Browse Topic: Air data computers

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Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924B (Current)11/26/2025
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category
E-36 Electronic Engine Controls Committee
Static System Error Compensation in Air Data Calibration for Tiltrotor System CertificationF-0081-2025-01285/20/2025
Air data measurement and calibration are fundamental components in the pursuit of accurate and reliable aerodynamic assessments. The systematic collection of essential data regarding air properties are important for evaluating aircraft performance under various conditions and configurations. The scope is to achieve a comprehensive understanding of airflow characteristics, which is fundamental for design improvements and operational strategies, contributing to safer and more efficient flight operations in a several range of scenarios. This type of data measurement is even more challenging for the AW609 Tiltrotor which combines vertical take-off technology capabilities with the fixed-wing flight efficiency. The activity starts from known pitot-static system calibration methodologies for conventional applications and shows what were the difficulties encountered in a non-conventional Tiltrotor approach. The paper goes through the presentation of the original Pitot-Static and Air Data
Evangelista, Marco, Mori, Massimiliano
IAQG-03282025-1 IAQG-03282025-1 (Current)4/2/2025
IAQG-03282025-1
IAQG-1 Standards Committee
Flight Test Procedures for Static Pressure Systems Installed in Subsonic Transport AircraftARP921B (Current)12/22/2020
This SAE Aerospace Recommended Practice (ARP) covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
DATALINK GROUND SYSTEMS STANDARD AND INTERFACE SPECIFICATION (DGSS/IS)ARINC620-10 (Current)7/31/2020
ARINC Specification 620 defines the interfaces between the Datalink Service Provider (DSP) and the aircraft, other ground-based datalink services, and users. The datalink ground system standard definition supports traditional ACARS and AOA protocols, as well as Media Independent Aircraft Messaging (MIAM) as defined by ARINC Specification 841. MIAM messages can be much larger than ACARS messages (5 MB versus 3.3 kB per message). Supplement 10 improves Controller-Pilot Data Link Communications (CPDLC) by defining a “Deliver By (DB)” period that allows the DSP, that originated the message, to intercept and discard the message if it is not delivered by the specified time. Supplement 10 also adds a Media Advisory code for ACARS over IP (AoIP) indicating that an ACARS non Safety Services messages is being transferred over IP links. New Reason Codes are assigned for un-transmittable or undeliverable messages. ACARS Character set clarifications are also provided in Supplement 10.
Airlines Electronic Engineering Committee
Air Data Computer – Minimum Performance StandardAS8002B (Current)4/28/2020
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary and/or standby flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Over-speed Warning Total Air Temperature
A-4 Air Data Subcommittee
Air Data Computer – Minimum Performance StandardAS8002B-TEST-REC (Historical)4/28/2020
This SAE Aerospace Standard (AS) covers air data computer equipment (hereinafter designated the computer) which when connected to sources of aircraft electrical power, static pressure, total pressure, outside air temperature, and others specified by the manufacturer (singly or in combination) provides some or all of the following computed air data output signals (in analog and/or digital form) which may supply primary and/or standby flight instruments: Pressure Altitude Pressure Altitude, Baro-Corrected Vertical Speed Calibrated Airspeed Mach Number Maximum Allowable Airspeed Over-speed Warning Total Air Temperature
A-4 Air Data Subcommittee
Barometry for Altimeter CalibrationAIR1075B (Current)2/20/2020
This SAE Aerospace Information Report (AIR) is concerned only with aspects directly relating to available accuracy. While well-designed photoelectric, inductive or capacitive readers and pressure regulators, and other accessories are highly desirable for convenience and production rate, they are considered to be outside the scope of this AIR.
A-4 Aircraft Instruments Committee
Collins Aerospace provides avionics for C-130H modernization programSAE-MA-000029/3/2019
The Lockheed C-130H Hercules fleet operated by the Air National Guard and U.S. Air Force Reserve is getting new Collins Aerospace Systems avionics that will help extend the life of the legacy aircraft by 20 years.
