Abstract: An automated air-to-air refueling (A3R) system is usable with a tanker aircraft having a refueling boom. The system includes a camera connected to the tanker in proximity to the refueling boom which outputs a video stream of the boom and a fuel-receiving aircraft/receiver during an aerial refueling process. The system also includes a human-machine interface (“HMI”) located aboard the tanker, and an electronic control unit (“ECU”) in communication with the camera and HMI. The ECU identifies keypoints on the receiver indicative of flight control surfaces thereof, tracks corresponding positions of the flight control surfaces in real-time, and predicts a change in position of the receiver in free space as a predicted 3D position using the corresponding positions. The HMI also outputs a directional indicator indicative of the predicted 3D position, e.g., as a graphical overlay to a display screen.

Abstract: A manufacturing method that includes additively manufacturing a part from an additive manufacturing feedstock comprising a titanium alloy, the titanium alloy comprising: 5.5 to 6.5 wt % aluminum; 3.0 to 4.5 wt % vanadium; 1.0 to 2.0 wt % molybdenum; 0.3 to 1.5 wt % iron; 0.3 to 1.5 wt % chromium; 0.05 to 0.5 wt % zirconium; 0.2 to 0.3 wt % oxygen; maximum of 0.05 wt % nitrogen; maximum of 0.08 wt % carbon; maximum of 0.25 wt % silicon; and balance titanium, wherein a value of an aluminum structural equivalent [Al]eq ranges from 7.5 to 9.5 wt %, and is defined by the following equation: [ Al ] ? eq = [ Al ] + [ O ] × 10 + [ Zr ] / 6 , and wherein a value of a molybdenum structural equivalent [Mo]eq ranges from 6.0 to 8.5 wt %, and is defined by the following equation: [ Mo ] ? eq = [ Mo ] + [ V ] / 1 .5 + [ Cr ] × 1 . 2 ? 5 + [ Fe ] × 2 . 5 .

Abstract: An optical high-power amplifier (“OPHA”) circuit, e.g., for a spaceborne satellite-based communication network, includes fiberoptic gain and polarization maintenance (“PM”) stages, a polarization splitter, first and second photodetectors, and an electronic control unit (“ECU”). The gain stage outputs an amplified optical signal in response to a low-power (“LP”) optical input signal. The PM stage outputs separate high and low power output signals in response to the amplified signal. A majority of power of the input signal is allocated to the HP output signal. The polarization splitter transmits the LP output signal along the slow and/or fast polarization axis. The photodetectors are arranged on the slow and fast axes. The ECU outputs a polarizer control signal to a polarization rotator device in response to electrical signals from one or both photodetectors to command the rotator device to output the LP optical input signal with a targeted polarized output state.

Abstract: A method for determining fatigue properties of a structure includes mounting the structure in a load frame. The structure has a crack with a crack size. The method includes applying repeatedly an adjustable stimulus to the structure over multiple cycles. The adjustable stimulus is an adjustable load or an adjustable displacement applied to the structure. The method further includes storing the crack size at a start of the cycles, measuring a response of the structure subjected to the adjustable stimulus in each cycle, updating the crack size based on the response in each cycle, and updating the adjustable stimulus in each cycle. The adjustable stimulus as updated maintains a strain energy release rate approximately constant based on the crack size. The method includes calculating a growth rate of a crack propagation in the structure based on the response in each cycle, and storing the growth rate in a file.

Abstract: A system and method for an overwing exit door is provided. The overwing exit door system comprises a door, a handle connected to an inboard surface of the door, a guide track connected to a body of the aircraft, a roller, a first crank connected to the roller and associated with the handle, a first shaft system attached to the first crank, a latch system connected to the first shaft system, and a locking system associated with the latch system. The latch system comprises a rotating stop, a second crank associated with the rotating stop, and a second shaft system connected to the second crank and the rotating stop. These components together control operation of the overwing exit door between an open position and a closed position.

Abstract: Methods and apparatus for manufacturing a thermoplastic structure include laying a first plurality of braided plies on a mandrel, and laying one or more unidirectional plies on the plurality of braided plies. A second plurality of braided plies is laid on the one or more unidirectional plies. The layup thereby forms a thermoplastic structure having combined braided and unidirectional plies.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.

Abstract: Disclosed herein is a transverse tensioning system that comprises a left-side clamping assembly comprising a first left-side clamp element and a second left-side clamp element. The first left-side clamp element and the second left-side clamp element clamp down on the left edge portion of the stack of plies when the stack of plies moves in a feed direction and is shaped between opposing dies. The system also comprises a right-side clamping assembly, spaced apart from the left-side clamping assembly and comprising a first right-side clamp element and a second right-side clamp element. The first right-side clamp element and the second right-side clamp element clamp down on the right edge portion of the stack of plies when the stack of plies moves in the feed direction and is shaped between the opposing dies.

Abstract: Disclosed is a method of forming a composite door. A precursor frame sheet, comprising flaps, is formed by cutting a prepreg sheet. The precursor frame sheet is draped over a door-forming tool, comprising a frame face and flap supports, non-parallel to the frame face, such that each of the flaps of the precursor frame sheet is geometrically complementary with a corresponding one of the flap supports. A composite frame is formed by curing the precursor frame sheet, draped over the door-forming tool, wherein the composite frame comprises a first rail and a second rail. The composite frame is separated from the door-forming tool. The composite frame, first composite edge fittings, second composite edge fittings, a first composite side beam, a second composite side beam, and a composite skin are interconnected.

