Browse Topic: Flight control actuators

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Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS1290C (Current)02/12/2021
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
Technical Standard
Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS1290C-TEST-REC (Historical)02/12/2021
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
Technical Standard
Aerospace Fluid Power - Contamination Sensitivity - Considerations for Establishing Test Procedures for Flight Control ActuatorsARP5941 (Current)10/09/2020
This SAE Aerospace Recommended Practice (ARP) describes the design conditions under which tests should be conducted to demonstrate satisfactory performance of a flight critical servo-actuator under the maximum allowable particulate contamination in the associated airplane hydraulic system. Additionally, this document also describes the recommended tests and the required acceptance criteria.
A-6B1 Hydraulic Servo Actuation Committee
Recommended Practice
Electrohydraulic ServovalvesARP490G (Current)04/01/2020
This SAE Aerospace Recommended Practice (ARP) provides definitions and background information regarding the physical performance and testing of electrohydraulic flow control and pressure control servovalves. This ARP also provides extensive guidance for the preparation of procurement specifications and for functional testing. NOTE: An example of a procurement specification is provided as Appendix A.
A-6B1 Hydraulic Servo Actuation Committee
Recommended Practice
High-Performance, Piezoelectric, Hybrid Synthetic Jet ActuatorsTBMG-3618103/01/2020
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.
Magazine Article
In-Service Reliability Data of Continuously Active Ball Screw and Geared Flight Control Actuation SystemsAIR5713A (Current)10/14/2019
This Aerospace Information Report (AIR) has been written to provide in-service reliability data of continuously active ball screw and geared flight control actuation systems.
A-6B3 Electro-Mechanical Actuation Committee
Information Report
Flight Control Actuators - Dynamic Seals, Collection of Duty Cycle DataARP4895B (Current)05/16/2019
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
Recommended Practice
Automated 6DOF Model Generation and Actuator Sizing within AFSIM2019-01-133603/19/2019
The Air Force Research Laboratory has interest in automatically generating the extensive aerodynamic databases essential for six degree of freedom (6DOF) models and the use of 6DOF models for design. To be most useful, automation must include all aspects of producing the database including meshing, control surface deflections, running the CFD solution, and storage of the results. This effort applies newly-developed software to produce the desired results. Firstly, AFRL software called Computational Aircraft Prototype Syntheses (CAPS) allows automated meshing using the Advancing Front Local Reconnection (AFLR) software from Mississippi State University1 and automated control surface deflection using Engineering Sketch Pad (ESP) software from MIT/Syracuse. CAPS includes the ability to run the NASA CFD code FUN3D and interpret the FUN3D results via an Application Interface Module (AIM). This may sound like a complicated process. However, it is quite simple using a python interface to CAPS
Allison, Darcy, Shimmin, Kyle, Schley, William, Bryson, Dean
Technical Paper
Streamlining EMC Solutions for Avionics InterfacesTBMG-3377302/01/2019
Lightning strikes to jet airliners are common - about once every 1000 flight hours. The DO-160G standard, Environmental Conditions and Test Procedures for Airborne Equipment, is a standard for the environmental testing of avionics hardware. Many airplane manufacturers specify DO-160G Section 22, lightning induced transient susceptibility, as a requirement for critical systems like guidance, radars, communications, engine control, and heat and air controls. Aircraft fuselage, wing and tail flight controls, wing tips, fin tips, engine nacelles, and landing gear are the areas most likely to be hit by lightning strikes.
