Most widely held works by
A. L Scow
Repair Guide for Large Area Composite Structure Repair(
图书
)
1
edition published
in
1979
in
英语
and held by
1
library
worldwide
This repair guide presents recommended procedures for the repair of large damage areas on graphite/expoxy panels. The procedures were developed during a program in which repairs were analysed, designed and tested to verify their strength and durability. Both engineering design information and specific step-by-step shop procedures are given. The recommended repair configuration uses a scarf joint machined into the parent panel as the damaged material is removed. Repair plies of prepreg are stepped to fit the scarfed surface and made to extend slightly beyond the end of the scarf leaving an esentially flush surface. The repair plies are cocured in place with a layer of film adhesive. An alternate repair is shown using a precured external patch which may be simpler to install in some cases, although at the expense of aerodynamic smoothness and with some loss in strength. The procedures in this repair guide are intended to supplement, but not replace, instructions given for the repair of specific aircraft as given in technical orders or otherwise specified by the manufacturer of the aircraft. (Author).
Flightworthy Graphite Fiber Reinforced Composite Aircraft Primary Structural Assemblies. Volume II. Tasks 6 through 12. Supplement(
图书
)
1
edition published
in
1973
in
英语
and held by
1
library
worldwide
A graphite-epoxy horizontal stabilizer designed and fabricated for the F-5A fighter has been fatigue tested for an equivalent of 16,000 flight hours with no detectable damage. The stabilizer was designed to be flightworthy in every respect and to be fully interchangeable with an existing all metal F-5A stabilizer. It was loaded under spectrum load blocks, each block representing 400 flight hours comprising 30 different load levels. The testing was halted after 40 load blocks were completed, representing 16,000 flight hours or four times the design life of the aircraft. At the conclusion of the test as well as throughout the test, the stabilizer exhibited no degradation or damage from fatigue loading. Since it was very desirable to induce a fatigue failure, testing was resumed at limit load. The stabilizer was fatigue tested an additional 10,932 cycles before failure. Visual inspection revealed a single delamination of the upper surface composite skin at the inboard edge directly over the steel spar. This report contains a description of the fatigue test (set-up, loading, instrumentation, etc.) and a summary of the pertinent results. (Author, modified-PL).
Production processes for extruding, drawing, and heat treating thin steel tee sections(
图书
)
1
edition published
in
1968
in
英语
and held by
1
library
worldwide
The three-phase program concerns processes for the manufacture of thin extruded, drawn, and heat treated tee shapes. In phase I, a production manufacturing process for the extrusion of 0.062-inch-thick by 20-foot-long tee shapes in AISI 4340, PH 14-8 Mo, and 18% Ni maraging steel was provided using a 1,200-ton Hydropress. The extrusion procedures, glass lubrication, temperature, and post-extrusion thermal and mechanical property tests are described. The results of Phase I show a relationship between alloy content, extrudability, and ram speed. AISI 4340 is the easiest to extrude and has the highest ram speed of the three alloys extruded. 18% Ni maraging steel is the most difficult to extrude and has the lowest ram speed during extrusion. The ram speed and extrudability of PH 14-8 Mo is between the two. A reproducible drawing process was refined in Phase II to reduce the thickness of the 20-foot-long tee extrusions to a target thickness of 0.040 inch. The success of the drawing phase of the program is primarily attributed to the invention of an adjustable draw die system that completely eliminates the necessity for 'pointing.' A process to heat treat 20-foot-long by 0.040-inch-thick extruded and drawn AISI 4340, PH 14-8 Mo, and 18% maraging steel tee shapes was in Phase III. The heat treat response of the three alloys is adequate and exceeds the target mechanical properties for AISI 4340 and PH 14-8 Mo.
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