Abstract: In one embodiment, the disclosed technology involves a system having a generator set comprising a first engine and an output terminal coupled to a power distributor, a load comprising two or more sub-loads, wherein each of the sub-loads are coupled to the power distributor via one or more respective electrical contactors, and a controller communicably coupled to the electrical contactors and the generator set comprising a processor, and a memory, the memory having computer-readable instructions stored thereon that, when executed by the processor cause operations. The operations may include determining a number of sub-loads available, receiving data representing power generation of the generator set, determining which of the available sub-loads to connect in order to balance the generator set to the load, and controlling the respective electrical contactors of the determined sub-loads so as to provide electricity to the determined sub-loads.

Abstract: Instruments, methods, and kits are disclosed for performing fast thermocycling.

Abstract: A solidified melt extrudate comprising an active pharmaceutical ingredient in an amorphous form and a combination of at least two polymers.

Abstract: A drive train for a wind-up injection device is described. The drive train includes a torsional energy storage adapted to be loaded or unloaded by a rotatable element, a rotatable user handle, a rotationally driveable expelling mechanism adapted to expel the liquid drug, and a clutch element coupled with the torsional energy storage via the rotatable element and including a ratchet for maintaining the rotatable element at one of a number of discrete angular positions against the torque of the torsional energy storage. The clutch element is adapted to transmit the torque from the user handle to the torsional energy storage, or alternatively from the torsional energy storage to the expelling mechanism. The ratchet is switchable from one position to an adjacent position by a torque transmitted from the user handle to the torsional energy storage. The drive train is adapted to dampen torque peaks visco-elastically and/or visco-frictionally.

Abstract: A system and method for visually warning a person of a dangerous condition related to the proximity of the person to a machine is provided. The system includes a transmitter system located on the machine, a locator for being carried by the person, an algorithm performed at the transmitter for determining coordinates of the locator relative to the transmitter system, data input into the controller defining one or more safety zones around the machine, a warning indicator for generating a signal when the locator enters any of the one or more safety zones, and a lamp associated with the person. The lamp may be a spot lamp for illuminating the area around the person, and it may also include one or more warning lamps associated with the warning indicator such that the one or more warning lamps are illuminated when the locator enters either of the safety zones.

Abstract: The present invention relates to the development of and use of genetically modified human differentiated cells coupled with xenotransplantation into animal models to identify injury and disease-specific RNA and/or protein biomarkers. Specifically, the present invention encompasses two complementary methods for biomarker discovery that enable the direct and selective labelling, isolation, and analysis of human-specific RNA and/or proteins from xenotransplantation (or chimeric) animal models. Both methods involve the treatment of animal models with an RNA analog and/or amino acid analog that enables the specific isolation and quantification of human RNAs and/or proteins for the identification of novel human biomarkers for a large array of human injuries and diseases.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.

Abstract: In one embodiment, a method includes transmitting pulse power on two wire pairs, the pulse power comprising a plurality of high voltage pulses with the high voltage pulses on the wire pairs offset between the wire pairs to provide continuous power, performing low voltage fault detection on each of the wire pairs between the high voltage pulses, and transmitting data on at least one of the wire pairs during transmittal of the high voltage pulses. Data transmittal is suspended during the low voltage fault detection.

Abstract: Female fiber optic connectors having a weatherproofing collar disposed rearward of a connection port opening that receives a fiber optic plug along with cable assemblies comprising the female fiber optic connector and with methods of making the same. The female fiber optic connectors comprise an actuator such as a rocker latch arm or the like disposed under the weatherproofing collar used for releasing or securing an external fiber optic plug that may be received in the connection port. The weatherproofing collar protects the actuator such as the rocker arm latch and surrounding area from dirt, debris, moisture and the like from ingress into the connector. One or more end caps may be used with the weatherproofing collar. The weatherproofing collar allows for a ruggedized fiber optic connector having a quick connect and release mechanism for the external fiber optic plug connector mated to the female fiber optic connector.

Abstract: A channel graphical user interface (GUI) of a content sharing platform is provided for presentation to a channel owner. A request is received, via the channel GUI, to enable an online community option that (i) facilitates an online conversation between the channel owner and a subset of viewers of the channel of the channel owner on the content sharing platform, and (ii) allows the channel owner to control viewer responses that are permitted during the online conversation. In response to the request of the channel owner to enable the online community option, the online community option is associated with the channel in a data store, and the channel GUI is modified, the modified channel GUI presenting an online community GUI element representing the online community option.

Abstract: A system and method for monitoring a motor of a vehicle system monitor operating conditions of the vehicle system and determine whether the operating conditions of the vehicle system match designated operating conditions. Responsive to determining that the operating conditions of the vehicle system that are monitored match the designated operating conditions, an electrical signature representative of an electric current supplied to the motor of the vehicle system is examined and damage to one or more of the motor of the vehicle system or a mechanical coupling of the motor to one or more of a wheel or axle of the vehicle system is identified based on the electrical signature that is examined.

Abstract: A mapping system allows a user to interact with any location on a digital map and present the user with location related information associated with the selected location. The location related information may be in the form or a card, pop-up, image, or other graphic and may be displayed on the map at or near the selected location, around the map, etc. The displayed location related information may include predetermined or pre-stored data about the location or may include location related information collected and generated on the fly in response to the user interaction with the digital map. The displayed location related information may be displayed in the same graphical format on the digital map regardless of whether location related information is predetermined information about the location that already exists or information that is collected and generated on the fly in response to the user interaction.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, first thermal bus and heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, or each first electric machine, and the first heat exchanger. Waste heat energy transfers to the first heat transfer fluid. The first heat exchanger configures to transfer waste heat energy from the first heat transfer fluid to a dissipation medium. During steady-state operation of the first gas turbine engine, the first heat transfer fluid entering the first heat exchanger has a temperature of TFLUID(° C.), and a temperature of an inlet air flow entering the first gas turbine engine has a temperature TAIR(° C.) and a ratio B is in a range of between 5.0-18.0.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger. Waste heat energy generated by at least one first gas turbine engine, and first electric machine, transfers to the first heat transfer fluid. The first heat exchanger directs a first proportion of the first heat transfer fluid through a first heat dissipation portion wherein a first proportion of the waste heat energy transfers to a first dissipation medium dependent on the first dissipation medium temperature and mass flow rate. The first heat exchanger directs a second proportion of the first heat transfer fluid through a second heat dissipation portion wherein the second proportion of waste heat energy transfers to a second dissipation medium dependent on the second dissipation medium temperature and mass flow rate.

Abstract: A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that: 1.1*Q2<Q3<3.0*Q2.

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, a first heat exchanger, and one or more first ancillary systems. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the or each first electric machine, the first gas turbine engine, the first heat exchanger, and the or each first ancillary system. Waste heat energy generated by at least one of the first gas turbine engine, the or each first electric machine, and the or each first ancillary system, is transferred to the first heat transfer fluid. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.

Abstract: A flame simulating assembly is provided with a reflected flickering light that includes only one light source. Light from the light source passes through a rotating flicker element onto one or more reflectors, or mirrors, that reflect light up onto a simulated fuel bed and the some of the light is reflected off of the flicker elements towards a flame screen to create a simulated flame. The dipping flicker elements creates a fluttering light effect due to the flicker elements “intermittently dipping” into the light path. This fluctuating light is reflected onto the logs and ember bed in front and creates a dancing effect, which simulates glowing embers.