Abstract: A propulsion system for an aircraft includes a propeller assembly, a controller, and a pump system. The propeller assembly includes a propeller and a power system, the power system including an electric motor and a motor converter. The controller is connected to the power system and configured to switch the power system into a power-off arrangement in response to a temperature of the motor converter being greater than a threshold temperature. The pump system includes a pump and a coolant circuit that cools the motor converter. The pump is coupled to the propeller and to the motor such that rotation of either drives the pump.

Abstract: A propulsion system for an aircraft includes a propeller assembly, a controller, and a pump system. The propeller assembly includes a propeller and a power system, the power system including an electric motor and a motor converter. The controller is connected to the power system and configured to switch the power system into a power-off arrangement in response to a temperature of the motor converter being greater than a threshold temperature. The pump system includes a pump and a coolant circuit that cools the motor converter. The pump is coupled to the propeller and to the motor such that rotation of either drives the pump.

Abstract: Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.

Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

Abstract: An exemplary method of the present disclosure includes causing, by a processing system proximate to the wellbore, injection of the lift gas into the wellbore at a first gas injection rate; obtaining, by the processing system, a first indication of a parameter associated with the wellbore, an arrival of a first fluid at a wellhead associated with the wellbore, or a composition of the first fluid; determining, by the processing system and based on the first indication, at least one of: a second gas injection rate of the intermittent gas lift system, a first period to inject the lift gas with the intermittent gas lift system, or a second period, subsequent to the first period, with no injection of the lift gas by the intermittent gas lift system; and operating, by the processing system, the intermittent gas lift system according to the determination.

Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

Abstract: An exemplary method of the present disclosure includes causing, by a processing system proximate to the wellbore, injection of the lift gas into the wellbore at a first gas injection rate; obtaining, by the processing system, a first indication of a parameter associated with the wellbore, an arrival of a first fluid at a wellhead associated with the wellbore, or a composition of the first fluid; determining, by the processing system and based on the first indication, at least one of: a second gas injection rate of the intermittent gas lift system, a first period to inject the lift gas with the intermittent gas lift system, or a second period, subsequent to the first period, with no injection of the lift gas by the intermittent gas lift system; and operating, by the processing system, the intermittent gas lift system according to the determination.

Abstract: Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.

Abstract: An exemplary method of the present disclosure includes causing, by a processing system proximate to the wellbore, injection of the lift gas into the wellbore at a first gas injection rate; obtaining, by the processing system, a first indication of a parameter associated with the wellbore, an arrival of a first fluid at a wellhead associated with the wellbore, or a composition of the first fluid; determining, by the processing system and based on the first indication, at least one of: a second gas injection rate of the intermittent gas lift system, a first period to inject the lift gas with the intermittent gas lift system, or a second period, subsequent to the first period, with no injection of the lift gas by the intermittent gas lift system; and operating, by the processing system, the intermittent gas lift system according to the determination.

Abstract: An exemplary method of the present disclosure includes causing, by a processing system proximate to the wellbore, injection of the lift gas into the wellbore at a first gas injection rate; obtaining, by the processing system, a first indication of a parameter associated with the wellbore, an arrival of a first fluid at a wellhead associated with the wellbore, or a composition of the first fluid; determining, by the processing system and based on the first indication, at least one of: a second gas injection rate of the intermittent gas lift system, a first period to inject the lift gas with the intermittent gas lift system, or a second period, subsequent to the first period, with no injection of the lift gas by the intermittent gas lift system; and operating, by the processing system, the intermittent gas lift system according to the determination.

Abstract: An accessory for a device includes an actuator that is configured to be activated to operate a switch on the device when the accessory is physically engaged with the device. The switch is operable to cause the device to switch between on and off modes in which the device is configured to function. The off mode is a mode in which the device consumes less energy than when in the on mode. A controller is communicatively coupled with the actuator and is configured to activate the actuator to operate the switch when power is applied to the actuator.

Abstract: A method of determining common three-dimensional structural features of protein surfaces is provided, as is use of representations of these common structures in molecular database searching and in designing focused molecular libraries. The method is particularly concerned with the analysis and representation of protein surfaces such as b-turns, loops and contact surfaces. In one form, the method identifies common locations and orientations of amino acid side-chains, simplified as C?-C? vectors. In another form, the method identifies common regions of surface charge represented by grid points in three-dimensional space. Further provided are common three dimensional structural features of proteins that can be used to search molecular databases for the purposes of identifying molecules that match these common three dimensional structural features.