Kucinski, William
Analysis and Automated Detection of Ice Crystal Icing Conditions Using Geostationary Satellite Datasets and In Situ Ice Water Content Measurements2019-01-19536/10/2019
Recent studies have found that high mass concentrations of ice particles in regions of deep convective storms can adversely impact aircraft engine and air probe (e.g. pitot tube and air temperature) performance. Radar reflectivity in these regions suggests that they are safe for aircraft penetration, yet high ice water content (HIWC) is still encountered. The aviation weather community seeks additional remote sensing methods for delineating where ice particle (or crystal) icing conditions are likely to occur, including products derived from geostationary (GEO) satellite imagery that is now available in near-real time at increasingly high spatio-temporal detail from the global GEO satellite constellation. A recent study using a large sample of co-located GEO satellite and in-situ isokinetic evaporator probe (IKP-2) total water content (TWC) datasets found that optically thick clouds with tops near to or above the tropopause in close proximity (≤ 40 km) to convective updrafts were most
Bedka, Kristopher, Yost, Christopher, Nguyen, Louis, Strapp, J. Walter, Ratvasky, Thomas, Khlopenkov, Konstantin, Scarino, Benjamin, Bhatt, Rajendra, Spangenberg, Douglas, Palikonda, Rabindra
A Research on the Icing Flight Test and Computational Simulation for the Design of Ice Protection System for KUH (Korean Utility Helicopter)F-0075-2019-147385/13/2019
Icing of the fuselage and blades may occur when the helicopter is flying in the icing area. If ice accretion occurs in the ADS(Air Data System) of the fuselage, normal speed and altitude information are lost, making it difficult to flight. When windshield icing occurs, the view of pilot is limited and flight is difficult. Also, the ice accretion of the blades deforms the outer shape of the blades (Ref. 1) and makes the dynamic characteristics unstable due to an abnormal weight increase, resulting in deterioration of performance, deterioration of maneuverability, and structural instability. To avoid this, an anti-icing or de-icing system is required. Therefore, if the aircraft is not fitted with a proper anti-icing system, it is not possible to operate under icing conditions. However, it is difficult to design a proper anti-icing system considering the position of anti-icing protection area and icing phenomenon due to limitation of electric power, weight, thermal damage temperature
Park, Nameun, Kim, Jik, Lee, Sang, Woo, Cheol, Kim, Hyung, Hwang, Yoo
An Integrated Approach to Model Based Engineering with SysML, AADL and FACE2018-01-194210/30/2018
Multiple model-based engineering (MBE) frameworks have emerged to cover the many requirements for the engineering of avionics systems: from early requirement capture to the final system and embedded software generation, through refinement and V&V activities. In this paper, we consider the SysML, AADL and FACE standards. They are promoted by different standardization bodies, with different objectives. We note they are often seen as competitive, while we argue it is the opposite: there is a potential for a synergistic coupling. To date, no complete open evaluation on the feasibility of such capability has been done. In this paper, we present one workflow that illustrates the joint use of SysML, AADL and FACE. We consider a basic flight control system to exercise the proposed process and gateways between the three notations. We use SCADE Architect by ANSYS that supports the three notations in a unified workbench to illustrate refinement scenarios from one notation to another, then
Zhe, Wang, Hugues, Jerome, Chaudemar, Jean-Charles, LeSergent, Thierry
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107C (Current)9/4/2018
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Engine Control (FADEC) systems. The TLD concept is one wherein a fault-tolerant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects
E-36 Electronic Engine Controls Committee
New Products & Services: December 2017 Aerospace Manufacturing & FabricationTBMG-2793912/1/2017
Airborne Elastic Backscatter and Raman Polychromator for Ash DetectionTBMG-261921/1/2017
Volcanic ash is a significant hazard to aircraft engines and electronics. It has caused damage to unwary aircraft and disrupted air travel for thousands of travelers, costing millions of dollars. The small, jagged fragments of rocks, minerals, and volcanic glass that constitute volcanic ash are about the size of sand and silt. Volcanic ash is hard, does not dissolve in water, is extremely abrasive and corrosive, and conducts electricity when wet. The upper winds transport the particles away to eventual dispersal in an ash cloud. Ash clouds typically form above 20,000 feet, but the lower limit of the initial cloud depends on both the height of the volcanic vent and the vigor with which material is ejected from it.
