Abstract: Apparatus and methods provide for the exchange of heat in a cross flow heat exchanger having heat exchanger sub-chambers in an inline configuration. According to embodiments described herein, the heat exchanger sub-chambers may be arranged in an inline configuration, where two or more of the sub-chambers are positioned generally along a linear axis. In further configurations, to accommodate the linear configuration of two or more sub-chambers, inlet fluid flows to subsequent or downstream sub-chambers are directed to the sub-chambers using bypasses around the upstream or prior sub-chambers. Various configurations may reduce or minimize pressure losses of one or more of the fluids moving through the heat exchanger.

Abstract: A system and method for selecting and installing a software configuration for an aircraft. A configuration tool is configured to display configuration options for aircraft software to a user and to receive configuration selections for the aircraft software from the user. The configuration selections identify selected ones of the configuration options. The configuration tool is further configured to send the configuration selections to a software installer for installation on the aircraft of the aircraft software identified by the configuration selections.

Abstract: Technologies for detecting a passive object through the use of frequency diversity to find at least a resonant peak are disclosed. For example, a radar system may illuminate a suspect area with a pulsed radio wave based on a large number of frequency bands and based on parameters associated with the passive object. The reflected radio wave may be processed to generate synthetic aperture radar (SAR) maps associated with the frequency bands. The SAR maps may be analyzed and compared to determine large deviation amplitudes that may indicate a location of the passive object.

Abstract: There is provided a method of training a shape memory alloy (SMA) workpiece. The method includes applying a force couple to a shape memory alloy (SMA) workpiece to impart a generally planar transformational behavior to the SMA workpiece to obtain a trained shape memory alloy (SMA) workpiece.

Abstract: An electromagnetic shielding assembly may include a transparent substrate layer and a transparent active layer positioned with respect to the substrate, wherein the active layer is configured to absorb electromagnetic radiation having a first wavelength and emit electromagnetic radiation having a second wavelength, the second wavelength being different than the first wavelength, the active layer includes fluorescent molecules combined with a base material, the fluorescent molecules being configured to absorb electromagnetic radiation having the first wavelength and emit the electromagnetic radiation having the second wavelength, wherein the first wavelength is in a visible electromagnetic spectrum and the second wavelength is in a non-visible electromagnetic spectrum.

Abstract: A veil-stabilized composite may include at least one reinforcing layer, the reinforcing layers being formed of a reinforcing material, a plurality of interlayers disposed alternately between and bonded to the reinforcing layers, each of the interlayers being formed of an interlayer material having a first distortional-deformation capability, and a matrix material infused in the reinforcing layers and the interlayers, the matrix material having a second distortional-deformation capability, wherein the first distortional-deformation capability is greater than the second distortional-deformation capability to increase tensile strength of the composite.

Abstract: There is provided in an embodiment a composite radius filler for a composite structure. The composite radius filler has two or more radius laminates. Each radius laminate has a laminate of stacked composite plies formed in a desired radius with a desired radial orientation of the stacked composite plies substantially matching a radial orientation of adjacent stacked composite plies of a composite structure surrounding the two or more radius laminates. Each radius laminate is preferably trimmed to have at least one side align adjacent to the others to form a composite radius filler having a shape substantially corresponding to a radius filler region of the composite structure.

Abstract: A thermal seal may include a flexible insulation layer, and an element made of shape memory alloy attached to the insulation layer, the element being treated to bend in response to heating, whereby an increase in the temperature of the element causes the insulation layer to transform from a first configuration to a second configuration.

Abstract: Composite components are joined together by an amorphous thermoplastic film forming a fused thermoplastic joint between the components. Fusion of the film may be achieved at relatively low temperatures that are sufficient to cure thermoset composite components, but are below the melting point of semi-crystalline thermoplastic components.

Abstract: An unmanned aquatic surface vehicle for detecting and locating hazards is disclosed. The vehicle includes a propulsion system configured to impart a propulsive force to the vehicle and a steering system configured to impart a change in the direction of travel of the vehicle. A navigation system may be included to detect the location, direction, and motion of the vehicle. A hazard detection system is configured to detect and locate at least one of a subsurface, surface or above-water hazard. A communications device configured to transmit hazard data associated with a detected hazard to a remote receiver. A control station is able to control the vehicle, and receive and display information about hazards detected by the unmanned aquatic surface vehicle.

