document is organized into five sections covering systems, actuation, hydromechanical components, electrical components and miscellaneous, each further divided into subsections. The lessons are presented in a concise format of Problem, Issue, Solution and Lesson Learned, often with accompanying descriptive diagrams and illustrations for clarity and understanding. Because of the potential growth in the size of the document as new lessons are published, those presented to the A-6 Committee in 2000 and later years are planned to be released in separate slash number documents, AIR4543/1, AIR4543/2 and so on.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Aircraft Flight Control Systems DescriptionsAIR4094A (Current)7/18/2016
This SAE Aerospace Information Report (AIR) supplies information on the flight control systems incorporated on various current and historic fixed wing, rotary wing, and tilt rotor aircraft. A brief description of the aircraft is followed by a description of the flight control system, some specific components, drawings of the internal arrangement, block diagrams, and schematics. System operation redundancy management is also presented.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Loss-of-Control Mishaps in Revenue Airline ServiceAIR6237 (Current)7/12/2016
The scope of this document is to provide review of recent history of loss-of-control accidents during airline revenue operations.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Primary Flight Control Hydraulic Actuation System Interface DefinitionAIR4922A (Current)10/19/2015
This SAE Aerospace Information Report (AIR) provides a description of the interfaces and their requirements for generic and specific hydraulic actuation systems used in the flight control systems of manned aircraft. Included are the basic control system characteristics and functional requirements, and the essential interfaces (structural, mechanical, hydraulic power, control input, status monitoring, and environment). Major design issues, requirements, and other considerations are presented and discussed.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Aerospace - General Requirements for Commercial Aircraft Hydraulic ComponentsAS4941B (Current)3/9/2015
This SAE Aerospace Standard (AS) provides general requirements for components that are used in commercial aircraft hydraulic systems. It also includes the 14 CFR Part 25/CS 25 regulations that apply to hydraulic components. It also provides information to be included in the Procurement Specification in Appendix A and a checklist for design reviews in Appendix B. It does not provide requirements for distribution elements such as hoses, pipe fittings and general tubing.
A-6A1 Commercial Aircraft Committee
Aerospace Design and Installation of Commercial Transport Helicopter Hydraulic SystemsARP4925B (Current)10/9/2014
This SAE Aerospace Recommended Practice (ARP) establishes the factors which should be considered in the design and installation of a commercial transport rotorcraft hydraulic system, including the applicable airworthiness regulations that affect the hydraulic system. This ARP also provides information and guidelines on the many factors that arise in the design process to provide cost effectiveness, reliability, maintainability and accepted design and installation practices.
A-6A1 Commercial Aircraft Committee
Determination of Cost Benefits from Implementing an Integrated Vehicle Health Management SystemARP6275 (Historical)7/7/2014
This ARP provides insights on how to perform a cost benefit analysis (CBA) to determine the return on investment that would result from implementing an integrated Health Management (HM) system on an air vehicle. The word “integrated” refers to the combination or “roll up” of sub-systems health management tools to create a platform centric system. The document describes the complexity of features that can be considered in the analysis, the different tools and approaches for conducting a CBA and differentiates between military and commercial applications. This document is intended to help those who might not necessarily have a deep technical understanding or familiarity with HM systems but want to either quantify or understand the economic benefits (i.e., the value proposition) that a HM system could provide. Prognostics is a capability within some HM systems that provides an estimation of remaining useful life (RUL) or time to failure and so Prognostic Health Management (PHM) is used where this predictive element exists. IVHM refers to an integrated vehicle level system deployed on a fleet of platforms and might, but not necessarily, include predictive elements.
HM-1 Integrated Vehicle Health Management Committee
Aerospace - Design and Installation of Commercial Transport Aircraft Hydraulic SystemsARP4752B (Current)12/2/2013
This SAE Aerospace Recommended Practice (ARP) provides guidance for the design and installation of a commercial aircraft hydraulic system to meet the applicable requirements, including the applicable airworthiness regulations that affect the hydraulic system design. This ARP also provides information and guidelines on the many factors that arise in the design process to provide cost effectiveness, reliability, maintainability and accepted design and installation practices.