Aircraft Flight Control Systems DescriptionsAIR4094A (Current)7/18/2016
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.
A-6A3 Flight Control and Vehicle Management Systems Cmt
Airborne Elastic Backscatter and Raman Polychromator for Ash DetectionTBMG-248466/1/2016
Volcanic ash is a significant hazard to aircraft engine and electronics. It has caused damage to unwary aircraft and disrupted air travel for thousands of travelers, costing millions of dollars. The small, jagged fragments of rocks, minerals, and volcanic glass that constitute volcanic ash are about the size of sand and silt. Volcanic ash is hard, does not dissolve in water, is extremely abrasive and corrosive, and conducts electricity when wet. The upper winds transport the particles away to eventual dispersal in an ash cloud. Ash clouds typically form above 20,000 feet, but the lower limit of the initial cloud depends on both the height of the volcanic vent and the vigor with which material is ejected from it.
Pressure Altimeter SystemsAS8009C (Current)5/24/2016
This SAE Aerospace Standard (AS) specifies minimum performance requirements for pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. This document does not address RVSM requirements because general RVSM requirements cannot be independently detailed at the component level. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to mechanical type
A-4 Air Data Subcommittee
Descriptions of Systems Integration Test Rigs (Iron Birds) For Aerospace ApplicationsAIR5992 (Current)10/16/2015
This Aerospace Information Report (AIR) provides information on systems integration rigs, commonly referred to as “Iron Birds” for aerospace applications. a 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. b 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. c It includes recommendations for simulation, component development tests, system integration and lessons learned.
A-6A3 Flight Control and Vehicle Management Systems Cmt
FMS and AFCS Interface for 4D Trajectory Operations2015-01-24589/15/2015
The future revolution of the air traffic system imposes the development of a new class of Flight Management Systems (FMS), capable of providing the aircraft with real-time reference flight parameters, necessary to fly the aircraft through a predefined sequence of waypoints, while minimizing fuel consumption, noise and pollution emissions. The main goal is to guarantee safety operations while reducing the aircraft environmental impact, according to the main international research programs. This policy is expected to affect also the Unmanned Aerial Systems (UASs), as soon as they will be allowed to fly beyond the restricted portions of the aerospace where they are currently confined. In the future, in fact, UASs are expected to fly within the whole civilian airspace, under the same requirements deriving from the adoption of the Performance Based Navigation (PBN). For UASs, the most attractive strategy to reach this goal consists in adopting the mature technology developed for the civil
Sirigu, Giuseppe, Battipede, Manuela, Gili, Piero, Cassaro, Mario
Minimum Performance Standard for Pitot and Pitot-Static ProbesAS8006A (Current)8/8/2015
This SAE Aerospace Standard (AS) covers the following basic types: Type I - Pitot pressure, straight and L-shaped, electrically heated. Type II - Pitot and static pressures, straight and L-shaped, electrically heated.
