Browse Topic: Flight control actuators
This aerospace recommended practice provides a framework and suggested procedures or values for requirements for the design, performance, and test of hydraulically powered servoactuators for use in aircraft flight control systems. The original version of this document was intended for military usage: consequently, the requirements still often reflect such use. However, the basic requirements of this ARP may and should be applicable to commercial usage as well, provided that appropriate considerations are given for the applicable FAR/JAR 25 regulations, hydraulic fluids, and environmental conditions
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
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
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
This SAE Aerospace Recommended Practice (ARP) defines impulse test procedures that are recommended for hydraulic components
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
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
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
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
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
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
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
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
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
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
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
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
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
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
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
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
Systems shall be classified in terms of type, category and class
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
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
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
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
This specification covers the design and installation requirements for Types I and II military aircraft hydraulic systems
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
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
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
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