Browse Topic: Flight control actuators
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 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 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 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.
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
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.
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 SAE Aerospace Standard (AS) provides general requirements for components that are used in commercial aircraft hydraulic systems. It also includes the FAR/JAR/CS 25 regulations that apply to hydraulic components. It is to be used in conjunction with a Procurement Specification for each component. 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 information on distribution elements such as hoses, pipe couplings and general tubing.
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
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 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.
This SAE Aerospace Information Report (AIR) provides the hydraulic system designer with the various design options and techniques currently available to enhance the survivability of hydraulic systems. A comprehensive knowledge of the hostile environment to which the air vehicle will be exposed will form the basis upon which the overall design philosophy is formulated. The designer should strive to achieve at the absolute minimum a system which provides the actuation and control capability to meet the minimum acceptable flying quality level to complete the operational mission for which the aircraft is designed; i.e., the aircraft can be controlled and the mission terminated safely, including landing. This AIR will attempt to address the following threats: a Typical Small Arms Fire (5.56, 7.62, 12.7 and 14.5 mm AP) b Cannon (20, 30, and 40 mm API/HEI) c NBC/EMI/EMP/Beamed Particle d Chemical/Biological Protection against missiles is beyond the scope of this AIR. Except for electronic
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.
This SAE Aerospace Recommended Practice (ARP) establishes the minimum requirements and procedures for impulse testing of aerospace hydraulic actuators, valves, pressure containers, and similar fluid system components, for use in aerospace hydraulic systems; for exceptions, see paragraph 9.1. This ARP also refers to standard impulse test equipment, which may be used in conducting these impulse tests.
This SAE Aerospace Recommended Practice (ARP) establishes the factors which should be considered in the design and installation of a hydraulic system fitted to a commercial transport rotorcraft.
Systems shall be classified in terms of type, category and class.
This SAE Aerospace Information Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which aerospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices.
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 Recommended Practice (ARP) establishes the factors which should be considered in the design and installation of a hydraulic system fitted to a commercial transport rotorcraft.
This Aerospace Information Report (AIR) supplies information on the flight control systems incorporated on various 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.
Hydraulic and pneumatic systems are used on marine vehicles for steering, vehicle control and utility services. System components that generate and transmit noise are of concern. Noise of prime movers and lift systems is beyond the scope of this report.
This specification establishes general design, performance, and test requirements for hydraulically powered servoactuators when used in aircraft flight control systems.
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.
This Aerospace Recommended Practice (ARP) establishes the requirements and the procedures for impulse testing of actuators, valves and pressure containers for use in aerospace hydraulic systems. It also refers to standard impulse test equipment which may be used in conducting these impulse tests.
This ARP presents definitions of terminology used in conjunction with redundant flight control systems. No details of specific redundant system design approaches are given. Likewise, no recommendations are included for system performance and design requirements. Redundancy may be provided within individual components of a flight control system, or it may be used for the system in total. The scope of this ARP is sufficiently broad to include both of these extremes.
The recommendations of this bulletin apply to commercial type multi-engine transport aircraft.
The recommendations of this bulletin apply to conventional commercial type multi-engine transport aircraft.
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