Abstract: An example test fixture includes a lower frame having a first rocker rail and a second rocker rail coupled to the first rocker rail, wherein each of the first rocker rail and the second rocker rail has a respective curved surface that allows the lower frame to tilt about a first axis; a rotatable base coupled to the lower frame; an upper frame having a mounting system configured to couple a transmission of an aircraft to the upper frame; a support frame that couples the upper frame to the rotatable base; and a rotary actuator configured to rotate the rotatable base, the support frame, and the upper frame about a second axis perpendicular to the first axis.

Abstract: An example test fixture includes a lower frame having a first rocker rail and a second rocker rail coupled to the first rocker rail, wherein each of the first rocker rail and the second rocker rail has a respective curved surface that allows the lower frame to tilt about a first axis; a rotatable base coupled to the lower frame; an upper frame having a mounting system configured to couple a transmission of an aircraft to the upper frame; a support frame that couples the upper frame to the rotatable base; and a rotary actuator configured to rotate the rotatable base, the support frame, and the upper frame about a second axis perpendicular to the first axis.

Abstract: A fixture, system, and method are provided for testing one or more axial loads in a flexible aerodynamic member. The fixture has a structural frame assembly with a first end portion, a second end portion, and an intermediate portion. The fixture has a first pivotal linkage assembly pivotable about a pitch axis, a pair of pitch actuators to apply a pitch moment to the first pivotal linkage assembly, a second pivotal linkage assembly pivotable about a flap axis, and a pair of flap actuators to apply a flap bending moment to the second pivotal linkage assembly. The fixture has a third pivotal linkage assembly pivotable about the pitch axis, and has a pair of chord actuators to apply axial load to the flexible aerodynamic member. The fixture minimizes deflections of a tip of the flexible aerodynamic member during testing to provide an improved accuracy of axial load measurement data.

Abstract: A fixture, system, and method are provided for testing one or more axial loads in a flexible aerodynamic member. The fixture has a structural frame assembly with a first end portion, a second end portion, and an intermediate portion. The fixture has a first pivotal linkage assembly pivotable about a pitch axis, a pair of pitch actuators to apply a pitch moment to the first pivotal linkage assembly, a second pivotal linkage assembly pivotable about a flap axis, and a pair of flap actuators to apply a flap bending moment to the second pivotal linkage assembly. The fixture has a third pivotal linkage assembly pivotable about the pitch axis, and has a pair of chord actuators to apply axial load to the flexible aerodynamic member. The fixture minimizes deflections of a tip of the flexible aerodynamic member during testing to provide an improved accuracy of axial load measurement data.

Abstract: A test structure includes a frame, a shear reduction plate configured to couple to a first end of a test asset, and multiple rockers. Each rocker includes a first end that has a curved contact surface configured to contact the shear reduction plate and a second end having a connector movably coupled to the frame and configured to pivot, responsive to a bending moment applied to the test asset, such that the curved contact surface rocks in contact with the shear reduction plate.

Abstract: A test structure includes a frame, a shear reduction plate configured to couple to a first end of a test asset, and multiple rockers. Each rocker includes a first end that has a curved contact surface configured to contact the shear reduction plate and a second end having a connector movably coupled to the frame and configured to pivot, responsive to a bending moment applied to the test asset, such that the curved contact surface rocks in contact with the shear reduction plate.