Abstract: A method of determining common three-dimensional structural features of protein surfaces is provided, as is use of representations of these common structures in molecular database searching and in designing focused molecular libraries. The method is particularly concerned with the analysis and representation of protein surfaces such as b-turns, loops and contact surfaces. In one form, the method identifies common locations and orientations of amino acid side-chains, simplified as C?-C? vectors. In another form, the method identifies common regions of surface charge represented by grid points in three-dimensional space. Further provided are common three dimensional structural features of proteins that can be used to search molecular databases for the purposes of identifying molecules that match these common three dimensional structural features.

Abstract: Silicon-based high pressure sensor modules are manufactured in an array arrangement, incorporating a low temperature cofired ceramic (LTCC) substrate. The LTCC substrate can withstand high pressures. Bossed containers filled with oil are mounted on the substrate in an array. These bossed containers house the sensor cells which are composed of a sensor handle wafer and a diaphragm. The top surface of these bossed containers are flexible and deflect under pressure. By controlling the surface area and the thickness of the top surface, the pressure sensors can be configured to measure a wide range of pressures. The oil transfers pressure from the bossed container to the diaphragm of the sensor cell while protecting the sensor cell from high pressures and harsh media.

Abstract: A sensor module is provided having a compact housing containing a sensor. A low temperature co-fired ceramic substrate is located on the housing. The sensor and signal processing circuitry are located on the low temperature co-fired ceramic substrate. The sensor module further includes a metal shield substantially encapsulating the sensor.

Abstract: A silicon-based high pressure sensor module incorporates a low temperature cofired ceramic (LTCC) substrate. The LTCC substrate can withstand high pressures. A bossed container filled with oil is mounted on the substrate and houses a sensor cell. The top surface of the bossed container is flexible and deflects under pressure. By controlling the surface area and the thickness of the top surface, the pressure sensor can be configured to measure a wide range of pressures. The oil transfers pressure from the bossed container to the diaphragm of the sensor cell while protecting the sensor cell from high pressures and harsh media.

Abstract: A technique for manufacturing an integrated pressure sensor includes a number of steps. Initially, a substrate with conductive electrical traces located on first and second sides of the substrate is provided. A plurality of compensation circuits are positioned in an array on the first side of the substrate in electrical contact with one or more of the conductive electrical traces on the first side of the substrate. A plurality of pressure sensors are positioned on the second side of the substrate in electrical contact with one or more of the conductive electrical traces on the second side of the substrate. Each one of the sensors is associated with one of the compensation circuits to form a plurality of pressure sensor-compensation circuit pairs. The substrate includes conductive vias to electrically connect each of the sensor-compensation circuit pairs. Each of the compensation circuits provides temperature compensation for an associated one of the sensors.

Abstract: The invention relates to a group of novel piperazine and piperidine derivatives of the formula wherein Y is hydrogen, halogen, alkyl (1-3C), or CN, CF3, OCF3, SCF3, alkoxy(1-3C), amino or mono- or dialkyl(1-3C) substituted amino or hydroxy, X is O, S, SO or SO2, ---Z represents -C, =C or -N, R1 and R2 independently represent hydrogen or alkyl (1-3C), Q is benzyl or 2-, 3- or 4-pyridylmethyl, wich groups may be substited with one or more more substituents from the group halogen, nitro, cyano, amino, mono- or di (1-3C)alkylamino, (1-3C) alkoxy, CF3, OCF3, SCF3, (1-4C)-alkyl, (1-3C)alkylsulfonyl or hydroxy, and salts and prodrugs thereof. It has been found that these compounds have interesting pharmacological properties due to a combination of (partial) agonism towards the members of the dopamine D2-receptor subfamily and affinity for relevant serotonin and/or noradrenergic receptors.

Abstract: A method of determining common three-dimensional structural features of protein surfaces is provided, as is use of representations of these common structures in molecular database searching and in designing focussed molecular libraries. The method is particularly concerned with the analysis and representation of protein surfaces such as b-turns, loops and contact surfaces. In one form, the method identifies common locations and orientations of amino acid side-chains, simplified as C?-C? vectors. In another form, the method identifies common regions of surface charge represented by grid points in three-dimensional space. Further provided are common three dimensional structural features of proteins that can be used to search molecular databases for the purposes of identifying molecules that match these common three dimensional structural features.