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This course is verified by Probitas Authentication as meeting the AS9104/3A requirements for continuing Professional Development. This one-day program is designed to provide introductory information for those organizations who are considering transitioning from the Aeronautic, Space and Defense industry to the Food & Drug Administration (FDA), Medical Device Manufacturing market. Reviewing essential information necessary to understand and successfully begin the journey to FDA Medical Device approval, this course will examine many of the controls between the AS9100 Standard and FDA Regulations and identify the similarities.

Use of airborne high resolution digital sensor imagery is ever increasing. Color HDTV, infrared cameras and radar are examples of such sensors. And they are becoming increasingly used for mission purposes by the military, police, customs and coast guard onboard helicopters and fixed wing aircraft. These users have requirements for onboard presentation, analysis and storage. Use of weather radars and other similar types of sensors are flight oriented applications in major types of aircraft. Another application is the integration of cockpit and cabin surveillance systems onboard commercial airlines. Cabin surveillance systems, growing from cockpit door cameras to complete cabin surveillance, will use several cameras. The purpose is to acquire and store imagery from un-normal events including unruly passengers and eventual terrorists. The primary intentions are security awareness in the cockpit as well as collecting evidence for a potential prosecution.

The purpose of this document is to provide guidance on in-flight thrust determination of engines that are impacted by intentional or unintentional thrust vectoring. However, as indicated in the Foreword, the field of aircraft thrust vectoring is varied and complex. For simplicity and coherence of purpose, this document will be limited in scope to multi-axis thrust vectoring nozzles or vanes attached to the rear of the engine or airfame; single-axis thrust vectoring and unintentional thrust vectoring (fixed shelf or deck configuration) are special cases of this discussion. Specifically excluded from this scope are thrust vectoring created primarily by airframe components such as wing flaps, etc.; lift engines, propulsive fans and thrust augmenting ejectors; and powerplants that rotate or otherwise move with respect to the airframe.

The purpose of this SAE Aerospace Information Report (AIR) is to provide information that would be useful to potential users/operators and decision makers for evaluating and quantifying the benefits of an Engine Monitoring Systems (EMS) versus its cost of implementation. This document presents excerpts from reports developed to analyze “actual aircraft cost/benefits results”. These are presented as follows: a First, to outline the benefits and cost elements pertaining to EMS that may be used in performing a cost versus benefits analysis. b Second, to present considerations for use in conducting the analysis. c Third, to provide examples of analyses and results as they relate to the user/operator and decision-maker community. The document encompasses helicopters and fixed wing aircraft and distinguishes between civilian and military considerations.

The first cross-industry guidelines for the implementation of structural health monitoring for aerospace applications have been created as a SAE International Aerospace Recommended Practices document: SAE ARP 6461 ‘Guidelines for Implementation of Structural Health Monitoring on Fixed Wing Aircraft’ [1]. These guidelines have brought together manufacturers, operators / users, systems integrators, regulators, technology providers and researchers to produce information on the integration of SHM into aircraft maintenance procedures, generic requirements and advice on validation, verification and airworthiness. The take-up of SHM in the aerospace industry has been slow, in part due to the lack of accepted industry practices surrounding not just the technology itself (sensors and sensor systems) but also the associated issues arising from the introduction of new methods into aircraft maintenance.

Recent advances in small unmanned air vehicles (UAV) lead to robust on-board stabilized platforms ready to use for real-world problems. As a result, many different autonomy functions have been demonstrated, which allow controlling the UAVs at high level. However, the great variety of platforms also poses new challenges when adapting these autonomy functions to new platforms. For instance modifying a trajectory planning algorithm, which was designed for a rotary-aircraft with a moving camera, to work on a fixed-wing aircraft with a static camera is not a trivial task. Often such algorithmic solutions are tailored so specifically to a certain platform that it becomes very complicated to reuse algorithms. This results in a variety of many different approaches trying to solve the same task. We therefore encourage designing algorithms for UAVs autonomy function to be more generic. As an example, we focus on the task to autonomously follow a moving ground object using an UAV.

The power demands in terms of kilowatt-hour electrical use were compared for autoclave curing commercial thermosetting carbon fiber pre-pregs with an innovative alternative of high energy X-ray curing. An automotive component, now made with carbon fiber composites, was selected as an illustrative example, an Aston-Martin hood. Temperature resistant polyester molds for these hoods were used and manufacturer recommended autoclave curing conditions were followed. X-rays, which can penetrate about 15 cm (6 inches) in unit density materials (or less into higher density materials as molds), were used to cure pre-pregs made with a specialty matrix material using the same molds, but doing so without adding any heat for curing. High energy X-ray equipment, generated from a 7 MeV, 700 kW electron beam, is in commercial use for medical device sterilization. This same equipment can also be used for composite curing.

This work investigates the image quality achievable with a large-aperture endoscope system and high-speed cameras in terms of detecting the premixed flame boundary in spark-ignited engines by chemiluminescence imaging. The study is an extension of our previous work on endoscopic flame imaging [SAE 2014-01-1178]. In the present work, two different high-speed camera systems were used together with the endoscope system in two production engines to quantify the time-resolved flame propagation. The systems were cinematography with a CMOS-camera, both with and without an intensifier, the latter variation being used in a four-cylinder automotive engine as well as in a single-cylinder motorcycle engine. An algorithm with automatic dynamic thresholding was developed to detect the line-of-sight projected flame boundary despite artifacts caused by the spark and the large dynamic range in image brightness across each time series.

