Abstract: A device and method for analyte detection is provided. In an embodiment, the device includes a multi-layer filter configured to receive a fluid-borne sample including at least one analyte in combination with one or more non-analyte components. The multi-layer filter includes a sample preparation layer configured to dissolve upon receiving a portion of the fluid-borne sample to produce a solution including at least a portion of the fluid-borne sample. The device also includes an analysis cartridge for determining a presence and/or a concentration of the analyte in the solution. The device may be configured as a wearable mask or as a part of a ventilation system. In some embodiments, the analyte is detected using a polymerase chain reaction and a detectable marker. The device and method may be used to quickly detect the presence of an analyte in real-time and on-location.

Abstract: An augmented power converter may include a motor drive circuit. The motor drive circuit may include a motor drive transformer to convert a two-phase DC voltage to a three-phase output voltage for operating an electrical device. The motor drive circuit may also include a power control component for each phase of the two-phase voltage.

Abstract: A fastener comprises a head, and a shank having an outer surface and an axially-extending channel in the outer surface. Optically transmissive, strain-sensitive fills the channel.

Abstract: Provided are methods for decontamination of compartments, such as aircraft compartments and other types of compartments, and systems for implementing these methods. In some embodiments, a method involves detecting presence of one or more contaminants in a compartment. This information is used to select various decontamination conditions. In some embodiments, additional information, such as the type of the compartment (e.g., an aircraft compartment), temperature, and humidity, may be also considered while selecting the decontamination conditions. The decontamination conditions include identification of one or more decontaminating agents to be dispensed in the compartment, temperature profile of the air to be flown into the compartment, and timing of the decontaminant dispensing and air flowing operations. These conditions are selected to increase efficacy of the selected decontaminating agents with respect to the one or more detected contaminants and reduce impact on the aircraft compartment.

Abstract: A method and apparatus for managing a zone. Information is obtained about an environment in the zone with a sensor system. A determination is made by an analyzer system as to whether a contagious condition is present in the zone using the information from the sensor system. An action is performed by a management system in response to the contagious condition being present.

Abstract: Provided are methods for decontamination of compartments, such as aircraft compartments and other types of compartments, and systems for implementing these methods. In some embodiments, a method involves detecting presence of one or more contaminants in a compartment. This information is used to select various decontamination conditions. In some embodiments, additional information, such as the type of the compartment (e.g., an aircraft compartment), temperature, and humidity, may be also considered while selecting the decontamination conditions. The decontamination conditions include identification of one or more decontaminating agents to be dispensed in the compartment, temperature profile of the air to be flown into the compartment, and timing of the decontaminant dispensing and air flowing operations. These conditions are selected to increase efficacy of the selected decontaminating agents with respect to the one or more detected contaminants and reduce impact on the aircraft compartment.

Abstract: A method and apparatus for managing a zone. Information is obtained about an environment in the zone with a sensor system. A determination is made by an analyzer system as to whether a contagious condition is present in the zone using the information from the sensor system. An action is performed by a management system in response to the contagious condition being present.

Abstract: In representative embodiments, a system includes an acoustic emitter, a controller, an optical sensor, and an indicator for indicating a detection of a predetermined trace chemical vapor by the optical sensor. The acoustic emitter is positioned at a predetermined distance above the ground surface and configured to project a beam of acoustic energy toward the ground surface with a variable angle of incidence ?. The controller is configured to control the acoustic emitter to vary the angle of incidence of the acoustic beam within the variable angle of incidence ?, while the optical sensor is configured for standoff sensing of a trace chemical vapor proximate the ground surface. Excitation of the ground surface, particularly at a critical angle of incidence ?, causes the release of trace chemical vapors from a buried source and the soil into the air above the buried source.

Abstract: A method and apparatus for managing a zone. Information is obtained about an environment in the zone with a sensor system. A determination is made by an analyzer system as to whether a contagious condition is present in the zone using the information from the sensor system. An action is performed by a management system in response to the contagious condition being present.

Abstract: A method and system are provided for decontaminating at least a portion of an object. A misting device is configured to discharge a cloud formed from a plurality of cloud droplets. At least some of the cloud droplets include a decontaminating agent. A spraying device is configured to discharge a stream including a plurality of stream droplets into the cloud. At least some of the stream droplets have an electrostatic charge. At least some of the cloud droplets are deposited on the portion of the object to facilitate decontaminating the portion.

Abstract: In representative embodiments, a system includes an acoustic emitter, a controller, an optical sensor, and an indicator for indicating a detection of a predetermined trace chemical vapor by the optical sensor. The acoustic emitter is positioned at a predetermined distance above the ground surface and configured to project a beam of acoustic energy toward the ground surface with a variable angle of incidence ?. The controller is configured to control the acoustic emitter to vary the angle of incidence of the acoustic beam within the variable angle of incidence ?, while the optical sensor is configured for standoff sensing of a trace chemical vapor proximate the ground surface. Excitation of the ground surface, particularly at a critical angle of incidence ?, causes the release of trace chemical vapors from a buried source and the soil into the air above the buried source.

Abstract: A method and system are provided for decontaminating at least a portion of an object. A misting device is configured to discharge a cloud formed from a plurality of cloud droplets. At least some of the cloud droplets include a decontaminating agent. A spraying device is configured to discharge a stream including a plurality of stream droplets into the cloud. At least some of the stream droplets have an electrostatic charge. At least some of the cloud droplets are deposited on the portion of the object to facilitate decontaminating the portion.

Abstract: An integrated instrumentation system includes a body comprising a thermal protection system (TPS) material (e.g., an ablatable material), one or more sensors embedded within the body, and a processor (e.g., an FPGA or the like) communicatively coupled to the plurality of sensors. The processor is configured to acquire sensor signals from the plurality of sensors and produce digital sensor data associated therewith. The sensors may include, for example, recession sensors, pressure transducers, thermocouples, and accelerometers.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: A semiconductor die is attached to a packaging substrate by a patterned layer of conductive metal that includes voids. The voids provide a space into which the metal may expand when heated in order to avoid placing mechanical stress on the bonds caused by mismatches in the thermal coefficients of thermal expansion of the die, the conductive metal bond layer and the substrate. An additional coating of conductive metal may be flowed over the bond lines to reinforce the bonds.

Abstract: An integrated instrumentation system includes a body comprising a thermal protection system (TPS) material (e.g., an ablatable material), one or more sensors embedded within the body, and a processor (e.g., an FPGA or the like) communicatively coupled to the plurality of sensors. The processor is configured to acquire sensor signals from the plurality of sensors and produce digital sensor data associated therewith. The sensors may include, for example, recession sensors, pressure transducers, thermocouples, and accelerometers.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: A semiconductor die is attached to a packaging substrate by a patterned layer of conductive metal that includes voids. The voids provide a space into which the metal may expand when heated in order to avoid placing mechanical stress on the bonds caused by mismatches in the thermal coefficients of thermal expansion of the die, the conductive metal bond layer and the substrate. An additional coating of conductive metal may be flowed over the bond lines to reinforce the bonds.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.