Abstract: An analysis of the scans is performed to determine whether the selected item was moved from the back room to the shelf, then returned from the shelf to the back room. The analysis also determines a re-bin time when the selected product was returned to the back room. An adjustment to the PI is blocked when last PI adjustment time is later than the re-bin time. An adjustment to the PI is also blocked when an audit indicator is received at the interface indicating that the retail store is under an audit. An adjusted PI value is determined when the analysis indicates that the selected item was moved from the back room to the shelf, then returned from the shelf, the adjusted PI value being at least one more than the shelf capacity value.

Abstract: A vehicle includes a cabin interior, a dashboard located in the cabin interior, and a desk supported on the dashboard and movable between a stowed position on the dashboard and a deployed position extending outward from the dashboard, the desk comprising a plurality of interconnected panels having arms configured to engage a track to bend around at least a portion of the dashboard, and wherein the desk operably moves along the track when moved between the stowed position and the deployed position.

Abstract: A vehicle includes a body defining a cabin having an interior and a passenger door, an interior panel located in the interior, a track located in the passenger door within the interior, and a desk operably housed in a slot in the interior panel and slidably coupled to the slot in the interior panel and the track to move between a stowed position within the interior panel and a use position extending outward from the interior panel.

Abstract: A fuel management system includes: a fuel tank; a fuel supply line that supply fuel from the fuel tank to a combustor of the gas turbine engine; a reheat fuel supply line that supply fuel from fuel tank to a reheat of the gas turbine engine, the reheat fuel supply line extending from a reheat branching point on the fuel supply line to the reheat; a fuel supply pump disposed along fuel supply line upstream of the reheat branching point; a reheat pump disposed along reheat fuel supply line, the reheat pump that pressurise fuel to a reheat delivery pressure for delivery to the reheat; and a reheat recirculation line that recirculate fuel from the reheat fuel supply line to a location upstream of fuel supply pump, the reheat recirculation line extending from a reheat recirculation branching point on the reheat fuel supply line downstream of the reheat pump.

Abstract: The invention provides an ocular composition comprising: 99 to 60% (w/w) of a photopolymerizable composition selected from the group of fragments or monomers consisting of polyalkylene glycol diacrylate and polyalkylene glycol dimethacrylate, wherein the photopolymerizable composition has a molecular weight in the range of 100 to 20,000 Dalton; a biodegradable polymer selected from the group consisting of aliphatic polyester-based polyurethanes, polylactides, polycaprolactones, polyorthoesters and mixtures, copolymers, and block copolymers thereof; a photoinitiator; and a therapeutic agent. The composition can be used to form an ocular implant and an in situ ocular implant.

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 milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: Techniques for standardizing a catalog of data and for using the standardized data to implement various APIs are disclosed. Non-standardized data is received. This data includes information describing items, customer information, and unstructured review data. The non-standardized data is converted to a standardized format, resulting in the generation of standardized data. The standardized data includes a hierarchy of defined categories. Each category is associated with a set of attribute types. The standardized data also includes anonymized profiles. The unstructured review data is also provided structure. A data model is generated based on the standardized data. Various APIs can then use the data model to perform operations.

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 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 module. The first thermal bus includes 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 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 the first heat transfer fluid. The first heat exchanger module includes a first flow path and a second flow path. The first flow path is configured to direct a flow of the heat transfer fluid to a first heat dissipation portion.

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: The present invention relates to a part of a binding system for skiing, comprising a housing (3; 8) with, on the inside, a fully or partially through-going axial barrel (13) with an inner diameter (14), wherein two pins (1) moveable in each direction with at least one intermediate spring element (2) are arranged, and wherein the pins (1) are adapted to slide in the barrel (13) between a protruding and a retracted position. According to an aspect of the invention, the part of the pins (1) that is exposed when the pins (1) are in the protruding position, has a reduced outer diameter (15) compared with the inner diameter (14) of the barrel (13). The invention also relates to a method for lubricating the pins (1) with a lubricant.

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 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 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 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 comprises 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 module. 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 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 the first heat transfer fluid. The first heat exchanger module comprises a first flow path and a second flow path.

Abstract: A method for accessing customer data includes receiving an access request requesting access to customer data stored on a storage abstraction. The access request includes a justification that specifies a purpose/reason for requesting access to the customer data. The method also includes validating the justification, and after validating the justification, transmitting the justification to an external key management service associated with a customer of the customer data. The external key management service is configured to grant or deny access to the customer data based on the justification. The method also includes receiving an approved access token from the external key management service when the external key management service grants access to the customer data and accessing the customer data stored on the storage abstraction using the approved access token received from the external key management service.

Abstract: A button for a drug delivery device with a reduced operating loudness includes a plate-like button body forming a touch surface, wherein the plate-like button body is coupled by an axial supporting member to a noise-generating interface of the drug delivery device and movable into a longitudinal direction of the drug delivery device, wherein the plate-like button body includes a material composite with at least one first component consisting of a first material and at least one second component consisting of a second material different from the first material, wherein the at least one first component and the at least one second component are coupled via at least one coupling plane that is at least sectionwise slanted or perpendicular to the longitudinal direction. Further, the disclosure describes a button assembly for a drug delivery device which is shock resistant.