The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

Analytical Investigation of Medium STOL Transport Structural Concepts: Volume I. Study Results

Report Number: AFFDL TR 74-109 Volume I
Author: Adkisson, R. E.
Author: et al
Author: Deneff, G. V.
Corporate Author: Douglas Aircraft Company, McDonnell Douglas Corporation
Corporate Report Number: MDC J-6625, Volume I
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1974-08
Pages: 423
Contract: F33615-73-C-3049
Project: 1368
Task: 0212
AD Number: ADA005818
Original AD Number: AD/A-005818

Results of a study program to devise and evaluate new structural concepts of lower weight and cost for a medium STOL transport aircraft are presented. The wing box, fuselage shell and empennage stabilizer structure of the projected C-15 production airplane were designated as the study (and baseline) components. Selected concepts are evaluated for structural integrity, weight, manufacturing methods, applicability of NDI methods, production and life cycle costs and aircraft performance payoffs. Structural integrity analyses of both the baseline and new concepts are based on a common set of requirements for ultimate strength, fatigue life, damage tolerance and flutter rigidity.

The primary materials considered are aluminum. titanium. steel and beryllium. Of these, aluminum 7050 and 7475 are a best choice for minimum production cost and low weight. The primary geometry concepts considered include integral stiffened, honeycomb and isogrid (a special form of integral stiffened). Integral stiffened and honeycomb geometry, in conjunction with the selected aluminum materials, produce weight and cost savings in the participating individual components of up to 10% which are further reflected as overall life cycle cost savings and performance payoffs at the aircraft system level. Innovative concepts for wing cover panel spanwise skin splices are also shown.

Requirements for simple "design-for-weight" and "design-for-cost" methods are identified. A simple "design-for-weight" method integrating materials, geometries and requirements was conceived and is implemented. A simple concept selection parameter based on unit weight and cost is also identified. Methods for developing consistent material property data and correlating of notched specimen fatigue data are also presented •

Download this report

(PDF, 17.86 MB, 423 pages)

Other options for obtaining this report

Via the Defense Technical Information Center (DTIC):
A record for this report, and possibly a full-image download of the report, exists at DTIC

Via National Technical Information Service:
This report may have been digitized and made freely available for public download, or made publicly available for purchase by the National Technical Information Service through their online database, the National Technical Reports Library

Indications of Public Availability
No digital image of an index entry indicating public availability is currently available
There has been no verification of an indication of public availability from an inside cover statement

Related Reports

This report has the following parts/volumes: