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A Structural Weight Estimation Program (Sweep) for Aircraft - Vol. VII - Fuselage Module. Appendix A; Module Flow Charts and Fortran Lists, Appendix B; Fuselage Module Sample Output

The stnxtural weight estimtion prograrn been developed as 
an analytical aircraft structural weight prediction tool suitable for use in 
the preliminary design of vehicle synthesis. Structure weight estimtes 
for the three lifting surface components of any aircraft design are nude by 
the wing ard arpennage nndule of SWEEP. This volune describes the pro- 
caiures interrBI operations of the nodule for: 
StrtEture and huss properties estimation of wing, horizontal tail, 
and vertical tail surfaces. 
• Interface with the control and data developrmt mdules of SWæ. 
analysis of pri.•rury strwtures designed with metallic or 
advanced composite mterials. 
analysis and outB1t of design data for use by the stard- 
alone flutter optimization and flexible airloads programs. 
Volune VI is organized into eight separate books: 
Books I through 3 contain technical informtion describing the 
nodule, methods used, and the applicable mdule core reps. 
Books 4 through 8 contain Appendixes A through F, which inclt.de 
program flow charts and listings for the eight major segnents of 
the nodule.

The wing and mdule of SWEEP &velops structure wei*it and 
rnass distribution estimates for wing, horizontal tail, md vertical tail 
surfaces. The procedure used is desigled to analytically evaluate the effects 
important to desigu pararreters such as air vehicle design criteria, surface 
georretry structural arrangerrents, materials and constructions, etc. This 
is accmplished thro* a close approxinution desigl and analysis procedures 
programred to describe detail surface georretry properties and structural 
design requirements. Ihese are used to synthesize structural Fonetries and 
material requiren•ents so that ulalysis for weights aid rss distributions 
be made.