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This specification covers established metric manufacturing tolerances applicable to aluminum alloy drawn tubing ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "excl" applies only to the higher figure of the specified range.

This specification covers established metric manufacturing tolerances applicable to aluminum alloy drawn tubing ordered to metric dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "excl" applies only to the higher figure of the specified range.

This specification describes the general connectors, contacts, and backshells in their shape and characteristic for cabin systems for commercial aircrafts. ARINC 600, ARINC 404, and ARINC 801 connector specifications are published as independent standards.

This specification describes the general connectors, contacts, and backshells in their shape and characteristic for cabin systems for commercial aircrafts. ARINC 600, ARINC 404, and ARINC 801 connector specifications are published as independent standards.

The Manufacturing Message Specification is an application layer Standard designed to support messaging communications to and from programmable devices in a Computer Integrated Manufacturing (CIM) environment. This environment is referred to in this Standard as the manufacturing environment. This Standard does not specify a complete set of services for remote programming of devices, although provision of such a set of services may be the subject of future standardization efforts.

This document defines a secure Wi-Fi distribution network installed in the aircraft passenger cabin for passenger and crew use. Carry-on Portable Electronic Devices (PEDs) such as smart phones, tablets, and laptops may use this network to access public internet services provided on the aircraft.

Small aircraft and helicopters have an increasing need for heads out presentations, which means a projected presentation of symbols and images, primarily infrared, on an optical combiner in the pilots field of view. The information presented will appear at an infinite distance i.e. the focal point is far away enabling the pilot to see the symbology superimposed on and correlated to the outside world. The driving factors for a heads out presentations are increased safety through improved situation awareness in almost all weather conditions as well as operational improvements due to reduced landing minimal prerequisites in adverse weather conditions. Also safety during taxiing and landing are improved through early detection of eventual other aircraft and objects. The landing aid is important for small aircraft like business jets that often fly into unequipped airfields. The overall benefits are reduction in number of incidents/accidents, cost savings and reduced number of diversions.

Electroimpact Automatic Fiber Placement (AFP) machines lay-up composite parts by accurately placing carbon fiber tow (strips of impregnated carbon fiber) on a mould. In order to achieve high accuracy at high speeds, the processes of feeding and cutting tows must be tuned. Historically, the tuning has been a time-consuming, manual process. This paper will present a methodology to replace manual measurements with an automated laser, improve measurement speed by an order of magnitude, improve accuracy from +/? 0.020? (manual) to +/? 0.015? (laser), and eliminate human error. Presenter Joshua Cemenska, Electroimpact Inc.

The Aircraft Interiors subscription addresses the specialized needs and mechanical requirements for aircraft cabin interior design. The application of these standards will aid in the efficient and cost-effective manufacture of quality aircraft components. The standards in this resource include: Glossary of Technical and Physiological Terms Related to Aerospace Oxygen Systems Flight Deck Layout and Facilities Numeral, Letter and Symbol Dimensions for Aircraft Instrument Displays Oxygen Equipment for Aircraft Human Interface Design Methodology for Integrated Display Symbology

The 21 papers in this technical paper collection cover driver crash avoidance behavior; factors that influence drivers’ response choice decisions; collision avoidance systems; steering wheel switch technology; effects of hands-free phone conversation on visual behavior; seat support evaluation; and more.

This technical paper collection features 15 papers covering electrification of the commercial vehicle, techniques for efficiency and reliability; developments in sensors; model based design and embedded software development; heavy duty electronic technology; autonomous vehicles; electronic control module development and test; and vehicle structure.

This SAE Aerospace Information Report (AIR) describes procedures, required continuous sampling conditions, and instrumentation for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to calculate sampling loss performance. This AIR is not intended for in-flight testing, nor does it apply to engine operating in the afterburning mode.

This report defines the requirements and recommended practices for production testing of aircraft passenger seats and seat groups. Production testing is performed at the seat manufacturers' facilities prior to the shipment of the seats to the airframe manufacturers, Maintenance, Repair, and Overhaul (MRO), or airlines/operators for installation in the aircraft. Using this guidance, rework is minimized and schedules remain minimally affected.

