<?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%">Johnson, F E</style></author></authors></contributors><titles><title><style face="normal" font="default" size="100%">155. Utilization of Electrical Specialist in Weight Control</style></title><secondary-title><style face="normal" font="default" size="100%">16th National Conference, Broadview Hotel, Wichita, Kansas, April 29 - May 2</style></secondary-title></titles><keywords><keyword><style  face="normal" font="default" size="100%">24. Weight Engineering - System Design</style></keyword></keywords><dates><year><style  face="normal" font="default" size="100%">1957</style></year><pub-dates><date><style  face="normal" font="default" size="100%">5/29/57</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=41131</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%">Wichita, Kansas</style></pub-location><pages><style face="normal" font="default" size="100%">42</style></pages><language><style face="normal" font="default" size="100%">eng</style></language><abstract><style face="normal" font="default" size="100%">A multiple Station analysis and an exponential time trend are presented for estimating the weight of the structural box of an aircraft wing. Optimum weight s calculated from the multiple station analysis which is based upon a simple beam representation of a semi-wing. It was found that a high correlation exists between the ratios of optimum weight to actual weight and time. The ratios are estimated by a time function, 1-exp-(a+bT), where T is time of first flight in months from January 1944. Errors of estimation are found to be small and the root-mean-square error is less than nine per cent. All aircraft are placed in a single category. The estimating equation for structural box weight is W(B+S)e = kW(B+S)o where k is the function of time. </style></abstract><work-type><style face="normal" font="default" size="100%">24. WEIGHT ENGINEERING - SYSTEM DESIGN</style></work-type><accession-num><style face="normal" font="default" size="100%">0155</style></accession-num><custom1><style face="normal" font="default" size="100%">Non-Member Price: $26.46. 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>