In one aspect, there is a composite skin for a tiltrotor aircraft including a first skin having a periphery defined by a forward edge, an aft edge, and outboard ends; a second skin; and a honeycomb core disposed between the first skin and the second skin, the honeycomb core comprised of a plurality of honeycomb panels positioned along the longitudinal axis of the first skin, the plurality of honeycomb panels having an array of large cells, each cell having a width of at least 1 cm; wherein the second skin and the honeycomb core have an outer perimeter within the periphery of the first skin.

A cargo handling system is disclosed. In various embodiments, the system includes a wireless mobile maintenance display unit; a line replaceable unit; a data device configured to provide an operational status data concerning the line replaceable unit to the wireless mobile maintenance display unit; a first server configured to store a catalog of parts for repairing the line replaceable unit; and a system controller configured to communicate with a source of replacement parts for the line replaceable unit.

A cargo handling system is disclosed. In various embodiments, the system includes a wireless mobile maintenance display unit; a line replaceable unit; a data device configured to provide an operational status data concerning the line replaceable unit to the wireless mobile maintenance display unit; a first server configured to store a catalog of parts for repairing the line replaceable unit; and a system controller configured to communicate with a source of replacement parts for the line replaceable unit.

A method of designing a morphable aerodynamic surface includes discretizing and parameterizing a model of a morphable surface to create a function to optimize; utilizing finite element analysis to solve for displacements and associated errors at an initialization point; and iteratively calculating a gradient cost function, define step size and search direction, step according to defined step size and search direction, and recalculate displacements and associated errors to converge on final thickness vector.

A method of designing a morphable aerodynamic surface includes discretizing and parameterizing a model of a morphable surface to create a function to optimize; utilizing finite element analysis to solve for displacements and associated errors at an initialization point; and iteratively calculating a gradient cost function, define step size and search direction, step according to defined step size and search direction, and recalculate displacements and associated errors to converge on final thickness vector.

An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.

An aircraft propulsion system comprises a propulsor, a motor and a reduction gearbox coupled to a prime mover at an input side, and the propulsor at an output side. The reduction gearbox is configured to provide a reduction ratio between the input and output. The reduction gearbox is configured such that the input side rotates in an opposite direction to the output side, and the prime mover, motor, propulsor and reduction gearbox are configured such that gyroscopic forces of the propulsor, motor, prime mover and reduction gearbox generated during aircraft manoeuvres and/or propulsion system failures are substantially cancelled.

A high-volume low-pressure end effector is presented. The high-volume low-pressure end effector comprises a connection arm and a spray head. The connection arm comprises a housing with flexible conduits running through the housing. The spray head has integral channels configured to receive air and a fluid from the flexible conduits and deliver the air and the fluid to a number of outlets.

A high-volume low-pressure end effector is presented. The high-volume low-pressure end effector comprises a connection arm and a spray head. The connection arm comprises a housing with flexible conduits running through the housing. The spray head has integral channels configured to receive air and a fluid from the flexible conduits and deliver the air and the fluid to a number of outlets.

A method for positioning a ram air turbine during its assembly on a primary structure of an aircraft. The method includes the steps of: placing a first distance sensor on a first element among a first flap and the ram air turbine, a second distance sensor on a second element among a second flap and the ram air turbine, the first and second distance sensors being configured to respectively emit first and second signals corresponding to measured values over time of a distance between each of the first and second distance sensors and at least one mobile target attached to the ram air turbine or the first and second flap, pivoting the mast between the retracted and deployed positions, analyzing the first and second signals, and, if necessary, repositioning the ram air turbine according to the step of analyzing the first and second signals.