Abstract: A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.

Abstract: An article-forming tool comprises an elongate jig having a predefined shape, an elongate flexible vise configured to hold a fiber-composite article of a predefined cross section, and a spacer system. The vise opposes the jig; it includes a series of clamp segments and a flexible spline sheet configured to conform controllably to the shape of the jig. The clamp segments are arranged side-by-side along a length of the vise, each clamp segment comprising a set of platens configured to hold a corresponding longitudinal segment of the article. The flexible spline sheet extends through the series of clamp segments, between opposing platens. The spacer system is configured to control the conformation of the spline to the shape of the jig.

Abstract: A cargo loading system includes a drive unit extending along a length of a cargo area of an aircraft. The drive unit is configured to couple to a modular cargo structure via a handling member and to convey one or more cargo items coupled to the modular cargo structure. The cargo loading system further includes a rotation device and a driver. The rotation device is in contact with the drive unit. The driver is configured to apply torque to the rotation device to cause the drive unit to move the modular cargo structure within the aircraft.

Abstract: A fuselage is described that includes a plurality of frames and a plurality of seat rows spaced apart according to a seat pitch. Each frame includes a lateral floor beam, and each seat row of the plurality of seat rows includes a load-bearing structural base with a plurality of legs attached to a proximal lateral floor beam and a distal lateral floor beam. Each seat row also includes a seat or bank of seats attached to the load-bearing structural base, where the seat or bank of seats includes at least one seat bottom and at least one seat back. Further, each seat row includes an interface between (i) the load-bearing structural base and (ii) the seat or bank of seats to allow for attachment and detachment of the seat or bank of seats relative to the load-bearing structural base.

Abstract: A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.

Abstract: A cargo loading system includes a drive unit extending along a length of a cargo area of an aircraft. The drive unit is configured to couple to a modular cargo structure via a handling member and to convey one or more cargo items coupled to the modular cargo structure. The cargo loading system further includes a rotation device and a driver. The rotation device is in contact with the drive unit. The driver is configured to apply torque to the rotation device to cause the drive unit to move the modular cargo structure within the aircraft.

Abstract: A system for testing mechanical properties of a test specimen includes a first climate controlled enclosure and a mechanical tester configured to apply a load to a test specimen within the first climate controlled enclosure. The system also includes a second climate controlled enclosure proximate to a view port of the first climate controlled enclosure. The second climate controlled enclosure is configured to enclose a camera, and the camera is configured to capture image data representing the test specimen. The image data includes multiple images that enable measurement of distortion of the test specimen responsive to the load.

Abstract: A system for testing mechanical properties of a test specimen includes a first climate controlled enclosure and a mechanical tester configured to apply a load to a test specimen within the first climate controlled enclosure. The system also includes a second climate controlled enclosure proximate to a view port of the first climate controlled enclosure. The second climate controlled enclosure is configured to enclose a camera, and the camera is configured to capture image data representing the test specimen. The image data includes multiple images that enable measurement of distortion of the test specimen responsive to the load.

Abstract: A fuselage is described that includes a plurality of frames and a plurality of seat rows spaced apart according to a seat pitch. Each frame includes a lateral floor beam, and each seat row of the plurality of seat rows includes a load-bearing structural base with a plurality of legs attached to a proximal lateral floor beam and a distal lateral floor beam. Each seat row also includes a seat or bank of seats attached to the load-bearing structural base, where the seat or bank of seats includes at least one seat bottom and at least one seat back. Further, each seat row includes an interface between (i) the load-bearing structural base and (ii) the seat or bank of seats to allow for attachment and detachment of the seat or bank of seats relative to the load-bearing structural base.

Abstract: The invention provides an X-ray device for controlling a DC-AC converter, wherein the DC-AC converter is adapted for supplying a resonant circuit and a transformer (105) of a computer tomography gantry (91) with electrical energy, wherein the gantry comprises a rotary part (93) and a stationary part (92), wherein the transformer (105) is adapted for providing a current, feeding a high voltage rectifier circuit (106), providing an output voltage (107), the X-ray device comprises a detector for detecting the output voltage, a predictor (501) for calculating a first output with the use of processing the output voltage (107), wherein the first output represents the change of the output voltage (107) for the possible states of the DC-AC converter (102), a control loop (503) for calculating the required change of the output voltage (107) with the use of processing the output voltage (107) and the target specification, a decision block (502) for calculating a control value with the use of processing the first output