Search Results

Standard

Fluidic Technology

2007-01-11

HISTORICAL

ARP993C

The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.

Standard

Fluidic Technology

2012-05-31

CURRENT

ARP993D

The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.

Standard

FLUIDIC TECHNOLOGY

1995-06-01

HISTORICAL

ARP993B

The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.

Standard

Primary Flight Control Hydraulic Actuation System Interface Definition

2015-10-19

CURRENT

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.

Standard

Primary Flight Control Hydraulic Actuation System Interface Definition

2008-07-16

HISTORICAL

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.

Standard

Utility System Characterization, An Overview

2021-02-23

WIP

AIR5428A

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.

Standard

Aerospace Fly-by-Light Actuation Systems

2007-01-11

HISTORICAL

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.

Standard

Aerospace Fly-by-Light Actuation Systems

2014-12-18

CURRENT

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.

Standard

AEROSPACE FLUID POWER AND CONTROL/ACTUATION SYSTEM GLOSSARY

1985-10-01

HISTORICAL

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.

Standard

Power Sources for Fluidic Controls

2012-05-31

CURRENT

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.

Standard

Power Sources for Fluidic Controls

2007-01-11

HISTORICAL

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.

Standard

POWER SOURCES FOR FLUIDIC CONTROLS

1991-11-01

HISTORICAL

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.

Standard

Utility System Characterization, an Overview

2013-05-28

CURRENT

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.

Standard

Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business Aircraft

2018-10-15

CURRENT

ARP6252

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

Standard

TERMINAL SHANK-SWAGING, DIMENSIONS FOR

1999-08-01

HISTORICAL

AS10081

Standard

Aerospace Active Inceptor Systems for Aircraft Flight and Engine Controls

2018-07-24

CURRENT

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: 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.

Standard

Aircraft Flight Control Actuation System Failure-Detection Methods

2022-12-16

CURRENT

AIR5273A

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.

Standard

Actuation System Failure Detection Methods

2007-01-11

HISTORICAL

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.

Standard

Aircraft Flight Control Systems Descriptions

2022-10-05

WIP

AIR4094B

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.

Standard

DESCRIPTION OF ACTUATION SYSTEMS FOR AIRCRAFT WITH FLY-BY-WIRE FLIGHT CONTROL SYSTEMS

1999-05-01

HISTORICAL

AIR4253

This AIR provides a description of representative state-of-the-art, fly-by-wire (FBW) actuation systems used in flight control systems of 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 future 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.