Browse Topic: Air data computers

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IAQG-03282025-1 IAQG-03282025-1 (Current)04/02/2025
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
Air Data Computer – Minimum Performance StandardAS8002B (Current)04/28/2020
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)04/28/2020
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)02/20/2020
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-0000209/03/2019
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
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)09/04/2018
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-2793912/01/2017
Airborne Elastic Backscatter and Raman Polychromator for Ash DetectionTBMG-2619201/01/2017
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)07/18/2016
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-2484606/01/2016
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)05/24/2016
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 Operations2015-01-245809/15/2015
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)08/08/2015
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
Guide to Temperature Monitoring in Aircraft Gas Turbine EnginesAIR1900A (Current)05/01/2014
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-1912502/01/2014
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-1878512/01/2013
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 Systems2013-01-223309/17/2013
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 System2013-01-225709/17/2013
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 (Current)01/16/2013
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-1264701/01/2012
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
FLIGHT TEST PROCEDURES FOR STATIC PRESSURE SYSTEMS INSTALLED IN SUBSONIC TRANSPORT AIRCRAFTARP921 (Historical)08/10/2011
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
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)02/16/2008
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)02/16/2008
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)02/16/2008
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
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
Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators2006-01-241408/30/2006
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
Fault Detection and Isolation in Attitude and Heading Reference Systems For Fly-By-Wire Control System For General Aviation Aircraft2006-01-241508/30/2006
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
Motion-Based Flight Simulator Usage for F-35 Control Law Development2005-01-318010/03/2005
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.
Pressure Altimeter SystemsAS8009B (Historical)09/21/2005
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
Tomorrow's reality in defense electronicsAEROMAR05_0303/01/2005
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)01/28/2005
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
A History of Ice Protection System Development at Sikorsky Aircraft2003-01-209206/16/2003
Modern rotorcraft must have the capability to operate in all-weather conditions. Sikorsky Aircraft has conducted icing research and ice protection system development for helicopters over the past 58 years and the pace of that work has accelerated during the past two decades. Sikorsky participated in several helicopter icing flight tests, conducted wind tunnel tests of scale models and full-scale components, tested simulated ice shapes, and developed analytical tools for use in the design, certification, and qualification for flight in icing conditions. Engine inlets, airspeed systems, main rotor droop stops, and windshields are generally protected by thermal anti-icing systems. When rotor ice protection is required, rotors are protected with electrothermal deice systems. The UH-60A BLACK HAWK electrothermal rotor ice protection system, developed in the late 1970s, has been installed in 2400 H-60 helicopters and it remains one of the most effective rotor ice protection systems. This
Flemming, Robert J.
Assessment of the Dynamic Stability Characteristics of the Bell Model M427 Helicopter Using Parameter Estimation Technology2002-01-291611/05/2002
A joint program between Bell Helicopter Textron Canada and the Flight Research Laboratory of Canada's National Research Council was initiated to address the aerodynamic modelling challenges of the Bell M427 helicopter. The primary objective was to use the NRC parameter estimation technique, based on modified maximum likelihood estimation (MMLE), on a limited set of flight test data to efficiently develop an accurate forward-flight mathematical model of the Bell M427. The effect of main rotor design changes on the aircraft stability characteristics was also investigated, using parameter estimation. This program has demonstrated the feasibility of creating a forward-flight rotorcraft aerodynamic mathematical model based on time-domain parameter estimation, and the ability of a 6 degree-of-freedom MMLE model to accurately document the impact of minor rotor modifications on aircraft stability.
Hui, Kenneth, Ricciardi, Joseph, Srinivasan, Ramesh, Lambert, Edward, Sarafian, Ara
AIRBORNE COMPUTER HIGH SPEED DATA LOADERARINC615-4_ER2 (Current)05/06/2002
This standard provides general and specific guidance for the development of a Portable Data Loader (PDL) for carry-on application and an Airborne Data Loader (ADL) for on-board the airplane. It specifies use of a 3.5 inch floppy disk to upload and download of data and operational programs using an ARINC 429 data bus connected to avionics computers.
Airlines Electronic Engineering Committee
562 Terrain Awareness and Warning System (TAWS) - AnalogARINC562 (Current)12/01/2001
Terrain Awareness and Warning System (TAWS) Analog addresses the need for standard TAWS installations in older aircraft that have analog equipment interfaces. The analog unit is intended as a replacement for ARINC Characteristic 594: Ground Proximity Warning System (GPWS) equipment. The document is intended to compliment ARINC Characteristic 762: Terrain Awareness and Warning System (TAWS) for later model aircraft having digital equipment interfaces.