A-6A1 Commercial Aircraft Committee
Aerospace Fluid Power - FAA Regulatory History - Transport Airplane Hydraulic SystemsAIR5696 (Historical)11/22/2013
This SAE Aerospace Information Report (AIR) contains regulatory and guidance information related to transport airplane hydraulic systems. It contains certain Civil Air Regulations (CAR) and Federal Aviation Regulations (formerly referred to as FARs) from Title 14 Code of Federal Regulations (CFR) in their current version as well as the historical versions. This gives the reader an ability to assemble certain CAR/CFR parts as they existed at any date in the past (referred to as a Regulatory Basis). A certain amount of preamble explanatory material is included, which led to the regulatory rule changes (Amendments to the CFR).
A-6A1 Commercial Aircraft Committee
Long-Term Storage of Missile Hydraulic SystemsAIR974B (Current)10/4/2013
Much of the available long-term storage test data has been reviewed and topically separated to enable the independent discussion of storage effects on fluids, seals, hydraulic components, and hydraulic systems. Comments are made in Section 4 concerning the applicability of the test results and regarding design practices for storability. Conclusions are drawn in Section 5 regarding inactive storage of hydraulic systems for at least a 7 year period.
A-6A2 Military Aircraft Committee
Integrated Vehicle Health Management: Essential ReadingPT-1629/25/2013
Integrated Vehicle Health Management (IVHM) is a relatively new subject, with its roots back in the space sector of the early 1990s. Although many of the papers written around that time did not refer to it as IVHM, the fundamental principles of considering an integrated end-to-end system to monitor the overall health of the asset were clearly visible. As the subject of Integrated Vehicle Health Management (IVHM) and its associated technologies have grown up, businesses are making the transformation from selling a product to selling a service. This can be viewed as a positive disruption, as a relatively small technology breakthrough is being brought to market for a large business benefit. The sequence “sense—acquire—transfer—analyze—act “ feeds the information (processed data) on the asset’s health into the Operations or Management control center. Here, decisions can be made on maintenance actions with knowledge of the supply chain status, MRO loading, etc., provided by Maintenance and Logistics systems. Undoubtedly, a much more efficient and economical modus operandi. This book brings together a collection of twenty –two SAE International Technical papers on this very theme, organized according to specific areas of interest: • Engines • Airframes • Electrical Power Systems • Supporting Systems • Architecture They were selected by Dr. Ian K. Jennions, Director of IVHM Center at Cranfield University, in the UK. Dr. Jennions was also the editor of three other books on Integrated Vehicle Health Management, published by SAE International: • IVHM: Perspectives on an Emerging Field • IVHM: Business Case Theory and Practice • IVHM: The Technology
Jennions, Ian K.
A Methodology for Systems Integration in Aircraft Conceptual Design - Estimation of Required Space2013-01-22359/17/2013
This paper presents a methodology for conceptual aircraft design to evaluate the space available for systems (top-down approach) and to estimate the space required for critical components impacting the aircraft configuration (bottom-up approach). The presented top-down approach introduces the concept of “equivalent design volume”, including the space required for systems and the associated empty space to access, maintain and ventilate them. This approach enables an early feasibility check for aircraft configuration exploration regarding the integration and installation of systems, without having to detail the system architecture. In complement, the bottom-up approach introduces the estimation of the required dimensions for critical components. Here, the example of the flight control actuators integration in the wing tip is presented.
Liscouet-Hanke, Susan, Huynh, Kenny
Cold Gas Systems, Missile or Projectiles Design, Installation, Tests and Requirements ForARP1625B (Current)6/5/2013
Systems shall be classified in terms of type, category and class.
A-6A2 Military Aircraft Committee
Ship Systems and Equipment - Hydraulic Systems - Noise ControlJ1782_201305 (Current)5/31/2013
Hydraulic systems are used on marine vehicles for steering, vehicle control, and utility services. System components that generate and transmit noise are of concern. This SAE Information Report (a) addresses noise requirements which may apply to the hydraulic systems of ships and submersibles, and (b) identifies noise sources and techniques which may be used to reduce system noise. Noise of power sources (e.g., electric motors) and end items (e.g., steering linkages) is beyond the scope of this document.
