Browse Topic: Commercial aircraft

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AIR120425-1AIR120425-1 (Current)12/04/2025
AIR120425-1
A-10 Aircraft Oxygen Equipment Committee
Measurement of Exterior Noise Produced by Aircraft Auxiliary Power Units (APUs) and Associated Aircraft Systems During Ground OperationARP1307C (Current)11/26/2025
Test procedures are described for measuring noise at specific receiver locations (passenger and cargo doors, and servicing positions) and for conducting general noise surveys around aircraft. Procedures are also described for measuring noise level and directivity at noise source locations to facilitate the understanding and interpretation of the data. Requirements are identified with respect to instrumentation; acoustic and atmospheric environment; data acquisition, reduction and presentation, and such other information as is needed for reporting the results. This document makes no provision for predicting APU or component noise from basic engine characteristics or design parameters, nor for measuring noise of more than one aircraft operating at the same time. No attempt is made to suggest acceptable levels of noise or suitable subjective criteria for judging acceptability. ICAO Annex 16 Volume I Attachment C provides guidance on recommended maximum noise levels.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
Nitrogen Absorption/Desorption (Gas Dissolution) in Aircraft Shock AbsorbersAIR6942 (Current)11/26/2025
This document outlines the current state of the art in the understanding of gas in solution in shock absorber oils in unseperated shock absorbers. A literature review, overview of Henry's law, Henry's law coefficients for known gas and oil couples, in-service operational problems, lessons learned, and potential future work will be discussed in the document.
A-5B Gears, Struts and Couplings CommitteeNEW
Development and Qualification of Composite Landing GearsAIR5552A (Current)11/26/2025
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402B (Current)11/26/2025
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a. Single engine personal and/or liaison type b. Light twin engine c. Large multiengine propeller d. Large multiengine turbojet e. Military high performance fighter and attack f. Helicopter which are subject to the following CFR Parts certification: Part 23 – Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Aircrafts Part 25 – Airworthiness Standards: Transport Category Aircrafts Part 27 – Airworthiness Standards: Normal Category Rotorcraft Part 29 – Airworthiness Standards: Transport Category Rotorcraft
A-20B Exterior Lighting Committee
Fuel Flowmeters and IndicatorsAS407E (Current)11/26/2025
To specify minimum requirements for Fuel Flowmeters for use primarily in reciprocating engine powered civil transport aircraft, the operation of which may subject the instruments to the environmental conditions specified in Section 3.3. This Aeronautical Standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines as follows: TYPE I - Measure rate of flow of fuel used. TYPE II - Totalize amount of fuel consumed or remaining.
AS407 Fuel Flowmeters
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
Standardized composite training programAIR6671 (Current)11/26/2025
SAE CACRC has produced several standards, each representing the best-practice, recommended minimum training syllabus for the aforementioned target groups. The purpose of this document is to promote the use of these SAE standards, particularly for developing training programs for employee training, qualification in airlines and maintenance organizations, and as reference in regulatory guidance material. It summarizes, as a quick reference, the content of each training document and its relation to and interaction with other training documents. Thereby it allows users to select the appropriate training documents and syllabi to establish a comprehensive, sequential training program build-up customized to the specific needs of the aforementioned functions (see figure). This document does not intend to introduce new training content/syllabus.