Magazine Article
Streamlining EMC Solutions for Avionics Interfaces19AERP02_0402/01/2019
Lightning strikes to jet airliners are common - about once every 1000 flight hours. The DO-160G standard, Environmental Conditions and Test Procedures for Airborne Equipment, is a standard for the environmental testing of avionics hardware. Many airplane manufacturers specify DO-160G Section 22, lightning induced transient susceptibility, as a requirement for critical systems like guidance, radars, communications, engine control, and heat and air controls. Aircraft fuselage, wing and tail flight controls, wing tips, fin tips, engine nacelles, and landing gear are the areas most likely to be hit by lightning strikes. Modern aircraft are designed with fly by wire systems for flight controls. Fly by wire means that inputs from either flight control computers or pilot manual inputs are transmitted electrically to a servomotor, which controls flight control actuators. Communication interfaces for these flight control systems can be implemented on an RS-485 physical layer. Communication
Magazine Article
Airborne Hydraulic and Control System Survivability for Military AircraftAIR1083C (Current)08/23/2018
This SAE Aerospace Information Report (AIR) provides the hydraulic and flight-control system designer with the various design options and techniques that are currently available to enhance the survivability of military aircraft. The AIR addresses the following major topics: a Design concepts and architecture (see 3.2, 3.5, and 3.6) b Design implementation (see 3.3, 3.6, and 3.7) c Means to control external leakage (see 3.4) d Component design (see 3.8)
A-6A2 Military Aircraft Committee
Information Report
Improving Component Life in Abrasive, Corrosive Aerospace EnvironmentsTBMG-2907906/01/2018
In industries such as aerospace, characterized by extreme operating environments that push materials and components to the edge of their design capabilities, companies are challenged to continually seek economically viable ways to maintain and improve performance.
Magazine Article
Document for 270 Voltage Direct Current (270 V DC) SystemARP4729A (Current)11/30/2017
This SAE Aerospace Recommended Practice (ARP) provides technical design and application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. This document also provides references and definitions to permit comparisons of various electrical systems and components.
AE-7C Systems
Recommended Practice
Advanced Partial Discharge Testing of 540V Aeronautic Motors Fed by SiC Inverter under Altitude Conditions2017-01-202909/19/2017
The present paper reports non-electrically intrusive partial discharge investigations on aeronautic and electric vehicle motors fed by SiC inverter drive under variable environmental conditions. A representative test procedure and experimental set-up based on operating aeronautic conditions are essential to ensure the accuracy and reliability of partial discharge test on aircraft systems to make informed decisions on insulation system design choice. The aim of this paper is to demonstrate the feasibility of partial discharge test of the insulation system on a different type of motor under such conditions, both electrically and environmentally. To do so, the paper will start by detailing the innovative experimental set-up to be used in the study. It mainly consists in a high-voltage (1000V) inverter drive using SiC components to provide fast rise time surges. A vacuum chamber is used to simulate altitude while the association of non-intrusive sensors, analog filtering and wavelet based
BILLARD, Thibaut, Abadie, Cedric, Taghia, Bouazza
Technical Paper
Modelling and Simulation Tools for Systems Integration on AircraftTBMG-2699206/01/2017
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).
Magazine Article
Modelling and Simulation Tools for Systems Integration on Aircraft17AERP06_0306/01/2017
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
Magazine Article
Aerospace Hydraulics and Actuation Lessons LearnedAIR4543/1A (Current)02/23/2017
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
Information Report
Actuators, Linear Mechanical, General Specification GuideARP5812 (Current)02/02/2017
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
Recommended Practice
Modelling and Simulation Tools for Systems Integration on Aircraft2016-01-205209/20/2016
This paper presents an overview of a project called “Modelling and Simulation Tools for Systems Integration on Aircraft (MISSION)”. This is a collaborative project being developed under the European Union Clean Sky 2 Program, a public-private partnership bringing together aeronautics industrial leaders and public research organizations based in Europe. 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. In particular the high level of system integration that is characteristic of new aircraft designs is dramatically increasing the complexity of both design and verification. Simultaneously, the multi-physics interactions between structural, electrical, thermal, and hydraulic components have become more significant as the systems become increasingly interconnected. The aim of MISSION is to develop and demonstrate an integrated modeling, simulation, design and
Valdivia-Guerrero, Virgilio, Foley, Ray, Riverso, Stefano, Govindaraju, Parithi, Elsheikh, Atiyah, Mangeruca, Leonardo, Burgio, Gilberto, Ferrari, Alberto, Gottschall, Marcel, Blochwitz, Torsten, Bloch, Serge, Taylor, Danielle, Hayes-McCoy, Declan, Himmler, Andreas