Ship Fluid Systems Committee
Analysis of Helicopter Flight Dynamics Through Modeling and Simulation of Primary Flight Control Actuation SystemVFS-F69-0935/21/2013
The work presented describes a hydraulic servo system consisting of nonlinear valve and actuator dynamics and its effect on rotorcraft dynamics. An empirical second order model is used to describe valve dynamics, and accounts for both internal friction and hysteresis. Pressure dynamics in the actuator are calculated using the continuity equation including the effects of fluid compressibility. Actuator dynamics are determined via Newton's second law and a force summation including chamber pressures, friction on the piston, and external forcing. The model is integrated with HeliUM, a state space nonlinear rotorcraft flight dynamics simulation model. A linearized dynamic analysis of coupled actuator and rotorcraft dynamics are carried out with models obtained using numerical linearization. Rotorcraft performance is quantified through the use of frequency response data and handling qualities metrics. The effects of nonlinearities such as displacement and rate saturation on the dynamics of the rotorcraft is studied.
Nelson, Hunter, Celi, Roberto
Aerospace - Vehicle Management Systems - Flight Control Design, Installation and Test of, Military Unmanned Aircraft, Specification Guide ForARP94910 (Current)12/19/2012
This document establishes recommended practices for the specification of general performance, design, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military Unmanned Aircraft (UA), the airborne element of Unmanned Aircraft Systems (UAS), as defined by ASTM F 2395-07. The document is written for military unmanned aircraft intended for use primarily in military operational areas. The document also provides a foundation for considerations applicable to safe flight in all classes of airspace.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Electrical Energy Storage for Energy Optimized Aircraft2012-01-222610/22/2012
Given the goal of developing energy-optimized aircraft that employ increasingly higher power loads such as electric flight control actuation, directed energy weapon systems and on-demand cooling systems, advances in battery technology and associated integration methodology will be required to achieve a robust electrical power system design. Batteries based on various Lithium-Ion chemistry technologies represent a 50% improvement in both specific energy and specific power over legacy NiCad and Lead-Acid chemistries. However, along with these benefits come challenges in terms of overall safety, cost and availability. Safety considerations primarily include failure modes that result from the battery being subjected to short-circuit conditions and over-charge conditions. Cost and availability challenges arise primarily from one-off point designs and ensuing low production volumes, but also stem from limited marketplace competition. With respect to safety, recent developments in various subsets of Li-Ion chemistry including iron-phosphate cells indicate potential improvements in short-circuit and over-voltage performance. These cells should be extensively tested in effort to verify those claims as well to characterize their performance in general. External to the battery, EPS architectures should employ robust fault coordination and the use of external switches driven by electronics for both short-circuits and over-charge protection. To address cost and availability, as well as safety, it is recommended that air-framers leverage the electric vehicle industry in its pursuit of safe, low-cost batteries. The automotive industry represents greater volume than the aircraft industry as well as broadens the potential supplier base. Further, it is recommended that the air-framers investigate and possess experience in numerous vehicle-battery integration methods and technologies including the unique requirements of more-electric aircraft and DEW systems. Some programs have indeed demonstrated success in floating Lithium-Ion batteries on the bus under more-electric transient as well as emergency operation conditions. Integrating a battery that supports a weapon requires a clear understanding of the expected operation of that weapon including duty cycle and depth of magazine, both of which critically affect discharge and recharge rates of the battery and ultimately it safe operation. This paper addresses in detail various approaches to mitigating the aforementioned challenges of safety, affordability and availability.
Knowles, Jeff
Electrical Actuation Systems for Aerospace and Other ApplicationsARP4255A (Current)3/29/2012
This Aerospace Recommended Practice (ARP) is intended as a guide in the preparation of Procurement Specifications for electrical actuator systems to be used in aerospace and other applications. Detail requirements, as necessary to completely define a specific actuator, are the responsibility of the procuring agency.