AMS CACRC Commercial Aircraft Composite Repair Committee
Aerospace - Test Methodology for Electrohydrostatic ActuatorsARP5879A (Current)11/26/2025
This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators. In the discussion of the tests and test
A-6B2 Electrohydrostatic Actuation Committee
Electrohydrostatic Actuation Applications on Aircraft ProgramsAIR6353 (Current)11/26/2025
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
A-6B2 Electrohydrostatic Actuation Committee
Guidelines for Specifying LVDTs and RVDTsARP5554 (Current)11/26/2025
As per Committee/Henry E. Harschburger recommendations
A-6B1 Hydraulic Servo Actuation Committee
Aerospace - Lightning Effects on Hydraulic Transport Elements on AircraftAIR6185A (Current)11/26/2025
<p>This SAE Aerospace Information Report (AIR) describes hydraulic system design and installation to minimize the effects of lightning, especially when the aircraft structure is composite. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed.</p>
My new committee for commercial aircrafts
Verifying large alternate product code for an AIR document - AIR112425-1AIR1124250000000000000000/NEW1--1 (Current)11/24/2025
Verifying large alternate product code for an AIR document
A-10 Aircraft Oxygen Equipment Committee
Extraordinary and Special Purpose Landing Gear SystemsAIR4846B (Current)11/11/2025
A landing gear system comprises the most compelling assembly of engineering skills. Its importance to the successful design of an aircraft can be favorably compared with that of the aircraft's wings and engines. A landing gear system consists of several different engineering disciplines, and is continually in the public eye especially with regard to safety. The primary objective of AIR4846 is to present a record of a variety of interesting gears, gear/aircraft systems and patents, and to discuss wherever possible the lessons learned, and the reasons for the design. Thus, the document is not only a historical account, but a means of recording technical knowledge for the practical benefit of future landing gear designers. Commendable efforts have been made over the years by several individuals to make such recordings, and AIR4846 will make continual reference to them. This applies to all books, papers, or specifications that have the approval of the SAE A 5 Committee. AIR4846 also
A-5B Gears, Struts and Couplings CommitteeNEW
Landing Gear Component Heat DamageAIR5913B (Current)11/11/2025
The purpose of this report is to outline types of in-service heat damage that have been observed in high strength steel landing gear components, with an emphasis on a particular type that is referred to as “Ladder Cracking” which can develop in landing gear shock struts. The report discusses how ladder cracking can be detected visually and evaluated by non-destructive inspection methods, and how it can be repaired at overhaul with the prior approval of the Original Equipment Manufacturer. This report also describes the use of a bearing material that has resolved this problem without introducing other problems. Examples of other types of service induced heat damage are also discussed.
A-5B Gears, Struts and Couplings CommitteeNEW
Sponsor ChjangeARP050911 (Current)10/13/2025
Test
A-6A Systems Subsystem Integration Steering Group
Minimum Standard for Portable Gaseous, Oxygen EquipmentAS1046D (Current)09/29/2025
This standard is intended to apply to portable compressed gaseous oxygen equipment. When properly configured, this equipment is used either for the administration of supplemental oxygen, first aid oxygen or smoke protection to one or more occupants of either private or commercial transport aircraft.
A-10 Aircraft Oxygen Equipment Committee
Noise Reduction in High-Speed Sonic Under expanded jets using Slanted Perforated Tabs2025-01-003205/05/2023
Studies on High-Speed Jet control is of prime importance to aerospace as well as related industries. Proper mixing of Jet of a fuel with the surrounding air is indispensable in the combustion chamber of a propulsive system, this contributes to the need of enhancing mixing of Jet with ambient air. The noise radiated by a jet engine is also a major problem for many cities around the world and this method also reduces the Jet associated noise which is of immense environmental concern for transport aircrafts. The High-speed Jet control is achieved by using two different methods. They are active Control method and passive control method. In active control method, the idea is to introduce stream wise vortices into the mixing layer of the jet. Passive control of the jet can be achieved by adding geometrical modifications. The present study deals with an innovative passive control of jet using slanted perforated tabs. which focuses on the method of changing the structures in turbulent free
R, Asad Ahmed, SUBRAMANIAN, THANIGAIARASU
Numerical Drag and Lift Predictions of Transport Aircrafts2022-26-118605/26/2022
Accurate estimation of drag and lift during take-off/landing and flight of an aircraft is critical in improving its performance. The flow separation and aerodynamic forces estimation using a CFD simulation are very sensitive to numerical methods, types of grid, turbulence models and other numerical treatments. In this paper, results from the simulations of two aircraft models using a RANS based CFD software, SimericsMP+ are presented. One set of simulations are performed on a DLR-F6 model at conditions of 0.75 Mach number and 3.0e6 Reynolds number as provided in the 2nd AIAA CFD Drag Prediction Workshop. The flow behavior over a range of angle of attack during the flight condition at transonic speed is simulated for Wing Body Nacelle Pylon (WBNP) configuration of DLR-F6 model. The second set of simulations are performed on JAXA high-lift configuration Standard Model (JSM) with nacelle-off configuration. These simulations are performed for high-lift conditions of 0.172 Mach number and
Godavarthi, Raghu Vamsee, Wang, Junfeng, Maiti, Dipak
Application Guide for Aerospace Hydraulic MotorsARP4940A (Current)11/09/2021
This SAE Aerospace Recommended Practice (ARP) is an application guide for fixed and variable displacement hydraulic motors. It provides details of the characteristics of fixed and variable displacement hydraulic motors, architectures, circuit designs, controls, and typical applications. The applications include airborne and defense vehicles with emphasis on high performance applications.