A-4 Air Data Subcommittee
Wireless Sensing - Future's Password to Digital Avionics System2014-01-21329/16/2014
Performance of Avionics systems is dictated by the timely availability and usage of critical health parameters. Various sensors are extensively used to acquire and communicate the desired parameters. In today's scenario, sensors are hardwired. The number of sensors is growing due to automation which increases the accuracy of intended Aircraft functions. Sensors are distributed all over the Aircraft and they are connected through wired network for signal processing and communication. LRUs (Line Replaceable Unit) which are integrating various sensors also use a wired approach for communication. The use of a wired network approach poses challenges in terms of cable routing, stray capacitances, noise, mechanical structure and added weight to the structure. The weight of cables contributes significantly to the overall weight of the aircraft. As the weight of Aircraft increases, the required fuel quantity also increases. The Key driver for Airline operational cost is fuel. Fuel quantity is a
Vadgaonkar, Prashant, Janardhan, Ullas, Sivaramasastry, Adishesha
Embedded COTS - A Gateway for New Processors/High Performing Machines to Digital Avionics System Industry2014-01-22069/16/2014
Today's digital avionics systems leverage the use of the Embedded COTS (Commercial Off The Shelf) hardware to fit the need of small form factor, low power, reduced time to market and reduced development time with efficient use of DO-254 for compliance of product. COTS modules are entering in digital avionics systems such as COM (Computer On Module)/SOM (System On Module)/SIP (System In Package) with huge advancement in semiconductor and packaging industry. In today's scenario COTS are very useful for DAL (Development Assurance Level) C and below as the efforts on compliance for DAL A and B are huge. This paper proposes to use these for DAL A and B as well, where one can get enormous benefit on efforts of compliance and time to market. This paper makes an attempt to explain the current scenario of the Embedded COTS usage in Avionics Systems. This paper also brings the study of the selection process of Embedded COTS along with the important selection parameters, constraints, challenges
Vadgaonkar, Prashant
Guide to Temperature Monitoring in Aircraft Gas Turbine EnginesAIR1900A (Current)5/1/2014
This SAE Aerospace Information Report (AIR) provides an overview of temperature measurement for engine monitoring systems in various areas of aircraft gas turbine engines while focusing on current usage and methods, systems, selection criteria, and types of hardware. This document emphasizes temperature monitoring for diagnostics and condition monitoring purposes.
E-32 Aerospace Propulsion Systems Health Management
Tom Flatley, Computer Engineer, Goddard Space Flight Center, Greenbelt, MDTBMG-191252/1/2014
Tom Flatley, computer engineer and current head of the Science Data Processing Branch at Goddard Space Flight Center, leads a group of engineers and programmers in their development of flight and ground-based science data processing systems and applications, including SpaceCube, CubeSats/SmallSats, modeling/simulation/visualization, and other technologies.
Air-Data System Detects Aircraft IcingTBMG-1878512/1/2013
Michigan Aerospace Corporation (MAC) has begun work on a Phase I Small Business Innovation Research (SBIR) contract with NASA’s Langley Research Center. The contract, “RIDES: Raman Icing Detection System,” extends MAC’s present aircraft-based optical airdata system technology — which uses ultraviolet laser light to measure air speed, direction, temperature, and density — to also detect conditions aloft when ice is likely to form, enabling a multi-hazard sensing capability.
Small Airplane Considerations for the Guidelines for Development of Civil Aircraft and Systems2013-01-22339/17/2013
On September 30, 2011, certification authorities released Advisory Circular 20-174[1], Development of Civil Aircraft and Systems, which recognizes the Society of Automotive Engineers (SAE) Aerospace Recommended Practice (ARP) 4754A and the European equivalent ED-79A [2], in order to address “the concern of possible development errors due to the ever increasing complexity of modern aircraft and systems.” ARP4754A/ED-79A describes a process of development assurance which helps reduce the risk of design errors in the development of aircraft systems. This process is necessary for complex systems not easily comprehended by deterministic analyses or tests. This ARP was developed “in the context of Title 14 of the Code of Federal Regulations (14 CFR) part 25,” a category which includes complex systems such as full fly-by-wire flight controls. However, this paper shows that such systems are the exception to most, recent civil airplane designs. Of new airplanes designed in the last 10 years
Voros, Robert E.
