Abstract: Methods and systems for generating physiological metrics for display on a computing device are disclosed herein. In some implementations, an exemplary system comprises a torso wearable device including a wireless transmitter and a sensor, and non-transitory computer-readable media (CRM). The CRM, when executed by a computing device in communication with the wireless transmitter, can perform operations comprising: receiving the input signals representing respiration of the user; displaying a graphical user interface to the user; receiving one or more user inputs associated with a desired metric; displaying on the graphical user interface a first visualization corresponding to the desired metric; and displaying on the graphical user interface a second visualization corresponding to a physiological metric based on the input signals generated from the sensor. The second visualization can change in real time based on real time angular displacement of the sensor in response to the respiration of the user.

Abstract: A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

Abstract: A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.

Abstract: The fastener fitting (40) has a first fastener zone (42) for fastening to an element (24) of the deployment mechanism. This fastener fitting (40) has two longitudinal arms (46A, 46B) that extend substantially in parallel and in the same direction from the first fastener zone (42). The free ends of these arms that are remote from the first fastener zone are separate, with each arm being provided with a distinct fastener surface (48A, 48B), these respective fastener surfaces together forming the second fastener zone.

Abstract: A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

Abstract: A test bench for a reaction engine including a nozzle having a divergent. The bench includes a mechanism for holding the divergent in position, capable of holding the divergent so that its axis is vertical, and capable of interacting with a downstream portion of the divergent located in the downstream half thereof to limit distortion and/or displacement of this downstream portion. The test bench enables the divergent to remain undamaged even if lateral forces are applied to it during testing.

Abstract: A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.

Abstract: The fastener fitting (40) has a first fastener zone (42) for fastening to an element (24) of the deployment mechanism. This fastener fitting (40) has two longitudinal arms (46A, 46B) that extend substantially in parallel and in the same direction from the first fastener zone (42). The free ends of these arms that are remote from the first fastener zone are separate, with each arm being provided with a distinct fastener surface (48A, 48B), these respective fastener surfaces together forming the second fastener zone.

Abstract: A degradable compound, which may be used as a ball sealer and as an fluid loss additive for use in the oil and gas industry is disclosed. The compound comprises a particular composition of matter and injection molding technique that provides a ball sealer which will dissolve in stimulation or wellbore fluids after stimulation operations are complete. In a similar manner the compound may be used as a fluid loss additive which enhances the fracture filter cake and will dissolve completely after use in fracturing operations. Used as a ball sealer, the surface of the ball sealer softens slightly assuring a solid seal between the ball and the casing perforation. The pure composition when dissolved into wellbore fluids does not pose a hazard and has excellent dispersion in aqueous based wellbore fluids. The same composition, may be combined with fiber-glass to manufacture a high temperature ball sealer.

Abstract: Inducer equipment adapted to a pump having large induction capacity which cludes a case surrounding an inducer rotor having a plurality of blades leaving clearance relative to the case. The clearance between the peripheral portions of the blades and the case is of an increased value greater than the value of the normal clearance over a zone which extends both into a cylindrical first portion of the inside wall of the case upstream from the inducer rotor and into a portion of the inside wall of the case adjacent to the cylindrical first portion and overlapping an upstream portion of the inducer rotor over a distance from the leading edges of the blades of the inducer rotor. The ratio between the clearance of increased value and the clearance of normal value is advantageously greater than 10.

Abstract: A degradable ball sealer for use in the oil and gas industry is disclosed. The ball seat comprises a particular composition of matter and injection molding technique that provides a ball seal which will dissolve in stimulation or wellbore fluids after stimulation operations are complete. In use, the surface of the ball sealer softens slightly assuring a solid seal between the ball the and the casing perforation. The composition when dissolved into wellbore fluids does not pose a hazard and disperses well in aqueous based wellbore fluids. The same composition, made into a larger ball, may be used as a tubing sealer for pressure testing.