A-6C4 Power Sources Committee
Aircraft Brake Temperature MonitoringARP6812 (Current)10/28/2021
This SAE Aerospace Recommended Practice (ARP) provides recommendations for the function, design, construction, and testing of an on-aircraft Brake Temperature Monitoring System (BTMS), sometimes referred to as a Brake Temperature Indication System (BTIS). NOTE: This ARP does not address: Cockpit ergonomics and Aircraft operating procedures. Various handheld methods of temperature sensing or readouts, as these are not associated with transport aircraft during normal operation. Temperature sensitive paints as a means to indicate exceedance of a landing gear axle temperature threshold due to brake temperature.
A-5A Wheels, Brakes and Skid Controls Committee
Research on Locked Wheel Protection Function of Aircraft Brake System2021-01-126910/11/2021
Locked wheel protection is an important part of antiskid control for aircraft brake control system. Locked wheel protection compares the wheel speed of two or more wheels, if one of the wheels is too slow, locked wheel protection releases the brake pressure on the slow wheel. This work aims to study the control logic for locked wheel protection. Locked wheel protection control logic consists of 3 key factors: paired wheels, active threshold and inhibit velocity. Focus on comparison different options of these 3 factors, all aspects of control logic for locked wheel protection had been expounded in this study. Simulation and calculation analysis is applied for different locked wheel strategies to evaluate the effect. One conclusion is that the greatest wheel speed of the wheel under control shall be set as a reference speed for locked wheel protection. This study provide the basis to design a proper locked wheel protection function of aircraft brake control system.
Li, Bing, Dong, Jin, Xiao, Peng, Meng, Qingtang
Aircraft Ground Service Connections Locations and TypeARP4084B (Current)09/30/2021
The purpose of this SAE Aerospace Recommended Practice (ARP) is to standardize locations of aircraft ground service connections to accommodate the trend toward fixed systems, which use the passenger boarding bridge and/or underground “pop-up” or pit systems as a source of utilities. It must be recognized that, in standardizing the locations of the aircraft service connections, they must continue to be served efficiently in those instances where mobile ground support equipment is used. There is an ever increasing number of fixed installations for aircraft servicing. The objectives to be met by standardizing the locations of the aircraft service connections are the following:
AGE-3 Aircraft Ground Support Equipment Committee
Ramp MarkingsARP5910A (Current)09/30/2021
This SAE Aerospace Recommended Practice (ARP) outlines recommended ramp pavement marking standards for proper guidance and positioning of GSE on commercial transport aircraft parking and handling stands (gates), in line with International Civil Aviation (ICAO) recommendations applicable to airport aprons. Throughout this document, the minimum essential criteria are identified by use of the key word “shall”. Recommended criteria are identified by use of the key word “should” and, while not mandatory, are considered to be of primary importance in providing safety effective ramp markings. Deviation from recommended criteria should only occur after careful consideration and thorough service evaluation have shown alternate methods to provide an equivalent level of safety.