Multi-Axis Serially Redundant, Single Channel, Multi-Path FBW Flight Control System2013-01-22579/17/2013
A multi-axis serially redundant, single channel, multi-path FBW (FBW) control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands from the primary flight control computer, and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands in accordance with the control law algorithms implemented in the flight control
Lin, Shu, Smith, Tim, De Serres, Pierre
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924A (Historical)1/16/2013
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category
E-36 Electronic Engine Controls Committee
SOFIA Closed- and Open-Door Aerodynamic AnalysesTBMG-126471/1/2012
Work to evaluate the aerodynamic characteristics and the cavity acoustic environment of the SOFIA (Stratospheric Observatory for Infrared Astronomy) airplane has been completed. The airplane has been evaluated in its closed-door configuration, as well as several open-door configurations (see figure). Work performed included: acoustic analysis tool development, cavity acoustic evaluation, stability and control parameter estimation, air data calibration, and external flow evaluation.
Holistic Granular Programming: A Novel Approach for Modeling Aircraft2011-01-276410/18/2011
Description of work-in-progress design candidates during the pre-concept and conceptual aircraft design stages have traditionally followed protocol compatible with the later, more mature phases of contemporary product development, i.e. preliminary and detailed design. Up to this moment in time there has been a natural, intuitive tendency to approach design description using geometry as the initial basis upon which all analysis and design refinement could proceed. Design and integration, whether kinematic or structural (static) systems, and irrespective of applications, should be treated as a holistic problem with functionality as opposed to geometric description of a physically tangible artifact being the first step in product definition. This paper presents a coherent, logical method of describing an aircraft concept using functionality as a basis. Hereafter known as Holistic Granular Programming (HGP), any collection of assemblies and components can be described mathematically, and
Isikveren, Askin T., Ziemer, Sven, Stenz, Gernot, Hornung, Mirko
An Overview of the V&V of Flight-Critical Systems Effort at NASA2011-01-256010/18/2011
As the US is getting ready for the Next Generation (NextGen) of Air Traffic System, there is a growing concern that the current techniques for verification and validation will not be adequate for the changes to come. The JPDO (in charge of implementing NextGen) has given NASA a mandate to address the problem and it resulted in the formulation of the V&V of Flight-Critical Systems effort. This research effort is divided into four themes: argument-based safety assurance, distributed systems, authority and autonomy, and, software intensive systems. This paper presents an overview of the technologies that will address the problem.
Brat, Guillaume
FLIGHT TEST PROCEDURES FOR STATIC PRESSURE SYSTEMS INSTALLED IN SUBSONIC TRANSPORT AIRCRAFTARP921 (Historical)8/10/2011
This Aerospace Recommended Practice covers the test procedures and equipment for performing flight testing on pitot-static systems installed in subsonic transport type aircraft.
A-4 Aircraft Instruments Committee
Challenges in Validating Safety-Critical Embedded Systems2009-01-328411/10/2009
The embedded software has played an increasing role in safety-critical systems. At the same time the current development process of “build, then integrate” has proven unaffordable for the Aerospace industry. This paper outlines challenges in safety-critical embedded systems in addressing system-level faults that are currently discovered late in the development life cycle. We then discuss an architecture-centric approach to model-based engineering, i.e., to complement the validation of systems with analysis of different operational quality aspects from an architecture model. A key technology in this approach is the Architecture Analysis & Design Language (AADL), an SAE International standard for embedded software system. It supports analysis of operational qualities such as responsiveness, safety-criticality, security, and reliability through model annotations. A number of industry initiatives have been underway to demonstrate the feasibility of using this technology in industrial
Feiler, Peter H.
Method and System for Making a Fuel-tank Inert without an Inert Gas2009-01-313411/10/2009
In Chemistry “Inert” implies ‘not readily reactive with other elements; forming few or no chemical compounds or something that is not chemically active’. “Inerting” is the process that renders a substance inert. A method for making a fuel-tank inert without the use of an inert gas is described. In this method fuel-air ratio of ullage is reduced until it becomes inert. The method does not discharge fuel vapors as an inert gas inerting system. Two systems employing the method are described explaining their pros and cons. Advantages of the method over Nitrogen Enriched Air (NEA) inerting method with an On-board Inert Gas Generating System (OBIGGS) are discussed. Patent application on the method and system is pending.
