Abstract: An aircraft includes a first electrical connector configured to couple with a first power cable, a first data communication network and a first modem coupled to first electrical connector and first data communication network and is configured to transmit data received at first electrical connector through first power cable to first data communication network and to transmit data from first data communication network to first power cable through first electrical connector. The aircraft additionally includes a second electrical connector configured to couple with a second power cable, a second data communication network and a second modem coupled to second electrical connector and to second data communication network and is configured to transmit data received at second electrical connector through second power cable to second data communication network and to transmit data from second data communication network to second power cable through second electrical connector.

Abstract: A method and apparatus for managing movement. A navigation system comprises a first inertial measurement unit enabled global positioning system device having a first inertial measurement unit with a first level of accuracy in a first vehicle and is configured to provide first information that identifies a position of the first vehicle relative to a second vehicle. The navigation system further comprises a second inertial measurement unit enabled global positioning system device in the first vehicle having a second inertial measurement unit with a second level of accuracy that is greater than the first level of accuracy and is configured to provide second information that identifies the position of the first vehicle relative to the second vehicle. The navigation system further comprises a controller that is configured to perform an action based on a desired level of accuracy of the first information.

Abstract: A stiffened composite panel is fabricated using modular tooling. Composite pre-preg is laid up and formed over forming block modules each of which is assembled by co-linearly arranging a plurality of forming block segments. The formed stiffeners are respectively transferred to individual cure tool modules that are assembled by co-linearly arranging a plurality of cure tool module segments. The stiffeners are assembled by arranging the cure tool modules side-by-side, and a composite skin is placed on the assembled stiffeners. The panel is vacuum bagged using a segmented vacuum bag.

Abstract: Systems and methods for compacting a charge of composite material. These systems and methods may utilize a vacuum compaction device to compact the charge of composite material on a supporting surface. The vacuum compaction device may be reusable and may be configured to define an enclosed volume when positioned on the supporting surface and may include a barrier structure and a sealing structure that is configured to form a fluid seal when compressed between the supporting surface and the barrier structure. The vacuum compaction device also may include a vacuum distribution manifold that is in fluid communication with and configured to selectively apply a vacuum to the enclosed volume. Application of the vacuum to the enclosed volume may decrease a pressure within the enclosed volume and transition the vacuum compaction device from an undeformed configuration to a deformed configuration, thereby compacting the charge of composite material on the supporting surface.

Abstract: Flexible material transfer devices, flexible vacuum compaction devices that include the flexible material transfer devices, flexible vacuum chucks that include the flexible vacuum compaction devices, and systems and methods including the same. The flexible material transfer devices include a flexible substrate that is configured to selectively and repeatedly transition between a stowed conformation and a deployed conformation. The flexible substrate defines a material contacting surface that is configured to contact a charge of composite material and to selectively and operatively attach to the charge of composite material. The flexible substrate further defines a plurality of retention conduits that are at least partially defined by the material contacting surface and are configured to have a retention vacuum applied thereto. The flexible material transfer device further includes a retention manifold that provides fluid communication between the plurality of retention conduits and a vacuum source.

Abstract: A method and system for communication with a mobile platform is provided. An antenna system coupled to a transmitter for use in providing a communication channel to a mobile user includes a first linear transmit array of radiating horns, a second linear transmit array of radiating horns, and at least one reflector coupled to at least one of the first linear transmit array and the second linear transmit array, the at least one reflector configured to reflect illumination from the first and second linear transmit arrays to form a communication channel for the mobile user.

Abstract: An apparatus and method for installation of a frame assembly to a body may include a tooling assembly configured to support a frame assembly, the tooling assembly being positioned with respect to a body, wherein the frame assembly is positioned with respect to the body at a plurality of predetermined engineering locations.

Abstract: A plurality of fasteners is installed in an aerodynamic surface of an aircraft. Holes for shanks of the fasteners and countersinks for heads of the fasteners are drilled. The countersinks are drilled at an included angle between 100 and 180 degrees. Fasteners having a ratio of head-to-shank diameter of less than 2.0 are installed.

Abstract: A method for inspecting a composite structure includes acquiring an image of the composite structure. The composite structure includes at least a first ply and a second ply adjacent the first ply. The method also includes transforming the image into a binary image, and determining a first boundary line between the first ply and the second ply. The method further includes characterizing an irregularity in the composite structure based at least partially on the first boundary line.

Abstract: Methods and apparatus to determine aircraft flight conditions are disclosed herein. An example apparatus disclosed herein includes a gaseous packet generator to generate a gaseous packet adjacent an aircraft. The example apparatus also includes a sensor array disposed on the aircraft to acquire information related to the gaseous packet. The example apparatus further includes a processor to determine at least one of a first characteristic of air flowing along the aircraft or a second characteristic of the aircraft based on the information.