Abstract: A winglet attach fitting may include a wing attachment portion, an upper winglet attachment portion, and a lower winglet attachment portion. The upper winglet attachment portion may be coupled to the wing attachment portion and may be configured to support an upper winglet. The lower winglet attachment portion may be coupled to the wing attachment portion and may be configured to support a lower winglet. The wing attachment portion may be removably attachable to a wing tip using fasteners.

Abstract: A system and method for placing a structure in a design for an interior of an aircraft. An initial placement for the structure is received by a processor unit. A suggested placement for the structure is identified by the processor unit from a number of structure placement engineering designs in an engineering design database for the aircraft using the initial placement. The suggested placement for the structure is displayed by the processor unit.

Abstract: A method of manufacturing is provided comprising forming a mounting plate adaptable to a plurality of models of aircraft, forming an adapter plate configured for use with the mounting plate, forming a radome configured to attach to the mounting plate, configuring a shape of the adapter plate to encompass at least one footprint of at least one antenna, and providing a plurality of hole patterns through the adapter plate corresponding to known hole patterns of the at least one antenna.

Abstract: There is provided in an embodiment an airfoil. The airfoil has one or more fuel containment regions disposed in the airfoil and one or more continuously curved spars extending from a root end of the airfoil toward a tip end of the airfoil. At least one continuously curved spar has a unitary configuration, has one or more continuous curves along the continuously curved spar, and either has a portion forming a structural wall of at least one of the one or more fuel containment regions, or, is internal to the one or more fuel containment regions.

Abstract: A vacuum barrier system for curing a composite part may include a bag carrier and a compliant, relatively thin film bladder formed over the bag carrier to function as a vacuum barrier. The bag carrier may be configured complementary to the composite part. The bladder may seal the bag carrier therewithin.

Abstract: A tooling system may include an outer mold line (OML) tool and one or more inner mold line (IML) tools. The OML tool may have an OML tool surface. Each one of the IML tools may have an IML tool surface and may be receivable within the OML tool 202. Each IML tool may be formed of expandable material. Each IML tool may apply an internal compaction pressure to a composite assembly positioned between the OML tool surface and the IML tool surface when the expandable material is heated.

Abstract: A method and apparatus for processing a signal. The signal is received in a receiver system in a satellite. The signal has a range of frequencies in which information is carried in a number of channels having a number of frequencies within the range of frequencies. The number of frequencies for a channel in the number of channels changes within the range of frequencies over time. The signal is transmitted using a transmitter system in the satellite. The signal is unprocessed to identify the number of frequencies for the channel used to carry the information by the satellite.

Abstract: A method and apparatus for processing a signal is present. Information is carried in a frequency hopping signal. The frequency hopping signal is sent to a gateway in a communications network through a satellite. The frequency hopping signal is unprocessed by the satellite to identify the information in the frequency hopping signal.

Abstract: A system for connecting two relatively movable structures on an aircraft, comprising: a first rigid structure attached to one of the relatively movable rigid structures; a second rigid structure attached to another of the relatively movable structures; a flexible skin connected to the first and second rigid structures; a sleeve comprising first and second end portions; a first rod comprising a first end portion attached to the first rigid structure, a second end portion slidably coupled to the first end portion of the sleeve, and an intermediate portion made of shape memory alloy; a second rod comprising a first end portion attached to the second rigid structure, a second end portion slidably coupled to the second end portion of the sleeve, and an intermediate portion made of shape memory alloy; and means for heating at least the intermediate portions of the first and second rods.

Abstract: An electromagnetic energy protection system and method disclosed herein that includes a plurality of conductive sheets ohmically connected by conductive interconnects. The conductive interconnects can be metal formed by a metal deposition process. The metal deposition process can include a plasma deposition process. The conductive interconnects can help prevent the formation of surface deformities such as bumps that may be caused when connecting, either physically or electrically, adjacent conductive sheets.