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Viewing 1 to 30 of 45
2013-05-05
WIP Standard
AIR5273A
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 a historical review of the methods adopted for a series of aircraft, arranged approximately in design chronological order.
2013-03-11
WIP Standard
ARP6252
This Aerospace Recommended Practice (ARP) provides general requirements for a generic rudder and brakes pedal unit that could be used for Fly by Wire transport and business aircraft. It addresses the following: • The functions to be implemented • The geometric and mechanical characteristics • The mechanical and electrical interfaces • The safety and certification requirements
2017-03-22
WIP Standard
ARP6389
This ARP provides guidelines for improving the Failure Mode and Effect Analysis process, including alternative or additional methods, for flight critical actuation equipment electronics and software.
2015-10-07
WIP Standard
ARP4895B
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.
2007-10-13
WIP Standard
ARP5775
The document shall provide: - Guideline for specifying requirements for skew and disconnect solutions for High Lift Systems. - A structure for hazard assessment - A check list for the fulfillment of the structural and monitoring certification requirements - Examples of prior industry approaches
2017-04-11
WIP Standard
AIR6920
This AIR is for use by OEM's and Suppliers developing process gate checklists for highly integrated, complex flight control and vehicle management systems to support the life cycle development validation and verification activities prescribed by ARP4754.
CURRENT
2005-06-28
Standard
ARP5007A
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.
CURRENT
2012-05-31
Standard
ARP993D
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
CURRENT
2014-12-18
Standard
AIR4982A
This SAE Aerospace Information Report (AIR) has been prepared to provide information regarding options for optical control of fluid power actuation devices. It is not intended to establish standards for optical fluid power control, but rather is intended to provide a baseline or foundation from which standards can be developed. It presents and discusses approaches for command and communication with the actuation device via electro-optic means. The development of standards will require industry wide participation and cooperation to ensure interface commonality, reliability, and early reduction to practice. To facilitate such participation, this document provides potential users of the technology a balanced consensus on its present state of development, the prospects for demonstration of production readiness, and a discussion of problem areas within this technology.
CURRENT
2015-10-19
Standard
AIR4922A
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.
HISTORICAL
1997-06-01
Standard
ARP5007
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.
HISTORICAL
1994-02-01
Standard
ARP4895
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.
CURRENT
2006-05-17
Standard
ARP4895A
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.
HISTORICAL
1995-06-01
Standard
ARP993
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology. The purpose of this document is to promote the use of a common terminology and useful symbols and to encourage users and manufacturers of fluidic devices and systems to conform to meaningful standards of performance. This document is intended for use as the basis for a procurement specification for fluidic devices and systems when the need for such a specification arises. This document shall be the starting point for future SAE documents, either through revision or addition, in the field of fluidics as such documents become necessary.
HISTORICAL
1969-02-01
Standard
ARP993A
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology. The purpose of this document is to promote the use of a common terminology and useful symbols and to encourage users and manufacturers of fluidic devices and systems to conform to meaningful standards of performance. This document is intended for use as the basis for a procurement specification for fluidic devices and systems when the need for such a specification arises. This document shall be the starting point for future SAE documents, either through revision or addition, in the field of fluidics as such documents become necessary.
HISTORICAL
1995-06-01
Standard
ARP993B
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
HISTORICAL
2001-06-01
Standard
ARP993C
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
HISTORICAL
1999-03-01
Standard
AIR4982
This SAE Aerospace Information Report (AIR) has been prepared to provide information regarding options for optical control of fluid power actuation devices. It is not intended to establish standards for optical fluid power control, but rather is intended to provide a baseline or foundation from which standards can be developed. It presents and discusses approaches for command and communication with the actuation device via electro-optic means. The development of standards will require industry wide participation and cooperation to ensure interface commonality, reliability, and early reduction to practice. To facilitate such participation, this document provides potential users of the technology a balanced consensus on its present state of development, the prospects for demonstration of production readiness, and a discussion of problem areas within this technology.
HISTORICAL
1985-10-01
Standard
AIR1916
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.
CURRENT
2001-12-20
Standard
AIR5273
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.
CURRENT
2000-09-01
Standard
AIR5428
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.
CURRENT
2002-12-16
Standard
ARP1254
HISTORICAL
1973-06-01
Standard
AIR1245
This AIR concerns itself with the end use of Fluidic (or Flueric) control hardware on aerospace vehicle applications. The fluidic control hardware application is viewed as a system comprised of the following subsystems: Power Source Power Conditioner Fluidic/Flueric Control(s) This AIR identifies potential power sources and relates the design of the fluidic/flueric controls to the nature of both the power source and, as required, the power conditioner. In the unlikely event that the power source yields a fluid which is always at the desired pressure level, temperature range and flow rate capacity and, further, is free of particulate or liquid contaminate, pressure pulsation, etc., no power conditioner is required. Experience has shown that the power conditioner is usually necessary to assure operability and reliability of the total control system.
CURRENT
2012-05-31
Standard
AIR1245B
This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.
HISTORICAL
1995-07-01
Standard
AIR1245A
This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.
HISTORICAL
1996-10-01
Standard
AIR4922
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.
CURRENT
2009-11-20
Standard
AIR5992
This Aerospace Information Report (AIR) provides information on systems integration rigs, commonly referred to as “Iron Birds” for aerospace applications. 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. 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. It includes recommendations for simulation, component development tests, system integration and lessons learned.
CURRENT
2013-02-10
Standard
ARP5764
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: Aircraft prime contractors who want to understand active cockpit controller technology and develop their own set of requirements; Suppliers that develop active cockpit controller equipment and; Regulatory Authorities who will be involved in the certification of these types of systems.
CURRENT
2012-11-01
Standard
ARP5770
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.
Viewing 1 to 30 of 45