Technical Paper
Virtual Integration of an All-Electric Flight Control System Architecture and the Aircraft Electrical Power Distribution Network2016-01-203409/20/2016
The aviation industry is facing major challenges due to increased environmental requirements that are driven by economic constraints. For this reason, guidelines like "Flightpath 2050", the official guide of European aviation, call for significant reductions in pollutant emissions. The concept of the More Electric Aircraft offers promising perspectives to meet these demands. A key-enabler for this concept is the integration of new technologies on board of the next generation of civil transportation aircraft. Examples are electro-mechanical actuators for primary and secondary flight controls or the fuel cell technology as innovative electrical energy supply system. Due to the high complexity and interdisciplinarity, the development of such systems is an equally challenging and time-consuming process. To support the classical development process, a continuous model-based approach for the design and test of complex aircraft systems is currently developed at the Hamburg University of
Kreitz, Tobias, Thielecke, Frank
Technical Paper
Aircraft Flight Control Systems DescriptionsAIR4094A (Current)07/18/2016
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
Information Report
Loss-of-Control Mishaps in Revenue Airline ServiceAIR6237 (Current)07/12/2016
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
Information Report
Aerospace-Interface Definition for Mechanical Actuation SubsystemsARP5311 (Current)03/05/2016
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 Practice
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
Information Report
Descriptions of Systems Integration Test Rigs (Iron Birds) For Aerospace ApplicationsAIR5992 (Current)10/16/2015
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
Information Report
Simulation-Driven Methodology for the Requirements Verification and Safety Assessment of Innovative Flight Control Systems2015-01-247809/15/2015
The paradigm shift to focus on an enhancement of existing aircraft systems raises the question which of the many possible incremental improvements results in an advantageous solution still considering all existing requirements. Hence, new methodologies for aircraft system design are a prerequisite to cope with such huge and complex design spaces. In the case of flight control system optimization, major design variables are the control surface configuration and actuation as well as their functional allocation. Possible architecture topologies have to be verified inter alia with respect to system safety requirements. In this context, flight dynamic characteristics and handling qualities of the fully operational as well as of several degraded system states of each topology have to be evaluated and checked against common specifications. A model-based verification of the requirements is favorable, resulting in a rapid reduction of the design space. Safety objectives for valid configurations
Kreitz, Tobias, Bornholdt, Riko, Krings, Matthias, Henning, Karsten, Thielecke, Frank
Technical Paper
Architecture and Parameter Optimization for Aircraft Electro-Hydraulic Power Generation and Distribution Systems2015-01-241409/15/2015
The All-Electric-Engine with only electrical power offtake is a main goal in aircraft system development. The use of electric-motor pumps instead of engine-driven pumps for powering the central hydraulic systems could be a part of this objective. Additionally, the concept would meet the incremental development strategy performed by the aerospace industry today and saves costs by using state-of-the-art hydraulic actuation technology. This paper describes a process for optimizing such systems regarding their architecture and design parameters. For this task a methodology for the hydraulic consumer allocation called OPAL is used and extended by an automatic power system sizing. Feasible allocations, called permutations, are determined on the basis of preliminary system safety assessments regarding multiple top failure events. In the next step an automated sizing of the permutations is performed based on simplified hydraulic load analyses. This enables a comparison of a large number of
Dunker, Carsten, Bornholdt, Riko, Thielecke, Frank, Behr, Robert
Technical Paper
The Instantaneous Efficiency of Cantilever Geared Rotary Actuators in Flight Control Systems2015-01-241309/15/2015
The instantaneous efficiency of an epicyclic geared rotary actuator is an important factor in sizing flight control systems where compound epicyclic gear trains are typically used. The efficiency variation can be smooth or fluctuating depending on the combination and timing of the teeth of ring gears, planet gears and sun gears. In a previous paper [1], the instantaneous efficiency characteristics of actuators with symmetric planets were investigated. The actuator's reacting forces on the planets are symmetric and the overall length of the planet gears will not affect the efficiency. In this paper, a cantilever actuator with asymmetric planet gears is studied. The length and location of the reaction forces on the planet gears are key factors in the efficiency calculation. Theoretical derivation is presented and test results are compared.
