Search Results

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 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.

Modern air vehicles consist of many subsystems, traditionally managed as a federation of independent subsystems. Advances in control technologies, digital electronics and electro-mechanical hardware, provide potential opportunities to integrate subsystems for future aircraft. This document does not define any particular integration strategy. Its purpose is to provide information about traditional federated subsystems from the functional, control, resource, and hardware perspective. To be able to integrate subsystems, one must have a basic understanding of the subsystems, and this document provides an introduction or starting point for initiating the integration process.

General terms peculiar to aerospace fluid power and control systems are defined in this glossary. Relevant terms have been excerpted from the referenced documents and included herein from the aerospace terms felt to be most useful to the ISO. This is a systems document and the only component-related terms are those significant at the systems level.

This SAE Aerospace Information Report (AIR) outlines comprehensive aircraft flight control system fault isolation methodology that has proven to be effective. The methodology presented in this Information Report has been used in several successful fault isolation efforts on military aircraft.

This SAE Aerospace Information Report (AIR) outlines comprehensive aircraft flight control system fault isolation methodology that has proven to be effective. The methodology presented in this Information Report has been used in several successful fault isolation efforts on military aircraft.

Modern air vehicles consist of many subsystems, traditionally managed as a federation of independent subsystems. Advances in control technologies, digital electronics and electro-mechanical hardware, provide potential opportunities to integrate subsystems for future aircraft. This document does not define any particular integration strategy. Its purpose is to provide information about traditional federated subsystems from the functional, control, resource, and hardware perspective. To be able to integrate subsystems, one must have a basic understanding of the subsystems, and this document provides an introduction or starting point for initiating the integration process. The focus is on the aircraft subsystems, which includes utility, flight and propulsion control (e.g., electric power, environmental control subsystem (ECS), fuel, etc.) The depth of the information intends to provide an introduction to the subsystems.

This SAE Aerospace Recommended Practice (ARP) provides a process for the verification and validation of monitors used in highly-integrated and complex aircraft flight control and related systems.

This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft. This ARP addresses the following: The functions to be implemented The mechanical interconnection between captain and F/O station The geometric and mechanical characteristics The mechanical, electrical, and electronic interfaces The safety and certification requirements

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.

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.

The purpose of this document is to develop the general characteristics and requirements for feel-force control systems for active cockpit controllers, also known as Active Inceptors. The document presents technical material that describes the recommended key characteristics and design considerations for these types of systems. Where appropriate, the effects of platform specific requirements (e.g., single axis/dual axis, single seat/dual seat, civil/military, rotorcraft/fixed wing aircraft, etc.) are clearly identified. The material developed will serve as a reference guide for: a Aircraft prime contractors who want to understand active cockpit controller technology and develop their own set of requirements; b Suppliers that develop active cockpit controller equipment and; c Regulatory Authorities who will be involved in the certification of these types of systems.

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 AIR provides descriptions of aircraft actuation system failure-detection methods. The methods are those used for ground and in-flight detection of failures in electrohydraulic actuation systems for primary flight control. The AIR concentrates on full Fly-By-Wire (FBW) flight control actuation though it includes one augmented-control system. The background to the subject is discussed in terms of the impact that factors such as the system architecture have on the detection methods chosen for the flight control system. The types of failure covered by each monitoring technique are listed and discussed in general. The way in which these techniques have evolved is illustrated with an historical review of the methods adopted for a series of aircraft, arranged approximately in design chronological order.

This document provides a description of a process for development of fly-by-wire actuation systems. Included are (1) the development of requirements for the servo-actuator hardware and the electronics hardware and software, (2) actuator and servo-electronics interface definitions and, (3) the required communications and interactions between the servo-actuator and the servo-electronics designers.

This document provides a description of a process for development of fly-by-wire actuation systems. Included are (1) the development of requirements for the servo-actuator hardware and the electronics hardware and software, (2) actuator and servo-electronics interface definitions and, (3) the required communications and interactions between the servo-actuator and the servo-electronics designers.

The scope of this SAE Aerospace Recommended Practice (ARP) covers acquisition of flight test data for use in developing a statistical data base of aerospace vehicle flight control surface actuator duty cycle. The statistical data base is intended for use in establishing industry guidelines and procurement specification requirements for actuator displacement duty cycle. The objective of this ARP is to provide a uniform method for the aerospace industry to collect flight control displacement type duty cycle data during demonstration and full scale development of new aircraft or during development testing of new models of existing aircraft.

This SAE Aerospace Recommended Practice (ARP) provides an algorithm aimed to analyse flight control surface actuator movements with the objective to generate duty cycle data applicable to hydraulic actuator dynamic seals. This algorithm can be used to process digitally recorded actuator positions, generated either by pure simulation, or hardware-in-the-loop simulation, or flight test of full scale demonstrator of new aircraft, of new aircraft models in development, or of in-service aircraft, depending on what is available at different stages of the aircraft development and the purpose of the duty cycle investigation. This generated duty cycle data can be used as a basis for defining dynamic seal life requirements, dynamic seal life testing, or to assess the impact of control law or other changes to dynamic seal behavior.

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 Recommended Practice (ARP) provides guidelines for the configuration and design of mechanical control signal transmission systems and subsystems. It is focused on the recommended practices for designing cable and pulley, pushrod and bellcrank and push-pull flexible cable control systems. These systems are typically used in some combination to transmit pilot commands into primary, secondary and utility control system commands (mechanical or electrical) or aircraft surface commands. On mechanically controlled aircraft, most pilot control commands are initiated through cockpit mounted wheels, sticks, levers, pedals or cranks that are coupled by pushrods or links to cable systems. The cable systems are routed throughout the aircraft and terminated in close proximity to the commanded surface or function where cranks and pushrods are again used to control the commanded function.