AGE-3 Aircraft Ground Support Equipment Committee
Aircraft Maintenance Jacks - General RequirementsAS4775B (Current)09/30/2021
This document covers the general requirements for hydraulic aircraft jacks. It can be applied to tripod, unipod, and axle jacks that may be used on open ramp areas as well as in the aircraft hangar. Throughout this Aerospace Standard, the minimum essential criteria are identified by the key word “shall”. Recommended criteria are identified by use of the key word “should”. Deviation from recommended criteria should only occur after careful consideration and thorough service evaluation have shown alternate methods to provide an equivalent level of safety. The term “vertical load” throughout this Aerospace Standard is defined as the force imposed on the aircraft jack at the airframe jack point.
AGE-3 Aircraft Ground Support Equipment Committee
115/200 Volt, 400 Hz Aircraft External Electrical Power Connector Contact Maintenance ProceduresAIR4365B (Current)09/30/2021
This SAE Aerospace Information Report (AIR) describes procedures for use in the field to determine if 115/200 Volt, 400 Hz aircraft external electrical power connectors are excessively worn, which may result in the inability of the external power plug to be retained, intermittent electrical performance and arcing.
AGE-3 Aircraft Ground Support Equipment Committee
Carbon Fiber Fabric and Epoxy Resin Wet Lay-Up Repair Material Part 5 - Carbon Fiber Fabrics, Plain Weave, 193 g/m2, and Epoxy ResinAMS2980/5A (Current)09/24/2021
This Material Specification defines the requirements of carbon fiber fabric and epoxy resin systems used for wet lay-up repair of carbon fiber reinforced epoxy structures, qualified according to AMS2980/1 and AMS2980/2. Unless otherwise specified by the drawing, the order or the inspection schedule, the present specification shall be used in conjunction with the referenced documents.
AMS CACRC Commercial Aircraft Composite Repair Committee
Minimum Operational and Maintenance Responsibilities for Aircraft Tire UsageARP5265C (Current)09/20/2021
This SAE Aerospace Recommended Practice (ARP) sets forth criteria for the installation, inflation, inspection, and maintenance of aircraft tires and the maintenance of the operating environment to ensure the safety of support personnel and the safe operation of the aircraft.
A-5C Aircraft Tires Committee
Minimum Operational and Maintenance Responsibilities for Aircraft Tire UsageARP5265C-TEST-REC (Historical)09/20/2021
This SAE Aerospace Recommended Practice (ARP) sets forth criteria for the installation, inflation, inspection, and maintenance of aircraft tires and the maintenance of the operating environment to ensure the safety of support personnel and the safe operation of the aircraft.
A-5C Aircraft Tires Committee
TitleSAE-PP-0041809/13/2021
Abstract
Jackson, Alyssa, Jackson, Alyssa, SintzUSER, Jeneane, SintzUSER, Jeneane, Jackson, Alyssa, Jackson, Alyssa, SintzUSER, Jeneane, SintzUSER, Jeneane
Convenient Location of Oxygen Masks for Both the Crew and Passengers of AircraftAIR1390A (Historical)08/10/2021
There are four basic conditions requiring the dispensing of oxygen through oxygen masks to aircraft occupants in turbine powered aircraft during flight. The following conditions are derived from the Federal Aviation Regulations (FAR) as listed in Section 2.
A-10 Aircraft Oxygen Equipment Committee
Location of Crew and Passenger Oxygen Masks, Portable Oxygen System, and Protective Breathing EquipmentARP6390 (Current)08/10/2021
Various emergency situations may require the dispensing of oxygen to all occupants of aircraft during flight. During an emergency event, depending on the aircraft operational flight capability, all cabin occupants must be serviced by a mask presentation system connected to an operational oxygen source. Several regulations specify the functional characteristics and requirements of the oxygen systems for aircraft in support of different missions. These should be referred to for the exact functional performance requirements. It is not the intent of this document to ensure conformance with these regulations, but only to recommend general concepts for the location of the oxygen masks and oxygen system outlets for proper accessibility by the aircraft occupants, whether cabin occupants or crew members. Different requirements may apply when the mission of the pressurized aircraft or the operational altitude of the aircraft is not in excess of FL250. When the aircraft is operating above FL100
A-10 Aircraft Oxygen Equipment Committee
TIMELY RECOVERY OF FLIGHT DATA (TRFD)ARINC681 (Current)08/06/2021
The difficulty in locating crash sites has prompted international efforts for alternatives to quickly recover flight data. This document describes the technical requirements and architectural options for the Timely Recovery of Flight Data (TRFD) in commercial aircraft. ICAO and individual Civil Aviation Authorities (CAAs) levy these requirements. The ICAO Standards and Recommended Practices (SARPs) and CAA regulations cover both aircraft-level and on-ground systems. This report also documents additional system-level requirements derived from the evaluation of ICAO, CAA, and relevant industry documents and potential TRFD system architectures. It describes two TRFD architectures in the context of a common architectural framework and identifies requirements. This report also discusses implementation recommendations from an airplane-level perspective.
