Abstract: Provided is a method for determining access permission for a beamforming computing device communicating with a beamforming transceiver. The method includes obtaining, at an inter-zone sensor, location information from the beamforming computing device, wherein the inter-zone sensor is configured to monitor a location of the beamforming computing device; determining, by the inter-zone sensor, the location for the beamforming computing device based on the location information as the beamforming computing device nears a boundary between a first access zone and a second access zone; providing, by the inter-zone sensor, the location to a central control system; obtaining, by the inter-zone sensor, a command by the central control system that instructs the inter-zone sensor to communicate access instructions to a beamforming transceiver in the second access zone; and providing the access instructions to the beamforming transceiver.

Abstract: A method includes receiving a component history for a processor module, the component history including identities of host vehicles in a set of host vehicles in which the processor module was installed; receiving an operational history for the set of host vehicles for a time period the processor module was installed on the set of host vehicles; receiving indirect sensor measurements related to the set of host vehicles for the time period; receiving a part survival model that is based at least in part on a part status of a plurality of historical processor modules, the plurality of historical processor modules having a historical component history, a historical operational history, and historical indirect sensor measurements; and determining a survival probability of the processor module based at least in part on the component history, the operational history, the indirect sensor measurements, and the part survival model.

Abstract: A fire retardant (FR) composite composition, including a liquid polymer, wherein the liquid polymer includes a photopolymer including at least two of a first molecule, a second molecule, and a third molecule, a FR thermoset, and a photoinitiator.

Abstract: Decorative laminates including thermoplastic ink layers and related methods are disclosed. An example apparatus includes a reinforcing layer to provide a rigidity to a decorative laminate, thermoplastic ink applied to the reinforcing layer to form a decorative pattern of the decorative laminate, and a film layer coupled to the thermoplastic ink to form the decorative laminate. The film layer is to preserve the decorative pattern. The thermoplastic ink is solidified when the film layer is coupled to the thermoplastic ink.

Abstract: A system for taking into account micro wind conditions in a region. The system comprises a plurality of aerial vehicles within the region and a wind speed calculator. Each of the plurality of aerial vehicles has an altitude sensor and a GPS receiver. The wind speed calculator is configured to determine wind vectors within the region using measurements from the plurality of aerial vehicles.

Abstract: Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap and first and second actuators. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The first and second actuators are configured to move the flap relative to the fixed trailing edge. The first actuator is operatively coupled to the second actuator via a shaft. The first actuator is actuatable via pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the first actuator via a hydraulic module operatively coupled to the first actuator. The first actuator is configured to control movement of the second actuator via the shaft when the hydraulic system and the hydraulic module are functional. The second actuator is actuatable via an electric motor of the second actuator. The electric motor is selectively connectable to an electrical system of the aircraft.

Abstract: A method of making a ceramic composite comprises forming a wet ceramic composition comprising a plurality of discrete ceramic components and a fluxing agent dissolved in a solvent. At least a portion of the solvent is removed from the wet ceramic composition to form a dried ceramic composition comprising the plurality of discrete ceramic components coated with the fluxing agent. The dried ceramic composition is sintered to form the ceramic composite, the sintering being carried out at a sinter temperature sufficient to fuse the discrete ceramic components at bridging sites formed where two or more of the discrete ceramic components coated with fluxing agent are in physical contact.

Abstract: A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion includes one or more recesses in a first surface of the peripheral portion.

Abstract: A method, apparatus, and system for adjusting inertial reference data. The inertial reference data is received from an inertial reference unit in an aircraft. Replacement magnetic navigation data is determined for the aircraft at a current position of the aircraft. Magnetic navigation data in the inertial reference data is replaced with the replacement magnetic navigation data for the aircraft to form adjusted inertial reference data. The adjusted inertial reference data is sent to a number of aircraft systems that use the adjusted inertial reference data during operation of the aircraft.

Abstract: A flight control system for an aircraft is disclosed and includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a measured angle of attack that is based on a raw angle of attack and an estimated angle of attack based on a total pressure. The flight control system is further caused to compare the measured angle of attack with the estimated angle of attack to determine an error. In response to determining that the error between the measured angle of attack and the estimated angle of attack exceeds a threshold value, the flight control system determines the presence of a fault with an angle of attack value.

Abstract: An aircraft engine system has a turbofan engine with a lubricating oil system. An oil pump is connected to pump oil from the oil tank through a cooling circuit to the turbofan engine. The cooling circuit has a bleed air boosted engine oil cooler assembly with a liquid/air heat exchanger (LAHEX) connected to an oil inlet conduit and receiving fan air from a high bypass fan of the turbofan engine as the cooling working fluid. The LAHEX is connected to an oil exit conduit. An ejector downstream of the LAHEX receives bleed air from a compressor section of the turbofan engine. The ejector draws the fan air through the LAHEX.

