Abstract: An integral fluid measurement system includes a first sensor configured to communicate using a first communication technology, a second sensor configured to communicate using a second communication technology, and a hybrid interface unit including a first interface configured to communicate with a first sensor using a first communication technology and a second interface configured to communicate with a second sensor using a second communication technology, where the first and second communication technologies are different from each other and may include electrical, fiber optic, radio frequency, optical pulse, and sonic pulse. The hybrid interface unit may also include a digital signal processor, data bus, and power supply, and may be capable of being disposed on a fluid tank wall.

Abstract: An integral fluid measurement system includes a first sensor configured to communicate using a first communication technology, a second sensor configured to communicate using a second communication technology, and a hybrid interface unit including a first interface configured to communicate with a first sensor using a first communication technology and a second interface configured to communicate with a second sensor using a second communication technology, where the first and second communication technologies are different from each other and may include electrical, fiber optic, radio frequency, optical pulse, and sonic pulse. The hybrid interface unit may also include a digital signal processor, data bus, and power supply, and may be capable of being disposed on a fluid tank wall.

Abstract: A sensor assembly includes a capacitive probe, a resistive element, an electronic circuit and an optical interface. A capacitance of the capacitive probe and a resistance of the resistive element are indicative of characteristics of an environment. The electronic circuit is configured to convert the capacitance and the resistance into optical data. The optical interface is configured to provide the optical data to an optical link.

Abstract: Apparatus and associated methods relate to suppressing electrical arcing within a fuel tank in which a fuel density sensor is located by isolating electronic components of the fuel density sensor within a cavity surrounded by a dielectric housing. The dielectric housing physically isolates the sensor electronics from fuel in the fuel tank via a fuel barrier. The dielectric housing electrically isolating the sensor electronics within the cavity from potential high voltage hazards outside the cavity. Light energy optically from a first environment outside the cavity is transmitted through the dielectric housing to a second environment within the cavity to provide operating power for the sensor electronics. The light energy is converted into DC electrical energy within the cavity. A light signal indicative of fuel density is optically transmitted from the second environment within the cavity through the dielectric housing to the first environment outside the cavity.

Abstract: An aircraft fuel system comprises an integrated sensor assembly incorporating a housing. The housing receives a circuit board, a temperature sensor, a point level sensor and a fuel density sensor. A first fuel height sensor is positioned outwardly of the housing.

Abstract: Apparatus and associated methods relate to suppressing electrical arcing within a fuel tank in which a fuel density sensor is located by isolating electronic components of the fuel density sensor within a cavity surrounded by a dielectric housing. The dielectric housing physically isolates the sensor electronics from fuel in the fuel tank via a fuel barrier. The dielectric housing electrically isolating the sensor electronics within the cavity from potential high voltage hazards outside the cavity. Light energy optically from a first environment outside the cavity is transmitted through the dielectric housing to a second environment within the cavity to provide operating power for the sensor electronics. The light energy is converted into DC electrical energy within the cavity. A light signal indicative of fuel density is optically transmitted from the second environment within the cavity through the dielectric housing to the first environment outside the cavity.

Abstract: A sensor assembly includes a capacitive probe, a resistive element, an electronic circuit and an optical interface. A capacitance of the capacitive probe and a resistance of the resistive element are indicative of characteristics of an environment. The electronic circuit is configured to convert the capacitance and the resistance into optical data. The optical interface is configured to provide the optical data to an optical link.

Abstract: A sensor system includes a sensor operatively connected to a liquid storage vessel. An electronics unit is operatively connected to the sensor. The electronics unit includes a power source for providing electrical excitation to the sensor. An antenna is operatively connected to the electronics unit to receive data there from and to provide power to the power source. The antenna is wirelessly connected to a remote processing unit to transmit data thereto and to receive power there from.

Abstract: An aircraft fuel system comprises an integrated sensor assembly incorporating a housing. The housing receives a circuit board, a temperature sensor, a point level sensor and a fuel density sensor. A first fuel height sensor is positioned outwardly of the housing.

Abstract: An electromechanical braking system utilizes redundancy features to provide safe and reliable braking. The braking system is configured to operate on power provided by multiple power sources. Different modes of braking are available based on whether a failure has occurred in one or more power sources. Additionally, system redundancy allows for failure in one or more primary components without total loss of braking capacity. Proportional braking is provided even in an emergency braking mode.

Abstract: An electromechanical braking system utilizes redundancy features to provide safe and reliable braking. The braking system is configured to operate on power provided by multiple power sources. Different modes of braking are available based on whether a failure has occurred in one or more power sources. Additionally, system redundancy allows for failure in one or more primary components without total loss of braking capacity. Proportional braking is provided even in an emergency braking mode.

Abstract: A method is provided for arranging the components and power connection points within an electromechanical braking system architecture in order to better maintain isolation of the power busses, and thereby improve overall integrity of the system, while still meeting system redundancy, performance and safety requirements as in the past. In addition, a method is provided for connecting and efficiently using available power in emergency braking and parking modes.