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This document will contain methods to verify all aspects of the AS5725 interface, similar to how AS47643 contains verification methods for MIL-STD-1760.

The main purpose of this SAE Recommended Practice is to verify that vehicles are capable of communicating a minimum subset of information in accordance with the diagnostic test services specified in SAE J1979, or the equivalent document ISO 15031-5. Any software meeting these specifications will utilize the vehicle interface that is defined in SAE J2534. SAE J1699-3 tests shall be run using an SAE J2534-1 (API Version 04.04) Interface. However, the use of an SAE J2534-2 (API Version 04.04) Interface shall be permitted if the following conditions are met: The number of 29-bit ISO 15765 OBD ECUs exceeds the capability of the SAE J2534-1 Interface. The SAE J2534-2 Interface meets or exceeds all of the SAE J2534-1 requirements and also supports the SAE J2534 2 feature “Mixed Format Frames on a CAN Network.”

This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.

The Use Case Trace (UCTRACE) is SAE publication AIR6519 of the Department of Defense Unmanned Control Segment (UCS) Architecture. This document is the SAE publication of the Department of Defense UAS Control Segment (UCS) Architecture: Use Case Trace (UCTRACE) Version 3.4(PR) approved for Distribution A public release 15.S-1859. This information is produced from a script run against the System Use Case Model contained in the UCS Architecture Model AS6518-MODEL.eap configuration item. The System Use Case Model includes, at its lowest level of elaboration, use cases Level 2/3 (L2/L3) that describe specific scenarios of message exchanges between Actors and internal system Participants via ServiceInterfaces. These message exchanges provide a way to create detailed traces that answer the question: “What UCS service interfaces must my components implement to satisfy functional requirements represented by a given Level 2/3 UCS use case?”

This interface control document (ICD) specifies all software services in the Unmanned Systems (UxS) Control Segment Architecture, including interfaces, messages, and data model.

This AIR will provide a basic understanding of STPA and how it can be applied to development and safety assessment of civil aircraft. It will explain, by way of an example, the information needed to begin STPA, the expected STPA outputs, and the phases of aircraft development and safety assessment that can be supported by STPA.

The use of oxygenated and renewable fuels is nowadays a widespread means to reduce regulated pollutant emissions produced by internal combustion engines, as well as to reduce the greenhouse impact of transportation. Besides PM, NOx and HC emissions, also the size distribution of particles emitted at the engine exhaust represent meaningful information, considering its adverse effects on the environment and human health. In this work, the results of a comprehensive investigation on the combustion characteristics and the exhaust emissions of a GDI high performance engine, fuelled with pure bio-ethanol and European gasoline, are shown. The engine is a 4-cylinder, 4-stroke, 1750 cm₃ displacement, and turbocharged. The engine was operated at different speed/load conditions and two fuel injection strategies were investigated: homogeneous charge mode and stratified charge mode.

Electrolytically deposited chrome plate is the current standard surface treatment for landing gear component interface surfaces that require good wear resistance and corrosion protection. Chrome plated components are typically plagued by a slight debit in fatigue performance, detrimental mud cracking surface pattern, susceptibility to scoring, wear, and seal leakage. In addition, recent changes in environmental compliance standards place further restrictions on the use of electrolytically deposited chromium. Some commercial applications have already eliminated the use of chrome plate on current and future products. As a result, a substitute for electrolytically deposited chrome plate has been sought for several years. High Velocity Oxygenated Fuel (HVOF) thermal spray coatings have been developed to the point where they are being implemented as an alternative to hard chrome plate on high strength low alloy steels for external surfaces on landing gear applications.

Unregulated emissions of polycyclic aromatic hydrocarbons (PAHs), carbonylic compounds, benzene and particulate matter (PM) were quantified in exhausts of a vehicle fleet representative of in use gasoline cars. Emission factors were obtained during both cold and hot start driving cycles (from urban to motorway driving conditions). Carbonylic compounds were sampled by DNPH cartridges and analyzed by HPLC. Benzene and other light hydrocarbons were collected in bags and then analyzed by GC-FID. PAHs were trapped in XAD-2 cartridges and then analyzed by GC-MS. PM was sampled by using the gravimetric procedure required for diesel cars. The effect of technology is significant with respect to regulated and unregulated emissions but different emissive behavior was found by varying the driving cycles. Cold start has a major influence on hydrocarbon emissions (included unregulated ones). This experimental work was carried out within the framework of the EU Artemis project.