Airlines Electronic Engineering Committee
Aircraft Indicating Systems Optical PerformanceARP1088C (Current)06/01/2021
This ARP is intended to cover the warning, caution, and advisory indicating system required for commercial and military aerospace vehicles.
A-20A Crew Station Lighting Committee
Safety Considerations of Carry-On Baggage Relating to the Emergency Evacuation of Transport Category AircraftARP4072A (Current)05/20/2021
This SAE Aerospace Recommended Practice (ARP) provides information and recommended guidelines for handling carry-on baggage prior to emergencies and during the emergency evacuation of transport category aircraft. Recommendations are provided on limiting the size, amount, and weight of carry-on baggage brought into the cabin, improved stowage of carry-on baggage to minimize hazards to passengers in flight and during emergency evacuations, and procedures to ensure carry-on baggage is not removed during an emergency evacuation.
S-9B Cabin Interiors and Furnishings Committee
DRYING OF THERMOSETTING COMPOSITE MATERIALSARP4977 (Current)05/14/2021
This SAE Aerospace Recommended Practice (ARP) describes standard methods for drying commercial aircraft composite structures prior to repair and gives general guidelines on use and applicability. It addresses the removal of liquids that have collected inside the structures through open damage, microcracks, or porosity and the removal of absorbed moisture from the composite material. The methods described in this document shall only be used when specified in an approved repair document or with the agreement of the original equipment manufacturer (OEM) or regulatory authority. If this document is used for the drying of materials other than thermosetting composite materials, the fitness for this purpose must be determined by the user.
AMS CACRC Commercial Aircraft Composite Repair Committee
Landing Gear AlignmentAIR5556 (Current)04/23/2021
The purpose of this Aerospace Information Report is to provide the industry with methodologies for measuring tire/wheel gear alignment and the range of acceptable alignment settings for various types of non-military landing gear. This AIR will focus on the general aviation, corporate, and regional aircraft landing gear but could have applicability to commercial aircraft.
A-5 Aerospace Landing Gear Systems Committee
Capacitive Fuel Gauging System AccuraciesAIR1184B (Current)04/23/2021
This report is intended to identify the various errors typically encountered in capacitance fuel quantity measurement systems. In addition to identification of error sources, it describes the basic factors which cause the errors. When coupled with appraisals of the relative costs of minimizing the errors, this knowledge will furnish a tool with which to optimize gauging system accuracy, and thus, to obtain the optimum overall system within the constraints imposed by both design and budgetary considerations. Since the subject of fuel measurement accuracy using capacitance based sensing is quite complex, no attempt is made herein to present a fully-comprehensive evaluation of all factors affecting gauging system accuracy. Rather, the major contributors to gauging system inaccuracy are discussed and emphasis is given to simplicity and clarity, somewhat at the expense of completeness. An overview of capacitive fuel gauging operation can be found in AIR5691. This document also discusses how
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
Aircraft Flotation AnalysisAIR1780A (Current)04/23/2021
This document is divided into five parts. The first part deals with flotation analysis features and definitions to acquaint the engineer with elements common to the various methods and the meanings of the terms used. The second part identifies and describes the various methods used. To accomplish the minimum intent of this document, techniques could be limited to those needed for flotation analysis only; however, because of the close relation between flotation analysis and runway design, methods for the latter are also included. In fact, runway design criteria are used for flotation and evaluation in some cases, and are periodically the governing procedure in specific, if isolated, instances. From time to time, it may be necessary to deal with runways built to obsolete criteria. Therefore, a listing of most of these constitutes the third part. The fourth part of this document tabulates the recommended documents, categorizing them for commercial and civil versus military usage, by
A-5 Aerospace Landing Gear Systems Committee
Wheel ChocksAIR4905A (Current)04/08/2021
The purpose of this document is to present general considerations for the design and use of aircraft wheel chocks. The design and use of aircraft wheel chocks is a good deal more complicated than it may appear at first glance.
