Abstract: A vapor cycle compressor includes a motor section and a compression section operatively engaged with the motor section. A refrigerant path is in the motor section and in the compression section. The refrigerant path includes: a compression refrigerant path, for a single phase compression refrigerant, in the compression section; an inner rotor shaft refrigerant path, for a single phase inner rotor shaft refrigerant, in the compression section and in the motor section; and a stator refrigerant path, for a two phase stator refrigerant, in the motor section.

Abstract: A system for controlling activity in a combustion chamber. The system does not necessarily need to be mechanically adjusted and yet may provide precise control of a fuel air mixture ratio. A sensing module of the system may have a mass flow sensor that relates to air flow and another sensor that relates to fuel flow. Neither sensor may need contact with fuel. Fuel and air to the system may be controlled. Pressure of the fuel and/or air may be regulated. The sensors may provide signals to a processor to indicate a state of the fuel and air in the system. The processor, with reliance on a programmed curve, table or the like, often based on data, in a storage memory, may regulate the flow or pressure of the fuel and air in a parallel fashion to provide an appropriate fuel-air mixture to the combustion chamber.

Abstract: A camera captures an image of a structural bearing, such as a hanger bearing or a rocker bearing. Additionally, an instrument detects a temperature. A computing system determines, based on the temperature, an expected angle of the bearing relative to a base line. The computing system also determines an actual angle of the bearing relative to the base line. The computing system superimposes a first line on the image, the first line indicating the expected angle. Furthermore, the computing system superimposes a second line on the image, the second line indicating the actual angle.

Abstract: Devices, methods, systems, and computer-readable media for a dual wavelength source gas sensor are described herein. One or more embodiments include a gas sensor, comprising: a dual wavelength source to transmit a first wavelength and a second wavelength via an optical path, wherein a gas is present through the optical path, a detector to receive the first wavelength and the second wavelength via the optical path, and a computing device coupled to the detector to determine an determine a signal intensity for the first wavelength and the second wavelength.

Abstract: An ultra-high charge density electret is disclosed. The ultra-high charge density electret includes a three-dimensional structure having a plurality of sidewalls. A porous silicon dioxide film is formed on the plurality of sidewalls, and the porous silicon dioxide film is charged with a plurality of positive or negative ions.

Abstract: A communication system in an aircraft is described. The communication system includes a CMU that is coupled to at least one safety subnetwork and an AOIP computing device. The AOIP computing device is coupled to at least one non-safety subnetwork. The AOIP computing device determines whether ACARS messages received from the CMU are ACARS safety messages or ACARS non-safety messages. The AOIP computing device monitors CMU status messages from the CMU. In response to the AOIP computing device receiving an ACARS safety message, the AOIP computing device periodically transmits a second status message indicating that the AOIP computing device is unavailable. In response to determining that at least one safety subnetwork is available, the AOIP computing device stops periodically transmitting the second status message and transmits a first status message indicating that the AOIP computing device is available.

Abstract: Methods for radar altimeter integrity monitoring are provided.

Abstract: A heat exchanger includes a separator member that divides a first flow passage from a second flow passage. The heat exchanger also includes a plurality of first hollow members that extend across the first flow passage at respective non-orthogonal angles. The plurality of first hollow members are fluidly connected to the second flow passage. Moreover, the heat exchanger includes a plurality of second hollow members that extend across the second flow passage at respective non-orthogonal angles. The plurality of second hollow members are fluidly connected to the first flow passage.

Abstract: A system for controlling activity in a combustion chamber. The system does not necessarily need to be mechanically adjusted and yet may provide precise control of a fuel air mixture ratio. A sensing module of the system may have a mass flow sensor that relates to air flow and another sensor that relates to fuel flow. Neither sensor may need contact with fuel. Fuel and air to the system may be controlled. Pressure of the fuel and/or air may be regulated. The sensors may provide signals to a processor to indicate a state of the fuel and air in the system. The processor, with reliance on a programmed curve, table or the like, often based on data, in a storage memory, may regulate the flow or pressure of the fuel and air in a parallel fashion to provide an appropriate fuel-air mixture to the combustion chamber.

Abstract: In one embodiment, a method is provided. The method comprises: receiving a selection of at least one of: an initial air traffic control (ATC) message communications protocol and an initial controller-pilot data link communications (CPDLC) system; determining if a second communications protocol was selected; if the second communications protocol was selected, trapping at least one of a received ATC message in a first communications protocol, and a to be sent ATC message in the first communications protocol; and at least one of sending an ATC message in the selected communications protocol and receiving an ATC message in the selected communications protocol.