The UCS Architecture Model is the authoritative UML model of the UCS Architecture as defined in AS6512B

This platform specific Interface Control Document (ICD) provides an example mapping to the Object Management Group’s (OMG) Data Distribution Service (DDS) infrastructure middleware. The mapping is based on the Unmanned Systems (UxS) Control Segment (UCS) Architecture: Model, AS6518. A series of non-normative implementation choices have been made that are specific to this ICD. These implementation choices may not be appropriate for different system implementations. The machine readable ICD and result of this mapping and implementation choices are provided with AIR6521. Use and understanding of this document assumes a working knowledge of the UCS Architecture, the model structure and its contents.

This revision of AS6513 concerns conformance to the SAE Unmanned Systems (UxS) Control Segment (UCS) Architecture Revision B, designated AS6512B (or later). The superseded AS6513A concerned conformance to the previous UCS Architecture, designated AS6512A. This document is the authoritative specification within the UCS Architecture for establishing conformance requirements for UCS products. The conformance of UCS products is determined by assessing the conformance of the UCS Product Description to the UCS Architecture. The UCS Product Description includes test artifacts.

This document is the Architecture Description (AD) for the SAE Unmanned Systems (UxS) Control Segment (UCS) Architecture Library Revision B or, simply, the UCS Architecture. The architecture is expressed by a library of publications as referenced herein. The other SAE publications in the UCS Architecture Library Revision B are AS6513B and AS6518B. The library also includes the government-owned Autonomous Ground Vehicle Reference Architecture (AGVRA) Data Model Framework Version 3.1A.

This AIR addresses the use of Software tools to supplement or automate human activities in the development of systems, but not the hardware or software items within those systems. If a systems development tool is also used in the scope of hardware or software item development, for that usage it would then become subject to the guidance presented in DO-254 and DO-178B/C, respectively.

This Aerospace Information Report provides examples of single mechanical failure modes for components used in fixed wing, high lift actuation systems’ load paths, as well as the typical hazards posed by those failures at the aircraft level.

Spectral flame emissivity and absorption measurements with high temporal and spatial resolution were performed in an optically accessible high-swirl divided-chamber Diesel system. Simultaneous determination of soot temperature, soot volume fraction and the OH radical concentration were made from the start to the end of the combustion in 153 locations equally distributed in the chamber. The engine was run at 2000 rpm and at fixed air-fuel ratio realizing 200 consecutive combustion cycles. To visualize the spatial and temporal spray and flame evolution, direct high-speed photographic sequences were taken at 8000 frames/s. The photographic sequences showed that the spray is strongly distorted and mixed by very high swirl resulting in a well premixed region where the combustion starts. The OH radicals were detected in the fuel reaction zone. Moreover OH concentration and soot volume fraction are well correlated with soot temperature.

The purpose of this document is to define the power spectrum during normal and emergency operations of a twin engine helicopter and thereby to postulate suitable power plant rating structures. The document does not address the power requirements for single engine helicopters or those with more than two engines.

This standard establishes basic design criteria including preferred bend radii, straight lengths between bends, flattening and surface conditions in the bend area. Also included is a table of preferred tubing sizes and wall thicknesses and a formula for determining a minimum bend radius for a given tube diameter.

Most of the Trimmable Horizontal Stabilizer Actuators (THSA) feature a dual structural load path, the primary load path being loaded, the secondary load path being normally unloaded, or both load paths sharing in parallel the Horizontal Stabilizer load. This document describes existing methods for detecting rupture or disconnection of loaded load paths as an overview for those specifying or designing Horizontal Stabilizer Trim Actuators in order to compare existing solutions as reference for implementation in new aircraft programs.