|Item type||Location||Call number||Copy||Status||Notes||Date due|
|REPORT||Mesa Lab||102114 (Browse shelf)||1||Checked out||This version is a printed copy of the jpeg images from c.2||11/22/2016|
|REPORT||Mesa Lab||102114 (Browse shelf)||2||Available||This version is a cd containing jpeg images of each page of the report.|
This report is in 2 different formats, a cd containing jpeg images of each page (c.2) and a version printed from those images (c.1).
The results are presented of a comprehensive investigation into the bird impact resistance of aircraft leading-edge structures. The penetration velocity of typical designs using L73 aluminum alloy and riveted construction has been measured as a function of bird weight (up to 1.8 kg), skin thickness, nose radius, rib thickness and pitch, and sweep angle. An empirical design formula has been derived. Some trials have also been made with alternative skin materials (L72 aluminum alloy, nickel and titanium alloys and a cfrp-L73 alloy laminate) and bonded construction. For reference, empirical design formulae for the bird impact resistance of flat and curved walls of offset engine intakes are included.