Airlines Electronic Engineering Committee
Advanced Real-time Aerodynamic Model Identification Technique2001-01-296509/11/2001
The Flight Research Laboratory (FRL), National Research Council (NRC) of Canada is currently developing an in-flight aircraft aerodynamic model identification technique that determines the small perturbation model at a given test condition. Initial demonstrations have been carried out using the NRC Falcon 20 research aircraft. An efficient system architecture, in terms of both software algorithms and hardware processing, has been designed to meet the stringent near real-time requirements of an in-flight system. As well, novel hardware and software techniques are being applied to the calibration and measurement of the fundamental in-flight parameters, such as air data. The small perturbation models are then combined to develop a global model of the aircraft that is validated by comparing the model response to flight data. The maneuvers were performed according to the FAA Acceptance Test Guide (ATG). In-flight model development and validation is an innovative application of parameter
Hui, Kenneth, Swail, Carl, Leach, Barrie
Unusual Attitude Recovery Using the Roll Arrow2001-01-300909/11/2001
As part of the NASA High Speed Research program, an unusual attitude (UA), pilot-in-the-loop simulation study provided information on Primary Flight Display (PFD) symbology factors that affect UA recovery. Overall research objectives were to evaluate symbology concepts to facilitate pilot perception and safe recovery. It was concluded that UA recognition and recovery task performance is unacceptable when the pilot relies only on raw data but is improved markedly with appropriate second-generation symbology. The major result indicated that a newly-developed PFD symbol (the Roll Arrow) significantly reduced UA recognition errors. The Roll Arrow is a large, red arrow attached to the PFD Bank Angle Pointer. When the aircraft is in a UA, the Roll Arrow appears on the PFD and points left or right to indicate the required direction to roll for recovery. Other recovery actions are at pilot discretion. In comparison to other evaluated symbology designs, the Roll Arrow was associated with 90
Gershzohn, Gary
AIR DATA AND INERTIAL REFERENCE SYSTEM (ADIRS)ARINC738A-1 (Current)07/31/2001
This standard sets forth characteristics for a 4 MCU integrated digital ADIRS intended for installation in subsonic commercial transport aircraft. It is envisioned that the ADIRS will incorporate the capabilities of both an air data system and an inertial reference system.
Airlines Electronic Engineering Committee
GUIDANCE FOR TOOL AND TEST EQUIPMENT (TTE) EQUIVALENCYARINC738-3 (Current)07/01/2001
This standard defines an integrated ADIRS that provides air data information and directional guidance information for cockpit display. The ADIRS consists of up to three Air Data/Inertial Reference Units (ADIRUs) located in the aircraft electronic rack, an associated Control and Display Unit (CDU) and remotely mounted Air Data Modules (ADMs).
Airlines Electronic Engineering Committee
Initial Evaluation of CDTI/ADS-B for Commercial Carriers: CAA's Ohio Valley Operational Evaluation2000-01-552010/10/2000
Flight activities during the Cargo Airline Association's Ohio Valley Operations Evaluation (OpEval) were focused on near-term Cockpit Display of Traffic Information (CDTI) applications. Seven CDTI applications were ranked from highest to lowest priority, and the first two, Enhanced Visual Acquisition for “See & Avoid”, and Enhanced Visual Approaches, were evaluated during OpEval. Five other applications were demonstrated. For the Enhanced Visual Acquisition and Enhanced Visual Approach applications, a detailed, comprehensive operational concept document was prepared. The operational concept and the associated CDTI requirements were tested during OpEval. Both pilots and controllers reported that the CDTI augmented the visual acquisition and visual approach tasks and improved pilot awareness of surrounding traffic. Additionally, the results suggest operational performance benefits in the form of enhanced spacing awareness and a potential reduction in the misidentification of aircraft
Battiste, Vernol, Ashford, Rose, Olmos, Baltazar Oscar
704A Inertial Reference System (IRS)ARINC704A (Current)03/26/1999
This standard defines a 4 MCU IRS, consisting of inertial measuring devices and associated electronics specifically designed for installation in commercial transport type aircraft. It may be used in place of ARINC 704 Inertial Reference Systems. This system additionally provides capability to be interfaced to an ARINC 743A GNSS Sensor, to enhance the accuracy of the inertially derived navigation data.
Airlines Electronic Engineering Committee
The Feasibility of Using an INS for Control System Feedbacks98551709/28/1998
It has been suggested that the conventional air data probes used on modern high performance aircraft can be eliminated by exploiting the capabilities of the Inertial Navigation System (INS) and obtaining analytic estimates of angle-of-attack (α), sideslip angle (β), and possibly of dynamic pressure (q). The reasons for wanting to eliminate the probes are that they are vulnerable to ground handling damage, bird strikes, icing, and hostile action in the case of combat aircraft. To determine the feasibility of this approach, three methods for obtaining α and β estimates from INS information were programmed into a nonlinear simulation of a relaxed stability aircraft which requires a high level of artificial stability augmentation through its flight control system. It was found that none of the three methods provided satisfactory stabilizing feedbacks to the control system when the subject aircraft was disturbed by severe atmospheric turbulence. This was due to the inability of the INS to
Colgren, Richard D.
Flight Testing a Modern Flight Control System97552010/01/1997
With the increasing complexity of modern combat aircraft flight control systems, the flight trials phase of an aircraft development programme has become much more of an aircraft and systems model validaition exercise. This requires a highly integrated ground and flight test programme with accurate models of the aircraft and its systems and new analysis techniques to enable rapid and effective validation of these models. This paper describes recent experience at British Aerospace Warton on a number of aircraft programmes which has resulted in the development of effective real lime analysis techniques. These techniques provide the ability to perform in-flight model validation and are currently being used in the EF2000 development programme at Warton.
Smith, Terry D.
Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control SystemsARP5107 (Historical)06/01/1997
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
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