Abstract: A process for additive manufacture of an article comprises conveying a material through a heated nozzle to form a flowing mass of the material. The material comprises a polymer matrix including a plurality of polymeric chains and an alignment additive dispersible within the polymer matrix. The alignment additive is configured to align the plurality of polymeric chains in a flow direction of the flowing mass of the material. The process further comprises aligning at least a portion of the polymeric chains, via the alignment additive, along a direction of flow through the heated nozzle, releasing the flowing mass of the material from the heated nozzle, and allowing the material to solidify.

Abstract: A system for removing a panel insert from a panel includes a main housing. A loading cap is coupled to the main housing. A tension knob is coupled to the main housing. The tension knob is configured to couple to a puller rod. A tension spring is within the main housing. The loading cap is configured to set the tension spring at an initial tension. The tension knob is configured to set the tension spring at a subsequent tension. A heater is configured to apply heat to the panel insert.

Abstract: There is provided a forming apparatus for constraining a composite charge and forming the composite charge into a highly contoured composite structure. The forming apparatus includes a first die and a second die between which the composite charge is formed. The first die has pairs of first die portions spaced apart to define a die cavity into which the composite charge is formed into a contoured hat section having a cap. The forming apparatus includes a constraining assembly having a constraining device positioned in the die cavity. The constraining device is designed to constrain a cap portion, and to apply an upward resistive force against the cap portion, and against a downward compressive force applied by the second die, to provide wrinkle prevention in the cap as the contoured hat section is formed. The constraining assembly has a retaining element to retain the constraining device.

Abstract: An access system for a vehicle includes a door moveably coupled to a portion of a fuselage. The door is configured to be moved between an open position in which an opening of an internal chamber is opened, and a closed position in which the opening of the internal chamber is closed. One or more actuators are secured to the door. The one or more actuators are configured to move the door between the open position and the closed position.

Abstract: Methods and systems for a steerable antenna array are disclosed. The antenna array includes an array of antenna elements aligned in rows and columns on a substrate. Additionally, the antenna array includes a microstrip feed within the substrate, where the feed is configured to electromagnetically couple to each antenna element of the array of antenna elements. The antenna array further includes a ground plane within the substrate. Additionally, for each antenna element, the antenna array includes a first cavity disposed between the ground plane and feed, and a second cavity disposed on the other side of the ground plane from the first cavity. The antenna array further includes a plurality of fluid lines configured to selectively add or remove fluid from the cavities coupled to the fluid line and cause a deflection of the ground plane in a region of the cavities coupled to the fluid line.

Abstract: A fastener accessory includes a fastener body and a sacrificial radio frequency (RF) tag. A dielectric substrate of the tag is affixed to a contact surface of the fastener body. An RF antenna trace is connected to or printed on the substrate. The antenna trace transmits an RF response signal when energized by an external RF tracking circuit. The substrate is plastically deformed by an installation force to prevent transmission of the response signal. A method for locating the fastener body within a search area includes exciting a receiver trace of the tag using an interrogation signal, frequency-modulating an interrogation frequency using an RF modulating circuit, transmitting a response signal at a response frequency via a transmitting antenna trace of the tag, and detecting the response signal using an RF tracking circuit to locate the fastener body within the search area.

Abstract: The present disclosure provides a solar cell module, comprising (a) a laminate substrate having a first surface and a second surface opposite the first surface, (b) a solar cell positioned on the first surface of the laminate substrate, (c) a first contact pad positioned on the first surface of the laminate substrate adjacent to the solar cell, (d) a second contact pad positioned on the second surface of the laminate substrate, (e) one or more vias positioned through the laminate substrate to electrically connect the first contact pad to the second contact pad, and (f) one or more interconnects extending from the solar cell and electrically coupling the solar cell to the first contact pad.

Abstract: Systems and methods for enabling charged (ionized) air mass measurement for reliable air data computation onboard an aircraft. Ionic charge sensing may be used to derive air data having improved reliability. The systems and methods for ionic charge sensing employ an emitter electrode and two or more collector electrodes, which electrodes are disposed in proximity to the exterior skin of the aircraft and exposed to ambient air. The emitter electrode is positioned forward of the collector electrodes. The system further includes a solid-state ionic air data module that converts currents from the collector electrodes into air data parameter values. More specifically, the ionic air data module is configured to sense currents induced in the collector electrodes in response to corona discharge produced by the high-voltage emitter electrode.

Abstract: Systems and methods inspect a fastener installed at least partially through a hole in a part, by measuring fastener concentricity, measuring fastener flushness with a surface, and/or detecting foreign object debris near the fastener. Systems include an x-ray imaging system, a first camera device, a second camera device, a first support structure, and at least one processing unit. The first camera device produces a first image of the fastener from a first vantage point, and the second camera device produces a second image of the fastener from a second vantage point, such that a 3D image of the fastener can be created from the first image and the second image. The system inspects the fastener based on the x-ray image and/or the 3D image, to determine concentricity and/or flushness of the fastener. Systems may be automated and mounted on robot arms to be positioned relative to the fasteners being inspected.

Abstract: Visual inspection methods, systems, and apparatuses are presented for the in situ visual inspection of aircraft cabin windows installed in an aircraft from within an aircraft cabin, and where access and ability to visually inspect such aircraft cabin windows is otherwise restricted by placement of aircraft cabin fixtures blocking ordinary viewing of such aircraft cabin window from within an aircraft cabin. The visual inspection is conducted by activating an image capturing device of a personal electronic device incorporated into or otherwise in communication with an aircraft cabin fixture positioned adjacent to an aircraft cabin window.

Abstract: A method for forming a semiconductor structure. Two isolation structures are formed in a semiconductor. A cavity is etched in the semiconductor between the two isolation structures in the semiconductor. Dopants are implanted into a bottom side of the cavity to form a doped region in the semiconductor below the cavity between the two isolation structures. A contact is formed in the cavity. The contact is on the doped region and in direct contact with the doped region.