AGE-3 Aircraft Ground Support Equipment Committee
Main Line Aircraft Tow Bar Attach Fitting InterfaceAS1614D (Current)04/08/2021
This SAE Aerospace Standard (AS) specifies the interface requirements for tow bar attachment fittings on the nose gear (when towing operations are performed from the nose gear) of conventional tricycle type landing gears of commercial civil transport aircraft with a maximum ramp weight higher than 50,000 kg (110,000 pounds), commonly designated as “main line aircraft”. Its purpose is to achieve tow bar attachment fittings interface standardization by aircraft weight category (which determines tow bar forces) in order to ensure that one single type of tow bar with a standard connection can be used for all aircraft types within or near that weight category, so as to assist operators and airport handling companies in reducing the number of different tow bar types used.
AGE-3 Aircraft Ground Support Equipment Committee
Generalizing Aspects of System Safety to Broaden Applicability2021-01-003703/02/2021
The Safety Assessment Process, defined by SAE ARP4761 and associated regulatory guidance, is described in the context of conventional, crewed civil aircraft. While this material has been used for decades to evaluate airplanes and rotorcraft, the evolution of technology challenges it. As new entrants venture into aviation, they bring perspectives, which may not clearly align to those conventional concepts. For those skilled in the art of aviation safety assessment, the approach to new technologies might appear straight forward. Such an individual might easily perceive the accommodations for unconventional applications. Once accommodations are made, and failure conditions are established and classified to those new architectures, the rest of the process is somewhat mechanical -they flow out of these conditions. However, the context of their experience betrays the reality of the process description in the ARP and guidance. Such accommodations are not discussed in them, and the process
Voros, Robert
Improved Energy Management System for Airplane Electrical Power2021-01-000803/02/2021
As commercial transport aircraft progress toward a future More Electric Airplane (MEA) there are numerous opportunities to improve energy management of the electrical power system. Improved energy management of the airplane electrical power system not only has the potential to decrease the weight and improve the efficiency of the system, but also to improve system stability and reliability. This paper analyzes re-architecting of an MEA airplane electrical power system in order to better manage the current electrical loads. It also considers the use of new sources of power generation and energy storage that would enable improved energy management for a new improved MEA such as fuel cells, batteries and super capacitors. The analysis uses data associated with current methods for calculating electrical loads and evaluates how the energy management of those loads can be improved with a better understanding of their usage in various flight phases, their criticality, and their power quality
Breit, Joseph Sherman
7.0.119 - Development of Combustion Solution Meeting CPCB II Emission Norms for Medium Duty Diesel Engines with Mechanical Fuel Injection SystemSAE-PP-0029502/04/2021
Indian emission norms for stationary Gensets are upgraded from CPCB I to CPCB II. These new emission norms call for a significant change in emission limits. CPCB II emission norms call for 62% reduction in NOx+HC and 33% reduction in particulates for engines above 75 kW up to 800 kW power range compared to existing CPCB I norms. CPCB II norms are more stringent as compared to European Stage IIIA and CEV BS III. To meet equivalent emission norms in US and Europe most of the engine manufacturers have used Common Rail Direct Injection (CRDI) or electronic unit injection as the fuel injection technology. This paper describes mechanical fuel injection solution for meeting CPCB II emission norms on engines between 93 kW up to 552 kW with acceptable fuel consumption values. The paper presents simulation and experimentation work carried out to achieve the norms for the said power ratings. It describes the optimization strategy for controlling combustion related parameters viz. fuel injection
Lname, Fname
6.0.115 - Legal and Consumer Requirements in ASEAN CountriesSAE-PP-0027002/04/2021