In 2007, researchers at the Massachusetts Institute of Technology successfully completed a Wireless Power Transfer (WPT) experiment. Ever since, interest in WPT has been growing. At Toyota, we have been developing the underlying technology of a WPT system. Simultaneously we have been working with regulatory committees to create a standard for WPT. In particular, there are concerns that WPT’s radiated emissions could cause harm to humans and the neighboring electronic equipment. There are many challenges that need to be overcome, but a key concern is understanding WPT’s electromagnetic compatibility (EMI: Electro-Magnetic Interference and EMF: Electro-Magnetic Field). In this paper, we show the technical issues, the evaluation method, and the development status of EMI and EMF on PHVs/EVs when using WPT. For Electromagnetic interference (EMI) performance, we investigated both an open area test site and an electromagnetic anechoic chamber as evaluation environments.

This document covers recommendations for the application of existing qualified and approved in-service fixed wing aircraft tires, wheels and brakes to military and commercial rotorcraft. NOTE: This document does not address the use of radial tires due to insufficient data to support their approved use on rotorcraft, see paragraph 4.3.14 for specific impact on ground resonance.

The scope of this Vertical Flight document is limited to human behavioral technologies associated with design and/or implementation of Enhanced Synthetic Vision Systems (ESVS) in vertical flight aircraft. Any overlap into logic problems or hardware/software design shall be considered to be incidental to the human factors issues. Where the performance characteristics of specific technologies are relevant they will be identified, and where performance criteria are relevant to specific intended functions/use they will be identified. From a regulatory view, intended function (Full Flight Guidance or Information/Situation Awareness support) has a tremendous effect upon the design of an ESV System. However from a Human Engineering standpoint, the information on display must be discernible and comprehensible to the human operator in both cases and differences may be primarily in information content (required to support a specific task).

This SAE Aerospace Recommended Practice (ARP) discusses design philosophy, system and equipment requirements, environmental conditions, and design considerations for rotorcraft environmental control systems (ECS). The rotorcraft ECS comprises that arrangement of equipment, controls, and indicators which supply and distribute dehumidified conditioned air for ventilation, cooling and heating of the occupied compartments, and cooling of the avionics. The principal features of the system are: a A controlled fresh air supply b A means for cooling (air or vapor cycle units and heat exchangers) c A means for removing excess moisture from the air supply d A means for heating e A temperature control system f A conditioned air distribution system The ARP is applicable to both civil and military rotorcraft where an ECS is specified; however, certain requirements peculiar to military applications—such as nuclear, biological, and chemical (NBC) protection—are not covered.

This ARP discusses design philosophy, system and equipment requirements, environmental conditions, and design considerations for helicopter environmental control systems (ECS). The helicopter ECS comprises that arrangement of equipment, controls, and indicators which supply and distribute dehumidified conditioned air for ventilation, cooling and heating of the occupied compartments, and cooling of the avionics. The principal features of the system are: a A controlled fresh air supply b A means for cooling (air or vapor cycle units and heat exchangers) c A means for removing excess moisture from the air supply d A means for heating e A temperature control system f A conditioned air distribution system The ARP is applicable to both civil and military helicopters where an ECS is specified; however, certain requirements peculiar to military applications, such as nuclear, biological and chemical (NBC) protection, are not covered.

This SAE Aerospace Recommended Practice (ARP) establishes the requirements for the design, manufacture, and qualification of four hydraulic switching valves used in airborne applications. Two are pressure operated, Type IA and IB and two are solenoid/pilot operated, Type IIA and IIB. They are applicable to four pressure classes 3000, 4000, 5000 and 8000 psi. The equipment as designed is intended to be installed in hydraulic systems designed to AS5440 for military applications or ARP4752 and ARP4925 depending on the type of aircraft for commercial applications. Additional or refined requirements shall be contained in the detail (procurement) specification and these shall take precedence over any potentially conflicting requirements of this ARP or documents referenced by this ARP.

Many embedded software developers producing C code for automotive applications will be familiar with the MISRA C guidelines. These provide practical guidance in avoiding some of the common pitfalls associated with the C language. They were originally meant for automotive developers, but are now increasingly used in other critical sectors such as aerospace and medical devices. The commonly-held view, expressed in the MISRA C guidelines, is that all C code, whether hand-written or automatically generated, should be subjected to exactly the same verification and validation activities. However, as modeling language and automatic code generation techniques have evolved over the 10 years since the first edition of MISRA C, this advice may no longer be so relevant. This paper looks at some of the issues related to verification and validation of automatically-generated C code and identifies the situations in which the authors believe that a different approach is warranted.

Car seats with a variety of adjustments and massage systems are available in many cars. It could increase comfort. In a vehicle, particularly a car, it is difficult to increase comfort by variation in posture, since the person has to concentrate on traffic conditions and steering. A car seat has to support the body, since various forces occur, such as acceleration, slowing down and lateral forces. The driver / passenger is well supported by the car seat, and spends a certain time there in an unchanged position. Due to these facts it is meaningful to integrate a massage activity system (MAS) into a car seat. In this way, it is possible to devote oneself fully to the task of driving and the surrounding traffic. A MAS can take control of revitalising and changing the sitting position of the car occupants. Until now, the effect of the use of massage systems and additional equipment such as lumbar support on the intervertebral discs has never been studied.

This SAE Aerospace Recommended Practice (ARP) contains the general requirements and test procedures for Dual Mode (NVIS Friendly visible and Covert) exterior lighting for most rotorcraft and fixed wing aircraft and could be applicable to ground vehicles that desire a Dual Mode lighting system.