The weights of major structural components of hypersonic, liquid hydrogen fueled aircraft are estimated and discussed. The major components are the body structure, body thermal protection system tankage and wing structure. The method of estimating body structure weight is presented in detail while the weights of the other components are estimated by methods given in referenced papers. Two nominal vehicle concepts are considered. The advanced concept employs a wing-body configuration and hot structure with a nonintegral tank, while the potential concept employs an all body configuration and cold, integral pillow tankage structure. Characteristics of these two concepts are discussed and parametric data relating their weight fractions to variations in vehicle shape and size design criteria and mission foi HC pop Washington requirements, and structural arrangement are presented. Although the potential concept is shown to have a weight advantage over the advanced, it involves more design uncertainties since it is farther removed in design from existing aircraft. (Author)
Structural Weight Analysis of Hypersonic Aircraft
1972
56 pages
Report
No indication
English
Structural weight analysis of hypersonic aircraft
NTRS | 1972
|Structural weight analysis of hypersonic aircraft
TIBKAT | 1972
|Body Weight of Advanced Concept Hypersonic Aircraft
NTRS | 2012
|Body weight of advanced concept hypersonic aircraft
AIAA | 1991
|Structural materials for hypersonic aircraft
NTRS | 1967
|