"Fundamental" Parameteric Geometry Representations for Aircraft Component Shapes

2006 ◽  
Author(s):  
Brenda Kulfan ◽  
John Bussoletti
Keyword(s):  
Aircraft Component

scholarly journals Dynamic Properties and Fatigue Failure of Aircraft Component

2009 ◽  
pp. 105-114
Author(s):  
Sergei Kuznetsov ◽  
Eriks Ozolinsh ◽  
IImars Ozolinsh ◽  
Igors Pavelko ◽  
Vitalijs Pavelko
Keyword(s):  
Fatigue Failure ◽  
Dynamic Properties ◽  
Aircraft Component

High-Temperature, High-Power Performance of Ceramic Filter Capacitors

2011 ◽  
Vol 2011 (HITEN) ◽  
pp. 000027-000029
Author(s):  
K. Bridger ◽  
A. Cooke ◽  
D. Kohlhafer ◽  
R. Strite ◽  
W. Schulze ◽  
...  
Keyword(s):  
High Temperature ◽  
High Temperatures ◽  
High Power ◽  
Ceramic Filter ◽  
Power Performance ◽  
Output Stage ◽  
The Real Estate ◽  
Military Vehicles ◽  
New Family ◽  
Aircraft Component

Power conversion electronics in military vehicles and aircraft are currently experiencing high temperatures and future generations will see these temperatures rise even higher. The high temperatures arise not only from the environment but also from high power dissipation in the components themselves. Capacitors can occupy almost 50% of the real estate in some power converters and these capacitors are subjected to very high currents at high frequencies in dc-dc converters or 60-Hz 120 VAC in the output stage of an inverter. Dissipation resulting from the high power levels can lead to internal capacitor temperatures at least 50°C above their ambient and so for military hybrid electric vehicles (HEVs) capacitors are expected to reach at least 150°C and possibly 200°C, while future aircraft component temperatures are expected to exceed 250°C. A new family of high-temperature dielectrics based on sodium bismuth titanate has been developed by these authors and capacitors are now available from Novacap under the trade name “Type H” or “Type HA”. This paper examines the high-frequency, high-current and 60-Hz, 120-VAC performance of these capacitors including an estimate of internal heating. The primary operating temperature range studied is −40 to +150°C, although some higher temperature data are also presented.

An Overview of Aircraft Accident Investigation and Component Failures

2021 ◽  
pp. 778-786
Author(s):  
Ellen E. Wright ◽  
Suzanne F. Uchneat
Keyword(s):  
Case Studies ◽  
Environmental Effects ◽  
System Level ◽  
Accident Investigation ◽  
Materials Engineering ◽  
Aircraft Component ◽  
And Performance ◽  
Aircraft Accident ◽  
Component Failures ◽  
Structure Properties

Abstract This article focuses on failure analyses of aircraft components from a metallurgical and materials engineering standpoint, which considers the interdependence of processing, structure, properties, and performance of materials. It discusses methodologies for conducting aircraft investigations and inspections and emphasizes cases where metallurgical or materials contributions were causal to an accident event. The article highlights how the failure of a component or system can affect the associated systems and the overall aircraft. The case studies in this article provide examples of aircraft component and system-level failures that resulted from various factors, including operational stresses, environmental effects, improper maintenance/inspection/repair, construction and installation issues, manufacturing issues, and inadequate design.

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