South East Asia is one of the regions with highest traffic-related fatality rates worldwide −18.5 fatalities per 100.000 inhabitants-. In response to that, governments of ASEAN countries are currently introducing new regulations, which will help to improve the road safety standards in the region. This paper reviews new safety regulations in force of following ASEAN countries: Singapore, Thailand, Malaysia, Indonesia, Vietnam and the Philippines. General safety trends promote the approach to international standards as well as the adoption of UNECE regulations. In fact, the 1958 agreement was signed by Thailand and Malaysia in 2006. Besides, Malaysia has gradually adopted fifty-three UNECE regulations so far and is currently considering the inclusion of twenty-four more. After the success of other NCAP organizations, the ASEAN NCAP assessment program was established in 2011. This program is powered by the Malaysian Institute of Road Safety Research (MIROS) and the Global New Car
Mutagaana, Festo
Particle Swarm Optimization with Required Time of Arrival Constraint for Aircraft TrajectorySAE-PP-0025502/03/2021
Global warming has motivated the aeronautical industry to develop new technologies that will reduce polluting emissions. A direct way to achieve this goal is to reduce fuel consumption. Reference trajectory optimization contributes to this goal by guiding aircraft to zones where meteorological conditions are favorable to execute their required missions and thereby to reduce flight costs. In this paper, the reference trajectory was optimized in terms of geographical position, altitude, and speed, by taking into account a required time of its arrival constraint and weather conditions. The algorithm assumes that there is no traffic and that the aircraft can fly anywhere in the search space. The search space was modeled in the form of a unidirectional weighted graph, fuel burn was computed using a numerical model, and the weather forecast was taken into account. The methodology utilized in this paper to determine the most economical combinations of parameters that delivered the optimal
Anthony, Lindsay
Vertical Take-Off & Landing Aircraft, VTOL Ground EffectsSAE-PP-0024102/03/2021
The ground-effect problems of loss of thrust and fountain-effect instabilities are quantified. Experiments to control and augment ground-effect lift and stability are presented, including jet momentum-reflection and fountain re-direction using various types of internal and external underbody ventral strakes. By strategically designing the VTOL ventral surface, reflection of the impinging fountain momentum is possible, so that instead of losing 10% thrust while in ground-effect, remarkably, thrust is augmented 10% or more, to a considerable height above the ground, in addition to stabilizing random pitch and roll moments caused by fountain instability.
Anthony, Lindsay, Jackson, Alyssa
062 - An Investigation on the Auto-Ignition of Fuel-Air Mixture Induced by Release of Oil-Fuel Droplets from Cylinder-Liner Using Multi-Zone ModelSAE-PP-0020101/30/2021
This study investigated effects of gas inhomogeneity induced by droplets of fuels and oils on the auto ignition timing and temperature in the direct-injection spark ignition (DISI) engine by means of detailed numerical calculation using multi zone model. Recent researchers pointed out that droplets are made of fuels and oils which mix on the cylinder liner and released from the cylinder liner [1]. During the compression stroke released droplets reach the auto ignition temperature before flame propagation induced by spark ignition. It is called Pre-ignition. In combustion chamber, there is inhomogeneity caused by temperature and mixture distribution. In this study, the effects of gas inhomogeneity produced by droplet on the auto ignition timing and temperature have been investigated using Multi-Zone model of CHEMKIN-PRO by changing initial temperature and initial equivalence ratio. Especially, the volume of first ignition zone is focused on. As for fuels, this study used n-heptane to
Mutagaana, Festo
Automatic Pilots (Turbine Powered Subsonic Aircraft)AS440B (Current)12/22/2020
This SAE Aerospace Standard (AS) covers automatic pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight and/or to provide maneuvering about any of the three axes through servo control. Automatic control functions essential for primary or augmented flight control are excluded.
A-4 Aircraft Instruments 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
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