Gupta, Alankar
Remote Servoed Air Data Instruments for Subsonic AircraftAS791 (Current)2/16/2008
This standard provides minimum performance criteria for air data instruments intended to provide cockpit indication of: a Indicated airspeed (Vi) b Computer airspeed (Vc) c True airspeed (Vt) d Equivalent airspeed (Ve) e Mach number (M) f Altitude (H) g Vertical speed (Hpr) h Maximum operating limit speed (Vmo) i True angle of attack (αt) j Free air temperature (Tfat) k Total temperature (Tt) These functions shall be derived from a central air data computer (AS 417) and through system wiring applied to the respective indicator.
A-4 Aircraft Instruments Committee
MINIMUM SAFE PERFORMANCE OVER SPEED WARNING INSTRUMENTSAS8007 (Current)2/16/2008
This AS defines instruments which use inputs of static and pitot pressure equal to those which are utilized to establish the pressure altitude and speed of that aircraft. These pressures are applied to the instrument ports to provide means for generation of an aural warning whenever the aircraft reaches or exceeds the maximum operating limit speed. This Over Speed Warning Instrument function may be incorporated as part of an Air Data Computer, or an Air Speed Indicator, or an Air Speed/Mach Number Indicator, or other instruments. In those cases where the Over Speed Warning Instrument is part of another instrument, the standards contained herein apply only to the Over Speed Warning Instrument function. Each aircraft type and model has a defined maximum operating limit speed curve or curves which are a part of the airframe manufacturer's type certification approval data; this limit speed data shall be available from the subject airframe manufacturer as published in the operating manual
A-4 Air Data Subcommittee
Air Data Computers, MPSAS417A (Current)2/16/2008
This Standard covers air data equipment (hereinafter designated the instrument) which when connected to sources of aircraft electrical power, static pressure, total pressure and outside air temperature (singly or in combination) provides some or all of the following computed air data output signals: Pressure Altitude* Total Temperature* Pressure Altitude (Reporting) Altitude Rate Baro-Corrected Pressure Altitude* Overspeed Warning Vertical Speed* Altitude Hold Computed Airspeed* Airspeed Hold Mach Number* Mach Hold Maximum Allowable Airspeed* qc (impact pressure) Static Air Temperature (*when used as an alternate for total temperature) True Airspeed Others
A-4 Aircraft Instruments Committee
FLIGHT DECK PANELS, CONTROLS, AND DISPLAYSARP4102 (Current)7/10/2007
This document recommends criteria for the design, installation and operation of panels, controls, and displays on the flight deck of transport aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107B (Historical)11/15/2006
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Electronic Control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or
E-36 Electronic Engine Controls Committee
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107B-TEST-REC (Historical)11/15/2006
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Electronic Control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or
E-36 Electronic Engine Controls Committee
Fault Detection and Isolation in Attitude and Heading Reference Systems For Fly-By-Wire Control System For General Aviation Aircraft2006-01-24158/30/2006
The article presents problems of fault detection and isolation in AHRS systems for the Fly-By-Wire control system for general aviation. The system is currently being designed at the Rzeszów University of Technology. The idea of the system is to create a general aviation pilot-friendly aircraft. The FBW control system is equipped with three AHRSs. Their diagnostics is realized on three levels. The article describes hardware redundancy and software redundancy for AHRS systems and then shows how to use it for diagnostics. The article focuses especially on estimation techniques applied in research. For simulations data from flight tests were used.
Kopecki, Grzegorz, Dolega, Boguslaw
Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators2006-01-24148/30/2006
This paper presents tests of Electromechanical Actuators (EMA) designed in the Department of Avionics and Control at the Rzeszow University of Technology. Also, the architecture of the laboratory stand as well as testing methods and obtained results are described. Furthermore, the paper discusses the in-flight test results of the complete set of servos installed as a part of the experimental Fly-By-Wire (FBW) control system on board of the PZL-110 “Koliber” aircraft.
