Abstract: A receptacle device which detects when mail has been delivered to the receptacle using a pressure sensor, IR beam, and/or a magnetic sensor. The receptacle device is connected to a wireless or wired network and is configured to communicate with a smart home system at the delivery point. The receptacle detects mail delivery and communicates this information via a network bridge to the smart home device of the recipient. The network bridge also gathers information from an informed delivery system which includes information regarding and images of mailpieces being delivered for a given day. The network bridge sends images of mailpieces which were delivered and additional mailpiece information to the recipient on the smart home system. For parcel, the network bridge can receive information regarding parcels to be delivered and can provide delivery estimates and visual tracking on a map.

Abstract: An automated cleaning system is disclosed having a track or rail, and a body having a cylindrical or capsule configuration. The cleaning system further includes a cleaning or disinfectant solution disposed within the body and one or more nozzles secured to one or more sides of the body for dispensing the cleaning solution. The cleaning system also includes one or more wheels or bearings secured to the body, wherein the wheels or bearings are at least partially received within the track. Further, the track can be suspended from overhead within a structure. Here, the cleaning system can be automated and programmed to operate during predefined schedules with little to no human intervention, thereby minimizing the risk associated with cleaning surfaces and open areas, among other advantages.

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: The elastomeric money or wallet band is a fastening structure. The elastomeric money or wallet band comprises an elastic band and one or more negotiable instruments. The elastomeric money or wallet band is configured for use with the one or more negotiable instruments. The elastomeric money or wallet band binds the one or more negotiable instruments together.

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: A receptacle device which detects when mail has been delivered to the receptacle using a pressure sensor, IR beam, and/or a magnetic sensor. The receptacle device is connected to a wireless or wired network and is configured to communicate with a smart home system at the delivery point. The receptacle detects mail delivery and communicates this information via a network bridge to the smart home device of the recipient. The network bridge also gathers information from an informed delivery system which includes information regarding and images of mailpieces being delivered for a given day. The network bridge sends images of mailpieces which were delivered and additional mailpiece information to the recipient on the smart home system. For parcel, the network bridge can receive information regarding parcels to be delivered and can provide delivery estimates and visual tracking on a map.

Abstract: An auxiliary power unit for an aircraft, having an engine core, a compressor having an outlet in fluid communication with the engine core inlet, a turbine section in fluid communication with the engine core outlet, and an excess air duct having a first end in fluid communication with the compressor outlet and a second end in fluid communication with a turbine inlet of the turbine section. The excess air duct defines a flow path between the compressor outlet and the turbine section separate from the engine core. The auxiliary power unit may include a generator in driving engagement with the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: A piston head for a syringe pump comprises a barrier portion (11) for driving fluid through a syringe pump barrel (30), wherein a peripheral section (13,14) of the barrier portion (11) is shaped to seal against the syringe pump barrel (30); and a re-silent member (15) arranged to resist deformation of the shaped peripheral section (13,14) of the barrier portion (11).

Abstract: A method includes, within a Graphical User Interface (GUI), displaying a contact list and a conversation container to a user, the contact list including a plurality of contact objects, the conversation container being an active object used to represent an ongoing conversation, receiving input from a user through the GUI, the input instructing the client computing system to move a first contact object from the plurality of contact objects over the conversation container and drop the first contact object into the conversation container, in response to dropping the first contact object into the conversation container, instructing a server to open a first communication session between the client system and a first device associated with the one of the contact objects, the first communication session being of a first media type, and engaging in communication through the first communication session with the first device.

Abstract: A pump for use in low-profile applications comprises a barrel for holding fluid; and a piston that converts a rotational driving force into a longitudinal driving motion within the barrel. The pump provides space saving advantages by reducing the need for external equipment and mechanisms around the pump for providing actuation or moving the actuating mechanism.

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

Abstract: A pump for use in low-profile applications comprises a barrel for holding fluid; and a piston that converts a rotational driving force into a longitudinal driving motion within the barrel. The pump provides space saving advantages by reducing the need for external equipment and mechanisms around the pump for providing actuation or moving the actuating mechanism.