Wang, Anngwo, Davies, Jonathan, Gitnes, Seth, El-Bayoumy, Lotfi
Technical Paper
The Increasing Use of Electrical Actuators in the Aerospace and Defense IndustryTBMG-2266908/01/2015
Hydraulic and pneumatic systems have traditionally been the market leader in providing power in the aerospace and defense industry because of their low cost and high power density. But in recent years, attention has been focused on the limitations of hydraulic actuators, including their weight, performance, and high maintenance requirements, as well as concerns over their vulnerability due to security issues and other risks.
Magazine Article
Aerospace Design and Installation of Commercial Transport Helicopter Hydraulic SystemsARP4925B (Current)10/09/2014
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
Recommended Practice
Energy Analysis of Electromechanical Actuator under Simulated Aircraft Primary Flight Control Surface Load2014-01-218209/16/2014
The purpose of this study is to set up a laboratory test apparatus to analyze aircraft flight control EMAS' electrical and thermal energy flow under transient and dynamic flight profiles. A hydraulic load frame was used to exert load to the EMA. The actuator was placed within an environmental chamber which simulates ambient temperature as function of altitude. The simulated movement or stroke was carried out by the EMA. The under test EMA's dynamic load, stroke, and ambient temperature were synchronized through a real time Labview DAQ system. Motor drive voltage, current, regenerative current, and motor drive and motor winding temperature were recorded for energy analysis. The EMA under test was subjected to both transient and holding load laid out in a test matrix. It was found that the transient missions of EMAS presented the most electric demand on the aircraft electric power supply system while holding presented the most severe thermal stress on the EMAS, where the EMAS operated at
Racine, Evan, Lammers, Zachary, Barnett, Street, Murphy, John, Leland, Quinn
Technical Paper
Optimization of the Power Allocation for Flight Control Systems2014-01-218809/16/2014
Due to a shift of the major aviation concerns to focus on enhancements of the successful programs instead of pushing their successors, the need for new methodologies for aircraft system architecture design emerges. Challenging the existing requirements and reconsidering the functions and their allocation could help to dissolve the system specific development paradigm and lead to beneficial architecture concepts. To help understand the mechanisms and boundary conditions of developing fault-tolerant systems, the first part of the paper gives an overview of the successive process of architecture design. The significant architectural design decisions and the concurrent safety assessment process are discussed. One crucial step in the design space exploration of future aircraft system architectures is the allocation of the consumers to the available power sources. Within the paper a methodology for the optimization of the power allocation for flight control systems is proposed. With this
Bornholdt, Riko, Thielecke, Frank
Technical Paper
Thermal Management System Concept with an Autonomous Air-Cooled System2014-01-221309/16/2014
Electrical power management is a key technology in the AEA (All-Electric Aircraft) system, which manages the supply and demand of the electrical power in the entire aircraft system. However, the AEA system requires more than electrical power management alone. Adequate thermal management is also required, because the heat generated by aircraft systems and components increases with progressive system electrification, despite limited heat-sink capability in the aircraft. Since heat dissipation from power electronics such as electric motors, motor controllers and rectifiers, which are widely introduced into the AEA, becomes a key issue, an efficient cooling system architecture should be considered along with the AEA system concept. The more-electric architecture for the aircraft has been developed; mainly targeting reduced fuel burn and CO2 emissions from the aircraft, as well as leveraging ease of maintenance with electric/electronic components. The AEA should pursue more efficient and
Morioka, Noriko, Saito, Hidefumi, Takahashi, Norio, Seta, Manabu, Oyori, Hitoshi
Technical Paper
Long-Term Storage of Missile Hydraulic SystemsAIR974B (Current)10/04/2013
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
Information Report
Integrated Reconfigurable Aero-Propulsion (IRAP) Control for Improved Fault Tolerance2013-01-225509/17/2013
In this paper we present results of a study of an integrated aero-propulsion flight control system. The resulting problem is that of controlling the system in which actuators operate on different time scales. This is a difficult problem since the control strategy needs to balance between not using the slow actuator at all, and slowing down the overall system to the time scale of the slow actuator. In the case of aero-propulsion control design for F/A-18 aircraft, the part of the control derivative matrix associated with engines is not full rank so not all states of interest can be simultaneously forced to track the commands. A control strategy that takes this constraint into account has been developed. The proposed IRAP approach is illustrated through simulation of F/A-18 aircraft dynamics under flight-critical control effector failures.