ARINC 661 defines logical interfaces to Cockpit Display Systems (CDS) used in all types of aircraft installations. The CDS provides graphical and interactive services to user applications within the flight deck environment. When combined with data from user applications, it displays graphical images to the flight deck crew. The document emphasizes the need for independence between aircraft systems and the CDS. This document defines the interface between the avionics equipment and display system graphics generators. This document does not specify the "look and feel" of any graphical information, and as such does not address human factors issues. These are defined by the airline flight operations community. Supplement 7 adds the definition of: Selector Widget, Tree Widget, New FormatString options, Readouts available in MapItems, Provisions for Touch Screen Displays.

This document establishes the minimum criteria for effective training of air carrier and contractor personnel to deice/anti-ice aircraft to ensure the safe operation of aircraft during ground icing conditions. Appendix D specifies guidelines for particular airplane models.

Abstract More than a decade ago, we proposed combined use of direct injection (DI) and jet ignition (JI) to produce high efficiency, high power-density, positive-ignition (PI), lean burn stratified, internal combustion engines (ICEs). Adopting this concept, the latest FIA F1 engines, which are electrically assisted, turbocharged, directly injected, jet ignited, gasoline engines and work lean stratified in a highly boosted environment, have delivered peak power fuel conversion efficiencies well above 46%, with specific power densities more than 340 kW/liter. The concept, further evolved, is here presented for unmanned aerial vehicle (UAV) applications. Results of simulations for a new DI JI ICE with rotary valve, being super-turbocharged and having gasoline or methanol as working fuel, show the opportunity to achieve even larger power densities, up to 430 kW/liter, while delivering a near-constant torque and, consequently, a nearly linear power curve over a wide range of speeds.

Abstract It is reasonable to use a two-phase heat transfer loop (TPL) in a thermal control system (TCS) of spacecraft with large heat dissipation. One of the key elements of TPL is a heat-controlled accumulator (HCA). The HCA represents a volume which is filled with vapor and liquid of a single working fluid without bellows. The pressure in a HCA is controlled by the heater. The heat and mass transfer processes in the HCA can proceed with a significant nonequilibrium. This has implications on the regulation of TPL. This article presents a mathematical model of nonequilibrium heat and mass transfer processes in an HCA for microgravity conditions. The model uses the equations of mass and energy conservation separately for the vapor and liquid phases. Interfacial heat and mass transfer is also taken into account. It proposes to use the convective component k for the level of nonequilibrium evaluation.

Abstract Improving the energy performance of batteries can increase the reliability of electric aircraft. To achieve this goal, battery management systems (BMS) are required to keep the temperature within the battery pack and cells below the safety limits and make the temperature distribution as even as possible. Batteries have a limited service life as a result of unwanted chemical reactions, physical changes that cause the loss of active materials in the structure, and internal resistance increase during the charging and discharging cycle of the battery. These changes usually affect the electrical performance of batteries. Battery life can be increased only by reducing or preventing unwanted chemical reactions. Lithium-ion (Li-ion) batteries are a suitable option due to their high specific energy and energy density advantages. In this study, the necessity of heat management is emphasized. The discharge tests of the Li-ion battery provided 94.6 Wh under 10C and 90.9 Wh under 1C.

Abstract The preliminary gas turbine combustor design process uses a huge amount of empirical correlations to achieve more optimized designs. Combustion efficiency, in relation to the basic dimensions of the combustor, is one of the most critical performance parameters. In this study, semi-empirical correlations for combustion efficiencies are examined and correlation coefficients have been revised using an experimental air-blasted tubular combustor that uses JP8 kerosene aviation fuel. Besides, droplet diameter and effective evaporation constant parameters have been investigated for different operating conditions. In the study, it is observed that increased air velocity significantly improves the atomization process and decreases droplet diameters, while increasing the mass flow rate has a positive effect on the atomization—the relative air velocity in the air-blast atomizer increases and the fuel droplets become finer.