AE-7A Generators and Controls Motors and Magnetic Devices
Airbus - EMAs for Flight Controls Actuation System - An Important Step Achieved in 201111VATC404003/21/2012
A significant step is achieved on the flight control actuation system toward the more electrical aircraft through the Airbus A380, A400M and the A350 development phase ongoing. The A380/A400M/A350 features a mixed flight control actuation power source distribution, associating electrically powered actuators with conventional FlyByWire hydraulic servocontrols. In the scope of the preparation of the future Airbus Aircraft, this paper presents the perspectives of the use of the EMA technologies for the flight control systems in the more electrical aircraft highlighting the main technical challenges need to treat: jamming susceptibility, ?on board? maintenance reduction, Operational reliability increase, power electronics and power management optimization, and regarding the environmental constraints, the predicted performances; the benefits associated to the optimized utilization of on-board power sources. On the 4th of January 2011, an aileron EMA was successful flown on Airbus A320 MSN1. It is an important step towards the EMA technology for flight control actuation system. Presenter Michel Todeschi
Todeschi, Michel
Aerospace Hydraulics and Actuation Lessons LearnedAIR4543/1 (Historical)12/12/2011
This SAE Aerospace Information Report (AIR) contains Lessons Learned from aerospace actuation, control and fluid power systems technologies. The lessons were prepared by engineers from the aerospace industry and government services as part of the work of SAE Committee A-6, Aerospace Actuation, Control and Fluid Power Systems. Each lesson was presented to the appropriate A-6 technical panel. The technical topics are organized into five sections covering systems, actuation, hydraulic components, electrical components and miscellaneous, each further divided into subsections. The information topics are presented in a concise format of Problem, Issue, Solution and Lesson Learned, often with accompanying descriptive diagrams and illustrations for clarity and understanding.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Airbus - EMAs for Flight Controls Actuation System - An Important Step Achieved in 20112011-01-273210/18/2011
A significant step is achieved on the flight control actuation system toward the more electrical aircraft through the Airbus A380, A400M and the A350 development phase ongoing. The A380/A400M/A350 features a mixed flight control actuation power source distribution, associating electrically powered actuators with conventional FlyByWire hydraulic servocontrols. In the scope of the preparation of the future Airbus Aircraft, this paper presents the perspectives of the use of the EMA technologies for the flight control systems in the more electrical aircraft highlighting the main technical challenges need to treat: jamming susceptibility, “on board” maintenance reduction, Operational reliability increase, power electronics and power management optimization, and regarding the environmental constraints, the predicted performances; the benefits associated to the optimized utilization of on-board power sources. On the 4th of January 2011, an aileron EMA was successful flown on Airbus A320 MSN1. It is an important step towards the EMA technology for flight control actuation system.
Todeschi, Michel
Hydraulic Systems, Military Aircraft, Design and Installation, Requirements ForAS5440A (Historical)1/3/2011
This specification covers the design and installation requirements for Types I and II military aircraft hydraulic systems.
A-6A2 Military Aircraft Committee
Aerospace Hydraulics and Actuation Lessons LearnedAIR4543B (Historical)11/18/2010
This SAE Aerospace Information Report (AIR) contains Lessons Learned from aerospace actuation, control and fluid power systems technologies. The lessons were prepared by engineers from the aerospace industry and government services as part of SAE Committee A-6, Aerospace Fluid Power, Actuation, and Control Technologies, and were presented to the A-6 during meetings held from 1989 through 1999. The document is organized into five sections covering systems, actuation, hydromechanical components, electrical components and miscellaneous, each further divided into subsections. The lessons are presented in a concise format of Problem, Issue, Solution and Lesson Learned, often with accompanying descriptive diagrams and illustrations for clarity and understanding. Because of the potential growth in the size of the document as new lessons are published, those presented to the A-6 Committee in 2000 and later years are planned to be released in separate slash number documents, AIR4543/1, AIR4543/2 and so on.
A-6 Aerospace Actuation, Control and Fluid Power Systems
A Method of Shared Regenerative Power Management2010-01-177811/2/2010
The characteristics of large electrical loads encountered in the modern More Electric Aircraft (MEA) require regenerative power processing in order to preserve the power quality within acceptable transient and steady state limits. In an MEA with large active loads and pulsed power demands, it is necessary to employ an architecture that safely and effectively processes regenerative energy resulting from the dynamic loads. For instance, the electrical flight control actuation presents one of the largest regenerative power sources encountered by the generation system. Typical approach is to dissipate this energy through resistors of the power electronics which increases the size and penalizes the aircraft. This paper covers certain regenerative load properties, their electrical characteristics, the common approaches for mitigating regenerative power challenges, and an innovative approach for processing regenerative power by effectively utilizing on-board equipment to minimize the burden of the primary power generation and distribution system.
