<?xml version="1.0" encoding="UTF-8"?><xml><records><record><source-app name="Biblio" version="6.x">Drupal-Biblio</source-app><ref-type>47</ref-type><contributors><authors><author><style face="normal" font="default" size="100%">Staton, R N</style></author></authors></contributors><titles><title><style face="normal" font="default" size="100%">1019. Fuselage Basic Shell Weight Prediction</style></title><secondary-title><style face="normal" font="default" size="100%">33rd Annual Conference, Fort Worth, Texas, May 6-8</style></secondary-title></titles><keywords><keyword><style  face="normal" font="default" size="100%">23. Weight Engineering - Structural Estimation</style></keyword></keywords><dates><year><style  face="normal" font="default" size="100%">1974</style></year><pub-dates><date><style  face="normal" font="default" size="100%">5/6/74</style></date></pub-dates></dates><urls><web-urls><url><style face="normal" font="default" size="100%">http://www.sawe.org/store/product_info.php?products_id=40553</style></url></web-urls></urls><publisher><style face="normal" font="default" size="100%">Society of Allied Weight Engineers, Inc.</style></publisher><pub-location><style face="normal" font="default" size="100%">Fort Worth, Texas</style></pub-location><pages><style face="normal" font="default" size="100%">52</style></pages><language><style face="normal" font="default" size="100%">eng</style></language><abstract><style face="normal" font="default" size="100%">This paper presents a method for prediction of basic fuselage shell weight intended 
for use in a weight penalty estimation technique.  Consideration is given to internal 
loading based on the applied shear and bending loads and minimum gauge requirements.  
Expressions for internal loading are developed that are used in conjunction with test 
data to determine section sizing. Methods for description of cross sections in terms 
of conic segments and techniques for accountability of material and temperature 
variation are also given. The method is intended for use as a computerized analysis 
tool and the appendices contain a Fortran source listing, output description and  
input requirements of a routine written for application of the method as presented.  
Application of this method at VSD has been primarily for fighter/attack aircraft but 
extension to other aircraft categories should require only minor modification. The 
method was developed for use in advanced design studies and is not intended for use 
in a detailed design application. </style></abstract><work-type><style face="normal" font="default" size="100%">23. WEIGHT ENGINEERING - STRUCTURAL ESTIMATION</style></work-type><accession-num><style face="normal" font="default" size="100%">1019</style></accession-num><custom1><style face="normal" font="default" size="100%">Non-Member Price: $32.76. Members may download this paper for free. &lt;a href=&quot;http://www.sawe.org/dms&quot;&gt;Click here&lt;/a&gt;. (Login Required. See SAWE &lt;a href=&quot;http://www.sawe.org/faq&quot;&gt;Frequently Asked Questions&lt;/a&gt;.)</style></custom1></record></records></xml>