Disclosed herein are a system and method for producing paint templates for painting a design on a target surface. The system includes a processor configured to generate a geo-file of paint template designs. The processor includes a design module configured to parse the design into a set of paint sub-designs and a template design module configured to generate the geo-file of paint template designs based on the set of paint sub-designs. The generated geo-file of paint template designs includes a paint template design that corresponds to a paint sub-design. The system further includes a plotter configured to produce a set of paint templates based on the geo-file of paint template designs. Each paint template design includes a set of alignment marks and each paint template is produced with a set of alignment apertures corresponding to the set of alignment marks.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

The present invention is directed to an addition polymer comprising an addition polymer backbone; at least one moiety comprising a phosphorous acid group, the moiety being covalently bonded to the addition polymer backbone by a carbon-carbon bond; and at least one carbamate functional group. The present invention is also directed towards methods of making the addition polymer, aqueous resinous dispersions and electrodepositable coating compositions comprising the addition polymer, methods of coating a substrate and coated substrates.

The present invention relates to methods, computer program products and computing devices for calibrating a Digital Twin for an autonomous vehicle using machine learning and to the use of the calibrated Digital Twin to both tune at least one controller, navigation algorithms and/or guidance algorithms for an autonomous vehicle using machine learning and to optimising a vehicle shape of an autonomous vehicle using machine learning.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

A method of designing an aircraft shape of a supersonic aircraft according to an embodiment of the present invention includes: obtaining an equivalent cross-sectional area distribution of an initial shape at an off-track position of an aircraft; setting a target equivalent cross-sectional area distribution at the off-track position of the aircraft for reducing sonic booms on the basis of the obtained equivalent cross-sectional area distribution; and converting, on the basis of a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution, a required additional cross-sectional area of a cross-section of the aircraft on an off-track Mach plane that extends through an arbitrary position in an airflow direction into a required additional cross-sectional area of a cross-section of the aircraft on an on-track Mach plane of the aircraft that is located near the off-track Mach plane and adding the required additional cross-sectional area of the cross-section of the aircraft on the on-track Mach plane.

A method of designing an aircraft shape of a supersonic aircraft according to an embodiment of the present invention includes: obtaining an equivalent cross-sectional area distribution of an initial shape at an off-track position of an aircraft; setting a target equivalent cross-sectional area distribution at the off-track position of the aircraft for reducing sonic booms on the basis of the obtained equivalent cross-sectional area distribution; and converting, on the basis of a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution, a required additional cross-sectional area of a cross-section of the aircraft on an off-track Mach plane that extends through an arbitrary position in an airflow direction into a required additional cross-sectional area of a cross-section of the aircraft on an on-track Mach plane of the aircraft that is located near the off-track Mach plane and adding the required additional cross-sectional area of the cross-section of the aircraft on the on-track Mach plane.

Additive manufactured airframe structure having a plurality of additive manufactured airframe segments operable to be linked together in an assembled direction. Each of the plurality of additive manufactured airframe segments are separate from one another in an unassembled configuration. Plurality of reinforcement elements operable to be received in a receiving portion of the plurality of airframe segments and extending through the plurality of airframe segments in a normal direction. Receiving portion is located on the interior of a respective one of the plurality of airframe segments.

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.