Search Results

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 purpose of this document is to provide an overview of data networking standards recommended for use in commercial aircraft installations. These standards provide a means to adapt commercially defined networking standards to an aircraft environment. It refers to devices such as bridges, switches, routers and hubs and their use in an aircraft environment. This equipment, when installed in a network topology, can optimize data transfer and overall avionics performance.

The purpose of this document is to establish guidelines that should be observed during initial design, production, and maintenance of aircraft components, and to present short-term and long-term strategies to minimize the costs and impacts associated with decreasing availability of components.

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.

The growing need for an efficient worldwide airspace system management, generated by an increasing traffic load, requires new capabilities for air-ground data communication technologies. In order to cope with these requirements, the Federal Aviation Administration (FAA), EUROCONTROL, and the International Civil Aviation Organization (ICAO) have jointly made specific recommendations for candidate technologies for the airport surface communication network. In the SESAR project, the Aeronautical Mobile Airport Communication System (AeroMACS) technology is being developed in such a way to provide next generation broadband and wireless data communications for airport surface applications (i.e. Air Traffic Control ? ATC, Airline Operational Communications ? AOC, and surface vehicles services).

As a result of recommendation from the Augustine Panel, the direction for Human Space Flight has been altered from the original plan referred to as Constellation. NASA's Human Exploration Framework Team (HEFT) proposes the use of a Shuttle Derived Heavy Lift Launch Vehicle (SDLV) and an Orion derived spacecraft (salvaged from Constellation) to support a new flexible direction for space exploration. The SDLV must be developed within an environment of a constrained budget and a preferred fast development schedule. Thus, it has been proposed to utilize existing assets from the Shuttle Program to speed development at a lower cost. These existing assets should not only include structures such as external tanks or solid rockets, but also the Flight Software which has traditionally been a ?long pole? in new development efforts. The avionics and software for the Space Shuttle was primarily developed in the 70's and considered state of the art for that time.

This paper proposes a current limits distribution control strategy for a parallel hybrid electric vehicle (parallel HEV) which includes an advanced powertrain concept with two electrical driving axles. One of the difficulties of an HEV powertrain with two electrical driving axles is the ability to distribute the electrical current of one high voltage battery appropriately to the two independent electrical motors. Depending on the vehicle driving condition (i.e., car maneuver) or the maximization of the entire efficiency chain of the system, a suitable control strategy is necessary. We propose an input-output feedback linearization strategy to cope with the nonlinear system subject to input constraints. This approach needs an external, state dependent saturation element, which translates the state dependent control input saturation to the new feedback linearizing input and therefore preserves the properties of the differential geometric framework.

pilots, air traffic controllers, dispatchers, aviation meteorologists

This activity is focused on more electric and all electric type power systems for air vehicles. The scope of which includes source, distribution and user contributions to electrical power quality, failure modes, coordination, system reliabilty and robustness, impacts of being flight critical and the gaps which exist in present standards and guidance documents.

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 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.

Clarify the role of the human considerations in Functional Hazard Assessments by identifying the sufficient input information regarding those considerations from the development process, how failure conditions may use that information, and what information the safety assessment process provides to other processes, particularly Human Factors, to assure those aspects of failure conditions are valid.

This AIR would examine the applicability of ARP 4754 and ARP 4761 to UAS and would identify the shortcomings in both recommended practices with regards to the specific technical aspects needed for UAS development.

This SAE Aerospace Information Report is intended to provide advanced methods for wire selecting and sizing in aerospace application as a continuation of AIR6540, Fundamentals in Wire Selection and Sizing for Aerospace Applications. Also, it will provide valuable information for the electrical design engineer to verify the proper wire selection and validate a set of system design requirements which includes meeting environmental and installation constraints.

EPS stability is an essential property that defines EPS ability to provide secure operation under required range of operation scenario. Power system stability is defined as “the ability of an electric power system, for a given initial operating condition, to regain a state of operating equilibrium after being subjected to a physical disturbance, with most system variables bounded so that practically the entire system remains intact”. This is applicable for AC and DC systems and has to address steady state conditions, transient conditions as well as high power loads connection / disconnection on the network.

The need for developing this standard is driven by the quickly evolving field of electrified propulsion for aircraft. Industry is moving forward in development of a broad range of high voltage primary power systems. There is an immediate need to standardize power quality requirements for design, analysis, verification, and testing for these types of systems.

Technical requirements especially related to the design and construction and the minimum performance requirements (including qualification test conditions) for PM motors and power converters (operated as VFDs) used as the prime mover for more-electric, hybrid-electric, and fully-electric aircraft propulsion systems.

This Aerospace Recommended Practice will identify the problem with latency in the pilot's instrument control of an aircraft. Recommended evaluation techniques to characterize control problems will be documented.

This AIR intends to better document and tabulate electrical load dynamics that influence power source capacity, power quality and stabiltiy.

To determine the end-of-life criteria of electrical insulation materials and components and predict insulation life in high voltage aviation applications