<?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%">Wright, R L</style></author><author><style face="normal" font="default" size="100%">Deryder, D D</style></author><author><style face="normal" font="default" size="100%">Ferebee, M J</style></author><author><style face="normal" font="default" size="100%">Smith, J C</style></author></authors></contributors><titles><title><style face="normal" font="default" size="100%">1556. Interactive Analysis of a Large Aperture Earth Observation Satellite</style></title><secondary-title><style face="normal" font="default" size="100%">42nd Annual Conference, Anaheim, California, May 23-25</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%">1983</style></year><pub-dates><date><style  face="normal" font="default" size="100%">5/23/83</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=40187</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%">Anaheim, California</style></pub-location><pages><style face="normal" font="default" size="100%">21</style></pages><language><style face="normal" font="default" size="100%">eng</style></language><abstract><style face="normal" font="default" size="100%">A system level design and analysis has been conducted on an Earth Observation Satellite (EOS) system 
using the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) computer-aided design and
analysis program. The IDEAS program consists of about 40 user-friendly technical modules and an 
interactive graphics display. 

The reflector support system and feed mast of the EOS spacecraft are constructed with a box-truss
structural concept, a lattice configuration which can be packaged for delivery in a single Shuttle
flight and deployed in orbit. The deployed spacecraft consists of a 120-m by 60-m parabolic reflector, 
a 120-m-long support structure, and a 30-m feed arc beam on the focal axis. The spacecraft was modeled
for structural , thermal , and control systems analysis and structural elements were designed.  On-orbit
dynamic and thermal loading analyses were conducted and spacecraft weights were determined. </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%">1556</style></accession-num><custom1><style face="normal" font="default" size="100%">Non-Member Price: $13.23. 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>