We present a wireless sensor system for temperature measurement and icing detection for the use on aircraft. The sensors are flexible (i.e. bendable), truly wireless, do not require scheduled maintenance, and can be attached easily to almost any point on the aircraft surface (e.g. wings, fuselage, rudder, elevator, etc.). With a sensor thickness of less than two millimeters at the current state of development, they hardly affect the aero dynamical behavior of the structure. In this paper, we report laboratory and field results for temperature measurement and icing detection.
The ability to accurately and reliably annunciate the presence of aircraft wing contaminants greatly reduces the hazards of aircraft operation in winter precipitation environments. A new wing contamination detection system was designed to detect contaminants on the surface of an aircraft wing. Testing on a Fokker F100 aircraft was completed during the 1992-1993 winter icing season. The testing revealed that the system was able to detect ice, frost, hoar frost, and deicing fluid mixtures on the wing. The system performance was evaluated against Fokker's current requirements for an operational system.
This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and engine nacelles and the upper surfaces of the wing. The addition of an ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit. It is not intended that this Recommended Practice require the use of any particular light source such as Halogen, LED or other specific design of lamp.
This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and nacelles and the upper surfaces of the wing. The addition of ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit.
This paper discusses the importance of enroute wind conditions and the need for a wind measurement system which provides accurate and timely observations of wind and temperature conditions aloft. Recent advances in remote measurement of winds, temperature, and humidity such as the Stratospheric-Tropospheric radars and profilers developed at the National Oceanic and Atmospheric Administration’s Environmental Research Lab form the basis of such a system. A domestic system could and should be established using these devices together with a near real time winds aloft data dissemination network. Estimates of the saving in aircraft fuel consumption benefits range from 1 to 3 percent per year, or from $ 100 to $ 300 million for U.S. aviation system users at current prices and consumption.
Instrumentation that has been used for characterization of mixed-phase and glaciated conditions in the past, like the OAP probes, are subject to errors caused by variations in diffraction on the images away from the object plane and by the discrete nature of their particle detection and sizing. Correction methods are necessary to consider their measurements adequate for high ice water content (IWC) environments judged to represent a significant safety hazard to propellers and turbofan engine operability and performance. For this reason, within the frame of EU FP7 HAIC project, instrumentation characterization and validation is considered a major element need for successful execution of flight tests campaigns. Clearly, instrumentation must be sufficiently reliable to assess the reproducibility of artificial clouds with high ice water content generated in icing tunnels.
This paper is concerned with the development of statistical models for the gust field in the lowest 300 ft of the atmosphere. It presents some of the highlights of the underlying physics principles, what is known about gusts, and how gusts affect aircraft. The difficulties of developing gust models are accounted for by the lack of data in particular areas and thus direct attention to the work required to provide the needed information.
Committed to being the primary source for aerospace and ground vehicle engineering resources, SAE International has added the full compilation of our Wiley eBook collections to the SAE MOBILUS® technical resource platform. Purchasable as an annual subscription and containing the titles from the Wiley Aerospace Collection, the Wiley Automotive Collection, the Wiley Computer Systems Collection, and the Wiley Cyber Security Collection.
As an annual subscription, the Wiley Cyber Security Collection Add-On is available for purchase along with one or both of the following: Wiley Aerospace Collection Wiley Automotive Collection The titles from the Wiley Cyber Security Collection are included in the SAE MOBILUS® eBook Package. Titles: Network Forensics Penetration Testing Essentials Security in Fixed and Wireless Networks, 2nd Edition The Network Security Test Lab: A Step-by-Step Guide Risk Centric Threat Modeling: Process for Attack Simulation and Threat Analysis Applied Cryptography: Protocols, Algorithms and Source Code in C, 20th Anniversary Edition Computer Security Handbook, Set, 6th Edition Threat Modeling: Designing for Security Other available Wiley collections: Wiley SAE MOBILUS eBook Package Wiley Aerospace Collection Wiley Automotive Collection Wiley Computer Systems Collection Add-On (purchasable with the Wiley Aerospace Collection and/or the Wiley Automotive Collection)
Purchasable as an annual subscription and containing 30 eBook titles, the Wiley Aerospace Collection covers valuable engineering subject matter, such as aircraft fuel systems, aerodynamics, and propulsion. The series also goes beyond engineering, including eBooks on planning, logistical issues, and how human behavior can be managed and controlled while operating aircraft.
This paper was prepared to support supersession of MIL-S-8879C with Screw Thread Conformity Task Force selected industry standard AS8879C, published by the Society of Automotive Engineers (SAE). Other documentation changes will be covered by separate papers. Separate papers are anticipated for thread gaging issues, and thread gage calibration procedures. The STC-TF decided that the thread design standard needed to be completed before thread gage definition could be addressed. Thread gage definition has to be known before calibration procedures can be addressed.
The purpose of this document is to present general considerations for the design and use of aircraft wheel chocks. The design and use of aircraft wheel chocks is a good deal more complicated than it may appear at first glance.
In order for a large aerospace company to deliver a good product, on time, and to make a profit, its Engineering Department must be efficient and must also operate profitably, measured as a separate budget function. The Chief Project Engineer is responsible for the total performance of engineering on his program, and must see that all parts of the program are planned and accomplished efficiently and profitably. He requires much assistance from Engineering Administration; in fact, Administration must do for him many of the things that have to be done. Administration has functions deemed important in each of the three areas of work performance: technical, schedule, and cost. In the cost area of quoting and selling engineering manpower, which includes estimating, verifying estimates, preparing cost proposals, and negotiating contracts, Administration is key in each step. Methods of making accurate estimates and preparing convincing justifications are discussed.
On the whole, strategic sourcing and supplier rationalization have been successful Original Equipment Manufacturer (OEM) strategies. Often ignored however, are some of the longer-term ramifications of strategic sourcing and supplier rationalization that are less favorable, particularly if, in the process of embarking upon these strategies, an OEM looses visibility into and/or relinquishes control over, the finished part bill of material (BOM). Finished part BOM is defined as all of the material “inputs” that go into a manufactured part materials such as bar, sheet, tube, wire, fasteners, etc. This negative consequence of outsourcing, the loss of BOM visibility and control, can dilute and even undermine the very strategy that spawned it.
Unmanned Aerial Vehicles (UAV) are being deployed in military, law enforcement, search & rescue, scientific research, environmental & climate studies, reconnaissance and other commercial and non-commercial applications on a large scale. A design and development of landing gear system has been taken up for a UAV. This paper presents the design optimization of structural components of Wheel-Brake & Fork assembly pertaining to the Main Landing Gear (MLG) for a UAV. The wheel, fork, axle and brake unit constitute the wheel assembly. The wheel-brake assembly is assembled with the strut assembly and forms the Landing gear system. The Fork is the connecting member between the shock strut and the axle containing the wheel-brake assembly. As the fork and axle are subjected to shock loads while landing, the strength of these components are very much essential to withstand the dynamic loads.