Tajirian, Edmond, Walia, Paramjit (Pete), Lui, Clarence, Wong, Ivan, Lee, Chris
Terminology and Definitions for Aerospace Fluid Power, Actuation and Control TechnologiesARP4386C (Historical)7/22/2010
This SAE Aerospace Recommended Practice (ARP) comprises the technical terms and nomenclature, together with their definitions and abbreviations that are used in aerospace Fluid Power Actuation and Control Systems. NOTE: When a term is applicable to more than one branch or segment of the technology it may have different meanings and definitions in each. Where this occurs the multiple listings with appropriate designations will be shown under the same primary term.
A-6 Aerospace Actuation, Control and Fluid Power Systems
Electrically Driven General Systems for UAVsTBMG-582610/1/2009
General systems are defined as all of the flight safety critical systems of an aircraft, excluding the engine and flight control computing. Usually, the main subsystems in a general system include the electrical power generation and distribution system, the primary and secondary flight control actuation system, the hydraulic system, the environmental control system, the fuel system, and the landing gear and brake system.
Long-Term Storage of Missile Hydraulic SystemsAIR974A (Historical)11/6/2008
Much of the available long-term storage test data has been reviewed and topically separated to enable the independent discussion of storage effects on fluids, seals, hydraulic components, and hydraulic systems. Comments are made in Section 4 concerning the applicability of the test results and regarding design practices for storability. Conclusions are drawn in Section 5 regarding inactive storage of hydraulic systems for at least a 7 year period.
A-6A2 Military Aircraft Committee
Primary Flight Control Hydraulic Actuation System Interface DefinitionAIR4922 (Historical)7/16/2008
This SAE Aerospace Information Report (AIR) provides a description of the interfaces and their requirements for generic and specific hydraulic actuation systems used in the flight control systems of manned aircraft. Included are the basic control system characteristics and functional requirements, and the essential interfaces (structural, mechanical, hydraulic power, control input, status monitoring, and environment). Major design issues, requirements, and other considerations are presented and discussed.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Aerospace Fluid Power - Materials and Characteristics of Flight Control Servoactuators of Various AircraftAIR4066B (Historical)7/6/2007
This SAE Aerospace Information Report (AIR) defines the materials, strength, and finishes utilized in current linear hydraulic flight control actuators. To keep the information at a relevant minimum, only cylinders (barrels), glands, and pistons are listed. Also identified are the reasons for the material selection and any pertinent comments. All data were collected from the respective suppliers.
A-6B1 Hydraulic Servo Actuation Committee
Aerospace - Flight Control Systems - Design, Installation and Test of Piloted Military Aircraft, General Specification ForAS94900 (Historical)7/6/2007
This specification establishes general performance, design, test, development and quality assurance requirements for the Flight Control Systems of military piloted aircraft. Flight Control Systems (FCS) include all components used to transmit flight control commands from the pilot or other sources to appropriate force and moment producers. Flight control commands normally result in control of aircraft altitude, airspeed, flight path, attitude, aerodynamic or geometric configuration, ride quality, and structural modes. Among components included are the pilot’s controls, dedicated displays and logic switching, system inertial and air data sensors, signal computation, test devices, mechanical transmission devices, actuators, power sources, and signal transmission lines dedicated to flight control. Excluded are aerodynamic surfaces, engines and engine control systems, rotorcraft rotors, fire control devices, crew displays and electronics not dedicated to flight control. In the event of conflict between this specification and other referenced documents, this specification shall govern. The detail requirements for a particular system shall be specified in the FCS Specification, 4.6.2, the Aircraft Detail Specification, the contract, or purchase order for that system. Most of the technical concepts and approaches covered by the document represent industry "best practice". They are based on sound and proven engineering practices and have demonstrated successful production experience. Others require specific approval from the procuring activity before use. This requirement for approval is not intended to prohibit their use; but rather to ensure that the prime contractor has fully investigated their capability to perform reliably and to be sufficiently durable under the required conditions and that the prime contractor can present substantiating evidence for approval before the design is committed to.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Aerospace - Design and Installation of Commercial Transport Aircraft Hydraulic SystemsARP4752A (Historical)7/5/2007
This SAE Aerospace Recommended Practice (ARP) establishes the requirements for the design and installation of a commercial aircraft hydraulic system, including the applicable airworthiness regulations that affect the hydraulic system. This ARP also provides information and guidelines on the many factors that arise in the design process to provide cost effectiveness, reliability, maintainability and accepted design and installation practices.
A-6A1 Commercial Aircraft Committee
Items per page:
1 – 50 of 95