Abstract: A computer system displays a first object that includes at least a first portion of the first object and a second portion of the first object and detects a first gaze input that meets first criteria, wherein the first criteria require that the first gaze input is directed to the first portion of the first object in order for the first criteria to be met. In response, the computer system displays a first control element that corresponds to a first operation associated with the first object, wherein the first control element was not displayed prior to detecting that the first gaze input met the first criteria, and detects a first user input directed to the first control element. In response to detecting the first user input directed to the first control element, the computer system performs the first operation with respect to the first object.

Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.

Abstract: An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.

Abstract: A computer-implemented method for automatically uploading media content from a mobile device to an online service provider can include receiving, in the mobile device, identifying information corresponding to a user account associated with at least one of a plurality of online service providers; capturing media content with a media input component included in the mobile device; and after the media content is captured, automatically uploading to the at least one online service provider the captured media content and the identifying information, without receiving user input contemporaneous with the automatic uploading that specifies that the captured media content is to be uploaded. The mobile device can further include a wireless communication component configured to wirelessly send data to and wirelessly receive data from the plurality of online service providers, which can be external to the mobile device.

Abstract: A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

Abstract: A computer system can include an input device having a housing defining an internal volume. The housing can include a grip portion and a base portion defining an aperture. The computer system can also include a tilt sensor disposed in the internal volume, a position sensor disposed at the aperture, and a processor. The processor can be electrically coupled to the position sensor, the tilt sensor, and a memory component storing electronic instructions that, when executed by the processor, cause the processor to receive a first input from the tilt sensor, receive a second input from the position sensor, determine, based on the first and second inputs, if the base is in contact with a support surface and an angle of the base relative to the support surface. The processor can also output a signal based on the angle if the base is in contact with the support surface.

Abstract: A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.

Abstract: A computer input system includes a mouse including a housing having an interior surface defining an internal volume and a sensor assembly disposed in the internal volume. A processor is electrically coupled to the sensor assembly and a memory component having electronic instructions stored thereon that, when executed by the processor, causes the processor to determine an orientation of the mouse relative to a hand based on a touch input from the hand detected by the sensor assembly. The mouse can also have a circular array of touch sensors or lights that detect hand position and provide orientation information to the user.

Abstract: In some embodiments, a computer system displays a virtual surface for containing one or more virtual objects in a three-dimensional environment. In some embodiments, a computer system automatically resizes virtual surfaces that contain objects. In some embodiments, a computer system displays feedback related to removal and/or addition of objects to virtual surfaces.

Abstract: An input device, such as a mouse, can include a housing defining an exterior grip portion and an internal volume, a sensor assembly disposed in the internal volume, and an emitter electrically coupled to the sensor assembly. In response to the sensor assembly detecting a first touch input on the housing, the emitter sends a first signal including information regarding an angular position of the grip portion. In response to the sensor assembly detecting a second touch input on the housing, the emitter sends a second signal including information regarding a direction of a force exerted on the housing from the second touch input.

Abstract: A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section through an engine drive shaft. A tap is at a location up stream of the combustor section for drawing a bleed airflow. A bleed air heat exchanger places the bleed airflow in thermal communication with an auxiliary flow for heating the bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow.

Abstract: A wearable cardioverter defibrillator monitor case includes a housing configured to surround a defibrillator electronics assembly, a front cover removably attachable to the housing, and a rear cover removably attachable to the housing. The wearable cardioverter defibrillator case has a shock indicator positioned on the housing at an interface between the housing and the front cover.

Abstract: Disclosed herein is a propellent-driven golf club to launch a ball without requiring a swinging action on the propellent-driven golf club. Accordingly, the propellent-driven golf club may include a hollow shaft and a handle attached to the hollow shaft. Further, the propellent-driven golf club may include a golf club head assembly attached to the hollow shaft. Further, the golf club head assembly may include a rotary magazine configured to receive a reloadable wafer, the firing mechanism operationally coupled to the triggering device, a firing cylinder port configured to mate with at least a portion of the cartridge, a vortex generator, a range control mechanism comprising a range control valve fluidly coupled to an egress port of the chamber, a firing cylinder bore fluidly coupled to an outlet of the range control valve, and a piston movably disposed in the firing cylinder bore.

Abstract: A downhole assembly includes a tubular body having a bore and a downhole tool connected to the tubular body. The downhole assembly also includes a sensor assembly having a carrier and a sensor. A sensor adapter is used to couple the sensor assembly to the tubular body. The sensor adapter includes an adapter body disposed in the bore of the tubular body; an adapter shaft for connection with the carrier; and a plurality of channels formed between the adapter shaft and the adapter body.

Abstract: Disclosed herein is a propellent-driven golf club to propel a ball without requiring a swinging action. Accordingly, the propellent-driven golf club may include a hollow shaft, a handle attached to a top portion of the hollow shaft, and a golf club head assembly attached to a bottom portion of the hollow shaft. Further, the golf club head assembly may include a bar receptacle comprising receptacles configured to receive cartridges, the firing mechanism operationally coupled to the triggering device, a firing cylinder port configured to receive at least a portion of a cartridge, a vortex generator comprising a chamber that may include an ingress port and an egress port, a range control mechanism comprising a range control valve fluidly coupled to the egress port of the chamber, a firing cylinder bore fluidly coupled to an outlet of the range control valve, and a piston movably disposed in the firing cylinder bore.

Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path that is in communication with a compressor section, combustor section and a turbine section, the core engine is configured to generate a high energy gas flow, a first cycle turbine that is configured to drive a first cycle compressor at a cycle speed in response to expansion of a heated working fluid flow between a first inlet and a first outlet of the first cycle turbine, and a first power turbine that is configured to drive a first output shaft at a power speed that is different than the cycle speed in response to expansion of a working fluid flow received from the first outlet of the first cycle turbine.

Abstract: A LUS robotic surgical system is trainable by a surgeon to automatically move a LUS probe in a desired fashion upon command so that the surgeon does not have to do so manually during a minimally invasive surgical procedure. A sequence of 2D ultrasound image slices captured by the LUS probe according to stored instructions are processable into a 3D ultrasound computer model of an anatomic structure, which may be displayed as a 3D or 2D overlay to a camera view or in a PIP as selected by the surgeon or programmed to assist the surgeon in inspecting an anatomic structure for abnormalities. Virtual fixtures are definable so as to assist the surgeon in accurately guiding a tool to a target on the displayed ultrasound image.

Abstract: A transformer bobbin includes a first bobbin member including a first end defining a first opening, a second end defining a second opening, an inner surface defining the first opening and an outer surface. The inner surface includes a first plurality of fins that extend between the first end and the second end. A second bobbin member is disposed about and spaced from the first bobbin member. The second bobbin member includes a first end portion defining a first opening portion, a second end portion, an inner surface portion and an outer surface portion. One of the outer surface of the first bobbin member and the outer surface portion of the second bobbin member includes a second plurality of fins that extend between the first end portion and the second end portion.

Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.

Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.