Sawyer, James W. | Engineering Papers

NASA NTRS1992

Stiffened Carbon/Carbon Compression Panels

Panels with integral stiffeners made with woven fabric in two-dimensional, cross-ply layups. Local skin buckling does not cause collapse of panels, and ultimate failure occurs at loads 10 to 20 percent above buckling loads. For panels subjected to in-plane loading, separation of stiffeners from panel skins was not problem. High-temperature structural applications on advanced aircraft and spacecraft include leading edges, fairings, and control surfaces.

Sawyer, James W.↗

NASA NTRS1992

An instrumented fastener for shear force measurements in joints

Results are presented of a preliminary investigation of instrumented fasteners for use as sensors to measure the shear loads transmitted by individual fasteners installed in double splice joints. Calibration and load verification tests were conducted for instrumented fasteners installed at three fastener torque levels. Calibration test results show that the shear strains obtained from the instrumented fasteners vary linearly with the applied load and that the instrumented fasteners can be effectively used to measure shear loads transmitted by individual fasteners installed in double splice joints. The load distribution between individual fasteners is found to be dependent on the location of the fastener in the joint and the fastener torque level.

Sawyer, James W.↗