AEROSPACE VEHICLE WING PANEL WEIGHT OPTIMIZATION STUDY
Abstract
The objective of the study is to develop a simple and useful method of determining the optimum weights of wing panels for use in the preliminary design evaluation of advanced aerospace vehicles. An advanced aerospace vehicle is interpreted to mean a manned-recoverable single of staged booster as the most representative of future needs. The proposal is based on the premise that advanced aerospace vehicle wing panel weights are functions of basic loads, secondar loads, minimum gages, and thermal/meteorite protection requirements, any one of which may predominate. Recognition is made of the cro s effects of these requirements among themselves, and also the higher-order tradeoffs between structures, aerodynamics, and propulsion. A series of simplified analyses, to account for wing weigh s due to the 4 requirements discussed, in proposed. These analyses are to include all basic or key parameters affecting wing structure weight, on a preliminary design basis. These analyses are then programmed for a digital computer to handle all routine mathematics. The 4 basic weight influence programs are then coupled to allow simultaneous combination of these influences. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1961
- Accession Number
- AD0264654
Entities
Organizations
- General Dynamics