Boskovic, Jovan D., Jackson, Joseph, Mehra, Raman
Technical Paper
A Methodology for Systems Integration in Aircraft Conceptual Design - Estimation of Required Space2013-01-223509/17/2013
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
Technical Paper
From Airframer Requirements to Detailed Technical Specification of Electromechanical Actuators Aided by Knowledge-Based Methods2013-01-216309/17/2013
Recent trends towards lighter and more efficient commercial aircraft have motivated airframers to consider the use of electromechanical actuators EMA as the primary means of power for aircraft flight control systems. The transition from state-of-the-art hydraulic actuation to new electromechanical technologies poses a great challenge to both airframers and system suppliers for the correct and complete definition of new requirements. Transient effects such as electric motor overheating and inertial loads, previously not present or irrelevant for hydraulic actuators, now have to be taken into account. A knowledge-based environment containing design drivers for electromechanical components is combined with a validation method in order to aid the systems engineer to accomplish such task. This approach offers the potential to guarantee that all requirements are covered by a new technology, and that they are complete and consistent. In addition, analyzing representative mission profiles and
Arriola, David, Reysset, Aurelien, Budinger, Marc, Thielecke, Frank, Mare, Jean-Charles
Technical Paper
Cold Gas Systems, Missile or Projectiles Design, Installation, Tests and Requirements ForARP1625B (Current)06/05/2013
Systems shall be classified in terms of type, category and class.
A-6A2 Military Aircraft Committee
Recommended Practice
Ship Systems and Equipment - Hydraulic Systems - Noise ControlJ1782_201305 (Current)05/31/2013
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
Information Report
Determination of Costs and Benefits from Implementing an Engine Health Management SystemARP4176 (Historical)02/05/2013
This ARP provides an insight into how to approach a cost benefit analysis (CBA) to determine the return on investment (ROI) that would result from implementing a propulsion Prognostics and Health Management (PHM) system on an air vehicle. It 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 PHM systems but want to either quantify or understand the economic benefits (i.e., the value proposition) that a PHM system could provide.
E-32 Aerospace Propulsion Systems Health Management
Recommended Practice
8000 psi Hydraulic Systems: Experience and Test ResultsAIR4002A (Current)11/15/2012
Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.
A-6A2 Military Aircraft Committee
Information Report
Fault Detection and Isolation for Electro-Mechanical Actuators Using a Data-Driven Bayesian Classification2012-01-221510/22/2012
This research investigates a novel data-driven approach to condition monitoring of Electrical-Mechanical Actuators (EMAs) consisting of feature extraction and fault classification. The approach is designed to accommodate varying loads and speeds since EMAs typically operate under non-steady conditions. Since many common faults in rotating machinery produce unique frequency components, the approach is based on signal analysis in the frequency domain of both inherent EMA signals and accelerometers. The feature extraction process exposes fault frequencies in the signal data that are synchronous with motor position through a series of signal processing techniques consisting of digital re-sampling to the position domain, Power Spectral Density (PSD) computation to the frequency domain, and feature reduction. The reduced dimension feature is then used to determine the condition of the EMA with a trained Bayesian Classifier. Signal data collected from EMAs in known health configurations is
Chirico, Anthony, Kolodziej, Jason R.