Abstract: Apparatus and associated methods relate to fitting a virtual mask to a virtual face by first fitting a chin region of the virtual mask to the virtual face, then determining an virtual mask angle that maintains the fitted chin region while simultaneously fitting a nose-bridge region of the virtual mask to the virtual face, and then calculating a fit-quality metric corresponding to the fitted position. In an illustrative embodiment, the fitted chin region may include the high curvature menton region of the chin. In some examples, a virtual mask may be virtually pressed toward the virtual face using a predetermined force corresponding to a force of a mask securing device of a real mask corresponding to the virtual mask In an exemplary embodiment, the fitting of a virtual mask to a virtual face may advantageously yield a mask's fit quality in a brief amount of time.

Abstract: Disclosed herein is a method of forming an alloy material for use in a wire. The method includes forming a master alloy containing lead and silver; and creating a molten wire alloy by combining the master alloy, additional lead, and a third material in a vessel. The method also includes flowing argon gas through and over the molten wire alloy. The method also includes drawing the molten alloy from the vessel through an actively cooled die, and solidifying the molten wire alloy to form a bar of wire alloy.

Abstract: This disclosure provides an apparatus and method for virtual wireless devices for industrial wireless sensor networks, including but not limited to, in industrial control systems and other systems. A method includes initializing, by a physical wireless device, a plurality of virtual wireless devices executing on the physical wireless device. The method includes registering with a control network by the physical wireless device. The method includes emulating a plurality of wireless sensors, by the physical wireless device and in the control network, by using the virtual wireless devices.

Abstract: A system of pressure control for an environment to be pressurized includes a controller configured to calculate an environment leakage effective area CdALEAK according to: CdALEAK=f(Pc, Tc, Pa, WLEAK) wherein Pc is an environment pressure; Tc is an environment temperature; Pa is an ambient pressure outside of the environment; WLEAK=WECS?WOFV?WAPU; wherein WECS=air pressure inflow into the environment; WOFV=air pressure outflow to ambient that is outside of the environment; WAPU=f(Tin, Pin, APURPM, Flowfuel); wherein Tin=inlet temperature to a power source; Pin=inlet pressure to the power source; APURPM=rotational speed of the power source; Flowfuel=power source fuel flow. A processor is in communication with the controller and configured to compare a current CdALEAK value with a control limit; wherein the control limit is based on historical CdALEAK values.

Abstract: An adaptive non-invasive alternating current brain stimulation system and method includes supplying transcranial alternating current stimulation (tACS) from a tACS source to a person, and receiving electroencephalogram (EEG) signals from EEG sensors disposed on the person, where the EEG signals including stimulation interference. The received EEG signals are processed using an adaptive model to estimate the stimulation interference in the EEG signals. The estimated stimulation interference is subtracted from the EEG signals to estimate neural oscillations of the person. The estimated neural oscillations are processed through an autoregressive model to generate predictions of future neural activity of the person and, based on the generated predictions, one or more electrical characteristics of the tACS being supplied to the person are varied to thereby modulate the neural oscillations of the person.

Abstract: Systems and methods are provided for providing control instructions to a pilot in the event of a loss of control of primary flight surfaces of an aircraft. The control instructions are determined using an emergency flight controller for receiving a pilot input, the emergency flight controller being in operable communication with at least one sensor for sensing aircraft parameters. The emergency flight controller is configured to determine target thrusts for the multiple engines and a target stabilizer position for the trimmable stabilizer on the basis of pilot input and sensed aircraft parameters. A guidance module is configured to provide instructions to a pilot as to how to control the engine thrusts toward the thrust targets and as how to control the trimmable stabilizer towards the target trimmable stabilizer position.

Abstract: A pressure control system includes an overboard valve in indirect communication with a first enclosed environment and in direct communication with a second enclosed environment. The first environment is suitable for human occupancy and configured to receive pressurized air from an environmental control system. The second environment is configured to receive the pressurized air from the first environment. An inboard valve is configured to supply a discharge of pressurized air from the second environment. An outflow valve is configured to regulate a discharge of air from the first environment to an area outside the first and second environments. A positive pressure relief valve configured to regulate a discharge of air from the first environment. A negative pressure relief valve configured to regulate an ingress of air into the first environment. A control valve is configured to regulator and supply pressurized air from the first environment to a compressor.

Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between open and closed positions for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor, at which the inlet-adjustment mechanism is switched from one of its positions to the other. A fixed switch band straddling the threshold line can be used for determining when to initiate the switch of positions so as to time the switch to coincide with the operating point reaching the threshold line. Alternatively, a time to reach the threshold line can be instantaneously computed and compared to the actuator/mechanism response time.