Abstract: An applicator for applying a material over a fastener head, protruding from a non-horizontal surface of a part, comprises an enclosure and a daubing lever. The daubing lever passes through the wall of the enclosure and is movably coupled to the enclosure. The daubing lever comprises an actuation end, located on the outer side of the wall of the enclosure, a working end, located opposite the actuation end on the inner side of the wall of the enclosure, and an abutment portion, located at one of the actuation end, the working end, or between the actuation end and the working end. The applicator further comprises a biaser for imparting a moment on the daubing lever to bias the abutment portion of the daubing lever toward the enclosure.

Abstract: The present disclosure is generally directed to a primer saturated carrier medium assembly including a carrier medium having a front face and an opposing rear face, a primer saturating the carrier medium between the front face and the opposing rear face, and removable film impenetrable to the primer covering opposite faces of the carrier medium. A method of applying primer to a surface includes applying a face of a primer saturated carrier medium to contact a surface, and curing the primer saturated carrier medium on the surface. A structure includes a primer saturated medium including a carrier medium having a front face and an opposing rear face, and a primer saturating the carrier medium between the front face and the opposing rear face. The structure further includes a surface adhered to the primer on one face of the primer saturated medium.

Abstract: Disclosed herein is an attachment system, for providing a component mounting location, that comprises a laminated structure and a bracket. The bracket comprises an interface surface configured to interface with a first side of the structure, and a through hole open at the interface surface. A shear stud of the attachment system comprises a projection, shaped to pass through the hole of the structure and engage the through hole of the bracket, and a seal region, positioned to interface with a second side of the structure to form a seal with the second side of the structure. The attachment system additionally comprises a fastener comprising a head and a shaft, the shaft being shaped to pass through the through hole in the bracket and engage the shear stud to secure the shear stud relative to the bracket thereby reducing shear at the fastener.

Abstract: A method and system for an electrically switchable window system for an aerospace vehicle. The electrically switchable window system comprises electrically switchable windows and a window controller system connected to the electrically switchable windows. The window controller system receives a group of wireless signals from an onboard network system that controls systems in the aerospace vehicle and changes voltages applied to the electrically switchable windows when the group of wireless signals are received. The changes in the voltages change an amount of light passing through the electrically switchable windows.

Abstract: Systems and methods are provided for active vibration damping. One embodiment is a method for damping vibration in a mechanical system. The method includes detecting a vibration at a coupling of the mechanical system, generating a countervibration based on the detected vibration, and operating the mechanical system while generating the countervibration.

Abstract: A method, apparatus, and system for visualizing information. An augmented reality system comprises a computer system and a visualizer in the computer system. The computer system is in communication with unmanned vehicles using communications links. The visualizer system receives images of a physical object from the unmanned vehicles moving relative to the physical object and receive scan data for a region of the physical object from the unmanned vehicles. The visualizer creates an enhanced model of the physical object using the images and the scan data. The region of the physical object in the enhanced model has a greater amount of detail than the other regions of the physical object. The visualizer sends information to a portable computing device that is displayable by the portable computing device on a live view of the physical object. The information is identified using the enhanced model of the physical object.

Abstract: A rotorcraft has a frame and a plurality of rotors connected to the frame. The frame has a roll axis and a pitch axis. Each of the rotors includes a rotor shaft. The rotor shaft of each of the rotors is canted with respect to at least one of the roll axis and the pitch axis. The rotor shaft of each of the rotors may be canted between 3 and 15 degrees. Each of the rotors may be a co-axial co-rotating rotor. The rotors may be oriented in opposing pairs across the frame. Both rotors in each opposing pair rotate in the same direction. The rotorcraft may include at least two additional rotors, each having a forward cant. Each of the additional rotors may be a co-axial contra-rotating rotor.

Abstract: A method for assembly manufacturing including positioning a workpiece in an assembly position within an operational cell, positioning a fastening machine relative to the workpiece, wherein the fastening machine includes a robot frame comprising a throat, an assembly end effector coupled to the frame about the throat, and a plurality of linear actuators coupled to the frame, moving, by the plurality of linear actuators, the fastening machine about at least one of six degrees of freedom to receive at least a portion of the workpiece within the throat and position the assembly end effector relative to the workpiece, and performing, by the fastening machine, a fastening operation on the workpiece.