Journal Article
Energy Optimized Aircraft: What is it and how do we make one?2012-01-217910/22/2012
Efforts are underway to develop technologies to create a more Energy Optimized Aircraft (EOA). The question becomes how should one define an Energy Optimized Aircraft and how should energy optimization be measured to determine what is optimal? This paper provides a top level point of view for the goal of an Energy Optimized Aircraft. It outlines how one should approach the design of such an aircraft, the relevant vehicle systems technologies to enable energy optimization for fighter aircraft, and potential aircraft level measurands for determining degrees of goodness associated with incorporating different technologies. The top-to-bottom approach is provided for traceability of technologies being developed to aircraft and mission level goals.
Griggs, Steven C., Iden, Steven Mark, Lamm, Peter T.
Journal Article
Autonomous Electrical Power System for Multi Role Transport Tanker Aircraft2012-01-219210/22/2012
Today's civil airliners integrate electrical power capability properly sized to supply the growing demands of modern aircraft systems, that are more electrical than ever. The conversion of civil aircraft into a military derivative aircraft faces the challenge of rearranging the available generation capability to feed the new power-hungry military systems while at the same time minimizing the impact on certification of the base aircraft for use on civil operations. This challenge is particularly difficult when the new military systems demand high peak power consumption, as in the case of the conversion of a civil airliner into a military Multi-Role Transport Tanker aircraft with high performance multipoint refueling capabilities. In fact the selection of the type of actuation (either electrical or hydraulic) for the refueling systems is heavily conditioned by the excess of either electrical or hydraulic power available in the base aircraft. The A330MRTT Multirole Transport Tanker from
Fernandez-Garcia, F.Javier, Valdeolmos, Javier
Technical Paper
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
Knowles, Jeff
Technical Paper
Airbus - EMAs for Flight Controls Actuation System - An Important Step Achieved in 201111VATC4040003/21/2012
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
Todeschi, Michel
Video
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
Information Report
Challenges for Health Monitoring of Electromechanical Flight Control Actuation Systems2011-01-270110/18/2011
Flight control systems of civil aircraft have undergone huge developments in the last decades. The current more/ all electric aircraft concepts lead to the replacement of the hydraulic actuators in the primary flight control systems by electromechanical systems. Integrating electromechanical systems in safety critical applications implies three main challenges: (a) the detection of all fault cases which could lead to a safety critical state, (b) finding measurement parameters capable to detect faults, and (c) the development of algorithms to detect faults under all flight conditions. Putting the scope on the health monitoring of the mechanical components of a direct drive actuator, a new technology based on piezoresistive thin film sensors (TFS) is presented and its potential shown by using defective ball bearings as an example.
Wagner, Hannes, Nikolov, Galin, Bierig, Andreas, Spangenberg, Holger
Journal Article
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
Todeschi, Michel
Technical Paper
EMA Aileron COVADIS Development2011-01-272910/18/2011
In the frame of the COVADIS project (flight control with distributed intelligence and systems integration) supported by the DPAC and where Airbus and Sagem are partners, an electromechanical actuator (EMA) developed and produced by Sagem (SAFRAN group) flew for the first time in January 2011 as an aileron primary flight control of the Airbus A320 flight test Aircraft. With this new type of actuator, in the scope of the preparation of the future Airbus Aircraft, the perspectives of using EMA technologies for the flight control systems is an important potential enabler in the more electrical aircraft. The paper deals with the development phase of this actuator from the definition phase up to the flight tests campaign. It is focused on : COVADIS project context (flight control with distributed intelligence and systems integration), The challenges of the definition phase, Test results presentation (ground and flight).
Derrien, Jean-Claude, Tieys, Pierre, Senegas, David, Todeschi, Michel
Technical Paper
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