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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.

ARINC 800 is the first industry standard intended for characterization of aviation-grade high-speed (Gbps) Ethernet links. The test methods are based on realistic representation of cabin networks. The notional cabling architecture is based on IFE seat distribution using multiple intermediate disconnects. Sequential testing is supported by building up number of connectors in the link. Test guidelines for mixed intermediate cable lengths are provided.

Silicones have been utilized in multiple industries in the last 50 years and their applications are still expanding as technology grows. Ice phobic coatings, as an example, have been utilized on lock walls, navigation channels, wind turbines, hydropower intakes, and aircraft. Without protection these applications have a high risk of failure in the functions they perform. For example, ice build up on an aircraft?s aerodynamic surfaces increases drag which reduces lift during flight operations. Utilizing a silicone ice phobic coating significantly reduces the adhesion of ice to aerodynamic surfaces. Compared to other polymeric materials, silicones are known for their broad operating temperature range and lend themselves to excellent performance in a variety of harsh environments. Especially in low temperatures where ice adhesion is a concern, silicones retain their elastomeric physical properties and low modulus.

In this presentation we will present a COTS solution for an ARINC 653 IMA based system. It will cover IMA concepts from an OS point of view and show how a platform can be built for application development. It will also cover DO-297, and how that can isolate applications for certification and test purposes and allow for easy configuration of multiple applications between different development teams. Presenter Alex Wilson, Wind River

Abstract A novel use of state estimation methods as initial input for a landing response analysis is proposed in this work. Six degrees of freedom (DOF) non-linear landing response model is conceived by considering longitudinal dynamics of aircraft as a rigid body with heave-and-pitch motions coupled onto a bicycle landing gear † arrangement. The DOF for each landing gear consist of vertical and longitudinal motions of un-sprung mass, considering strut bending flexibility. The measurement data for state estimation is obtained for three landing cases using non-linear flight mechanics model interfaced with pilot-in-loop simulation. State estimation methods such as Upper Diagonal Adaptive Extended Kalman Filter (UD-AEKF) with fuzzy-based adaptive tuning and Un-scented Kalman Filter (UKF) were adapted for landing maneuver problem. On the basis of estimation error metrics, aircraft state from UKF is considered during onset of touchdown.

Abstract From the fact that a propulsor consumes less power for a given thrust if the inlet air is slower, simulations are conducted for a propulsor imposed behind an airfoil as ideal boundary layer ingestion (BLI) propulsor to stand on the benefits of this configuration from the point of view of power and efficiency and to get a closer look on the mutual interaction between them. This interaction is quantified by the impact on three main sets of parameters, namely, power consumption, boundary layer properties, and airfoil performance. The position and size of the propulsor have great influence on the flow around the airfoil. Parametric studies are carried out to understand their influence. BLI propulsor directly affects the power saving and all of the pressure-dependent parameters, including lift and drag. For the present case, power saving reached 14.4% compared to the propeller working in freestream.

Abstract A flight envelope for aircraft performance in the vertical plane illustrates the performance limitations on the aircraft, usually indicating the minimum and maximum airspeeds at a given altitude, the airspeeds for maximum rate of climb and maximum angle of climb at a given altitude, and the maximum altitude or absolute ceiling of the aircraft. This study outlines the procedure for constructing a vertical-plane flight performance aircraft for an aircraft with a fixed-pitch propeller, which involves additional complexities due to the variable propeller efficiency. The propeller performance, engine power, and drag polar models are described, as is the computational procedure. Envelopes for the flight performance in the vertical plane are presented for a particular remotely-piloted aircraft at different take-off weights.

This document establishes techniques for validating that a mission store complies with the interface requirements contained in MIL-STD-1760 Revision D.

This information report is useful for personnel involved in the design, manufacturing, and/or use of digital fiber optic transmitters, receivers, and transceivers for aerospace applications

A single depository for fiber optic and applied photonic definitions.

To detail the different epoxy types available for different aerospace applications which require different temperature ranges. Explain incoming/final inspection requirements and storage requirements. Examine the epoxy chemical make up with explanations of purpose in performance.

This document provides guidance on key areas of system design to achieve high performance and high reliability for mission critical aerospace systems and platforms. The fundamental element of a reliable, functional aerospace fiber optic application is the system design. It is the system designers’ task to define the methods, components, installation and processes supporting the transmission of the optical signal through the platform, while providing a physical layer with the necessary performance, reliability, and readiness for the application.

CONTACTS, ELECTRICAL CONNECTOR, SOCKET, CRIMP REMOVABLE, SIZES 12, 16, 20, 22 AND 23 (FOR MICRO MINIATURE CONNECTORS)

CONTACTS, ELECTRICAL CONNECTOR, PIN, CRIMP REMOVABLE, SIZES 12, 16, 20, 22 AND 23 (FOR MICRO MINIATURE CONNECTOR)

This project is being requested to convert MIL-C-39029/66 to an SAE standard so that this contact can be called out as a requirement in MIL-DTL-24308/41 and /42.

This project is being requested to convert MIL-C-39029/65 to an SAE standard so that this contact can be called out as a requirement in MIL-DTL-24308/41 and /42.

This request is to establish a new 39029 slash sheet to define a size 8 Quadrax socket contact.

This specification includes detailed requirements for a fiber optic cable splice compliant with AS5405.

This SAE Aerospace Standard (AS) defines the testing methods for all aerospace optic cables. The application of the test methods are defined in the slant sheets. Technical, dimensional, mechanical and operating performance requirements for the associated aerospace fiber optic cables are detailed in the applicable specification slant sheet. In the event of conflict between this standard and the slant sheet, the slant sheet shall take precedence.