Abstract: In one embodiment, the disclosed vortex generator may include a flap, a bearing configured to be mounted on a surface, an axle retained in the bearing, the flap attached to the axle such that the flap rotates relative to the bearing about the axle, and an actuator made of a shape memory alloy attached to the flap and to a support, the actuator shaped to receive the axle therethrough, such that a change in temperature of the actuator causes the actuator to rotate the flap relative to the bearing.

Abstract: A method and apparatus for visualizing an assembly of parts for an aircraft. A shop order instance is identified for the assembly of parts for the aircraft. A volume is identified for the shop order instance. The assembly of parts is displayed within the volume in context with a number of assemblies of other parts within the volume.

Abstract: Apparatus and methods provide for a configurable tray table and method of configuring a tray table. According to aspects of the disclosure, a tray table includes a support assembly and a tray assembly. The support assembly is configured to connect to a structure. The tray assembly is coupled to the support assembly and is configurable between coplanar and multi-planar tray configurations. The tray assembly includes a number of tray table segments pivotally coupled to one another.

Abstract: A method and apparatus for controlling a flow of a fluid through a valve. In one illustrative embodiment, an apparatus comprises an elongate member, an actuation device, and a valve body. The actuation device is configured to move the elongate member, which may be associated with the actuation device, between an open position and a closed position. The valve body is configured for attachment to the actuation device such that the elongate member is positioned within the valve body. Fluid that flows into the valve body from a fluid source is allowed to flow out of the valve body when the elongate member is in the open position.

Abstract: A method and apparatus is provided for adjusting a latch. An apparatus comprises a latch body, a first member, and a second member associated with the latch body. A receiving area extends through at least a portion of the latch body. The first member is configured to be at least partially received within the receiving area of the latch body. The first member has a first coupling element. The second member has a second coupling element. Movement of the first member along an axis through the receiving area changes a distance between the first coupling element and the second coupling element.

Abstract: A pump including a cylinder body having first and second ends and a cylinder bore, a plug shaft including first and second ends and a plug shaft bore, wherein the first end of the plug shaft is fixed relative to the cylinder body, and wherein the second end of the plug shaft includes a stop, a first piston received within the cylinder bore to partially bound a first gas chamber and a hydraulic fluid chamber, the first piston being received over the plug shaft and axially moveable relative to the plug shaft, a socket shaft including first and second ends and a socket shaft bore, the socket shaft bore being configured to sealingly receive the plug shaft, a second piston received within the cylinder bore to partially bound a second gas chamber and the hydraulic fluid chamber, the second piston being connected to the socket shaft.

Abstract: An induction heating system for manufacturing a part including an induction coil and a smart susceptor positioned within an oscillating electromagnetic field from the induction coil. The smart susceptor includes a ferromagnetic material cold sprayed onto a tool. The tool may be a sheet metal component formed to a desired shape by incremental sheet forming. The smart susceptor may be heated up by eddy currents generated in the ferromagnetic material by the oscillating electromagnetic field. The smart susceptor may be designed to have a desired Curie temperature based on the composition of the ferromagnetic material. The smart susceptor is formed into a desired shape by cold spraying ferromagnetic material onto a tool already formed into the desired shape. The smart susceptor may be removed from the tool by thermally shocking the smart susceptor and the tool and may be used to heat a part to be formed.

Abstract: An apparatus for aligning an inner collar associated with a bearing incorporates a base member with a first member extending substantially perpendicular from the base member and a second member also extending substantially perpendicular from the base member, substantially parallel with said first member with a defined distance between the first and second member. The first member and the second member form opposing sides defined by a semi-circular contour formed therein such that the first member and the second member are operable to engage an inner collar of a bearing in a snap-fit engagement on opposite sides of the bearing such that the inner collar is maintained in a substantially orthogonal orientation with respect to walls of a structure in which the bearing has been mounted.

Abstract: A system for distortional clamping of a flexible member may include a dimensional reader and a positioning fixture. The dimensional reader may have a plurality of reader pogos that may be axially movable into contacting relation with a detail to measure a detail contour. The positioning fixture may have a plurality of positioning pogos and at least one clamping finger configured to mechanically clamp a flexible member between the positioning pogos and the clamping finger. The positioning pogos may be axially movable to deflect the flexible member into a contour that may be complementary to the detail contour.

Abstract: An avionics system allows aircraft to introduce bogus “ADS-B Out” messages that are recognized as false only by authorized users. The system enables aircrafts flying at low altitudes to prevent misuse of their ADS-B Out information by maliciously operated cyber and physical attack tools. Aspects of the illustrative embodiment include the system architecture, including an Airborne ATC Processor and Ground ATM System Processor; a process employed by aircraft for generating authorized bogus ADS-B Out messages; a process employed by aircraft for transmitting authorized bogus ADS-B Out messages; and a process employed by air traffic control and other aircraft for decoding the authorized bogus ADS-B Out messages.