Rzucidlo, Pawel
Motion-Based Flight Simulator Usage for F-35 Control Law Development2005-01-318010/3/2005
Real-time simulation is an integral part of the Vehicle Systems and Mission Systems design and risk reduction processes for the three variants of the Joint Strike Fighter (JSF), or F-35, aircraft-Conventional Take-Off and Landing (CTOL), Short Take-Off and Vertical Landing (STOVL), and Carrier Variant (CV). The JSF Program is relying on increased use of modeling and simulation to reduce verification cost and schedule. The F-35 Lockheed Martin/Northrop Grumman/BAE SYSTEMS team utilizes the unique motion capabilities of the NASA Ames Vertical Motion Simulator (VMS) for control law and pilot-vehicle interface design maturation and evaluation. The first in a series of motion-based tests was conducted in February and March 2004 to (1) evaluate flying qualities characteristics where high-fidelity motion is most beneficial, (2) identify design solutions for stressing, land-based and shipboard landings, and (3) mature STOVL control laws. Complex hardware and software were successfully
Tallant, Sibille U.
A Simple Analytical Redundancy Method for Pitch and Bank Angles Estimation2005-01-336210/3/2005
The article presents the idea of Pitch and Bank Angles estimation with the use of incomplete measurement information. This idea is applied in Attitude and Heading Reference Systems used in the Fly-By-Wire control system for a general aviation aircraft. The idea of the Fly-By-Wire control system for a general aviation aircraft designed in the Department of Avionics and Control Systems is presented in brief. For estimations Lunenberger observers were used. Simulation results are based on the flight test data.
Kopecki, Grzegorz, Tomczyk, Andrzej
Pressure Altimeter SystemsAS8009B (Historical)9/21/2005
This SAE Aerospace Standard (AS) specifies minimum performance requirements for primary pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components. The test procedures specified herein apply specifically to analog type instruments. Digital instruments or automatic test instrumentation may require other test procedures. Such differing procedures shall be
A-4 Air Data Subcommittee
Super-sized rigAEROJUN05_016/1/2005
Goodrich has unveiled the world's largest landing gear test facility, lending credence to the notion that bigger sometimes can be better. During the public unveiling of a new 400,000-ft2 landing gear test facility in Oakville, Ontario, Canada, Goodrich Chairman, President, and CEO Marshall Larsen not only discussed his company's diverse product line but also placed great emphasis on its long-term relationship with European aircraft manufacturer Airbus. “Today's event is a very proud moment for Goodrich, and marks another milestone in the development of our relationship with Airbus,” Larsen said. “The A380 [has] a myriad of Goodrich products onboard.”
Newton, Matthew
Tomorrow's reality in defense electronicsAEROMAR05_033/1/2005
SAE 100 Future look: From space-based satellite communications systems to rifles equipped with laser and thermal imaging sights, electronics has integrated itself as a core ingredient of contemporary warfare. During the next quarter-century, Forecast International believes that the fields of communications, intelligence, computers, avionics, radars, lasers, electro-optical systems, and sensors will leap forward so dramatically that today's most advanced systems will seem prehistoric by comparison. Only a few decades ago, the high level of sophistication of today's defense electronics systems existed only in the realm of science fiction. In 1959, Robert Heinlein wrote the novel Starship Troopers that described infantry soldiers outfitted with computers, communications, optics, and sensor systems that gave them superiority over the enemy in battle by providing them with information while on the move. This story has practically become the blueprint for the future, as several major systems
Sterk, Richard
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107A (Historical)1/28/2005
This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of Time Limited Dispatch (TLD) to the thrust control reliability of Full Authority Digital Electronic Control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or
E-36 Electronic Engine Controls Committee
GNSS NAVIGATION AND LANDING UNIT (GNLU)ARINC756-3 (Current)2/27/2004
This standard describes the function of the GNLU, capable of providing enroute/terminal navigation, non-precision approach, and precision approach capabilities. The GNLS consists of a GNLU, associated controls and displays, antenna, and interfaces to other aircraft systems.
Airlines Electronic Engineering Committee
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