Abstract: A system and method for oblivious information retrieval are disclosed. A particular embodiment includes: a plurality of network nodes in data communication with each other via a network, each network node having a secure processing enclave, the enclave configured to include: at least one isolated memory device, processing logic isolated from operating system (OS) calls, and a remote attestation capability; and a view node in data communication with the plurality of network nodes and a transaction ledger, the view node including an account index horizontally scaled across a plurality of computing devices, the view node further configured to receive a transaction and a corresponding account hint, to decrypt the account hint, and to add a row corresponding to the transaction and the account hint to the account index.

Abstract: A cover plate according to certain embodiments is configured for use with a mounting plate and a control system, and has a front side and a rear side opposite the front side. The cover plate includes a support substrate, a cover plate coupler, and an electronic device. The support substrate includes an opening sized and shaped to receive a spindle of a door hardware apparatus associated with the rose assembly. The cover plate coupler is configured to releasably couple with a mounting plate coupler of the mounting plate. The electronic device is mounted to the support substrate, and includes a first electrical connector accessible from the rear side of the cover plate and configured for electrical connection with a second electrical connector of the control system, and an electronic component electrically connected with the first electrical connector.

Abstract: The disclosure is directed to improved methods for preparing substituted quinolinylcyclohexylpropanamide compounds.

Abstract: Gate-all-around integrated circuit structures having pre-spacer-deposition cut gates are described. For example, an integrated circuit structure includes a first vertical arrangement of horizontal nanowires and a second vertical arrangement of horizontal nanowires. A first gate stack is over the first vertical arrangement of horizontal nanowires, and a second gate stack is over the second vertical arrangement of horizontal nanowires. An end of the second gate stack is spaced apart from an end of the first gate stack by a gap. The integrated circuit structure also includes a dielectric structure having a first portion providing a gate spacer along sidewalls of the first gate stack, a second portion providing a gate spacer along sidewalls of the second gate stack, and a third portion filling the gap, the third portion contiguous with the first and second portions.

Abstract: Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The thrust chamber may be coupled with an injector having a circular array of support columns supporting a distribution system. Liquid may be flowed from the distribution system, through the support columns, and into a combustion chamber of the thrust chamber.

Abstract: Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The electrical turbopump impeller includes a coolant bypass port fluidically connected with a coolant passage that passes through the impeller central hub and allows some of the propellant that is acted on by the impeller to bypass the impeller outlet and instead be flowed into the electrical turbopump housing so that the diverted propellant may be used to cool the various components housed within the housing such as the electric motor bearings, stator, rotor, and electronics.

Abstract: Disclosed herein are various technologies pertinent to jettisonable battery systems for use in rocket engine-based launch vehicles. Such systems may feature battery units that are configured to be used to power one or more electric turbopumps that may be used to supply fuel to a rocket engine or engines. One or more of the battery units may be jettisoned during flight in order to reduce weight and as they are depleted. In some implementations, the battery units may be connected in parallel with the turbopump(s), with a depleted battery unit being electrically disconnected from the parallel circuit and jettisoned.

Abstract: Disclosed herein are various technologies pertinent to jettisonable battery systems for use in rocket engine-based launch vehicles. Such systems may feature batteries that are configured to be used to power one or more electric turbopumps that may be used to supply fuel to a rocket engine or engines. One or more of the batteries may be jettisoned during flight in order to reduce weight and as they are depleted. In some implementations, a depleted battery may remain electrically connected with the turbopump(s) while a new battery is electrically connected with the turbopump(s). The depleted battery may then be electrically disconnected from the turbopump and jettisoned.

Abstract: Identifying effects of geometric variations of physical parts may include measuring one or more surfaces of a physical part in three-dimensions, analyzing measurements of the physical part to determine a geometric variation from a baseline model, modifying an existing computational fluid dynamics (CFD) mesh for the baseline model based on the geometric variation using a mesh metamorphosis algorithm to create a target mesh for the physical part, and analyzing the target mesh using a CFD analysis to determine an effect (e.g., an effect on unsteadiness) in a system caused by the geometric variation.

Abstract: Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The electrical turbopump impeller includes a coolant bypass port fluidically connected with a coolant passage that passes through the impeller central hub and allows some of the propellant that is acted on by the impeller to bypass the impeller outlet and instead be flowed into the electrical turbopump housing so that the diverted propellant may be used to cool the various components housed within the housing such as the electric motor bearings, stator, rotor, and electronics.

Abstract: Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a highly efficient rocket engine and methods of manufacturing such devices, such as additive manufacturing. The use of additive manufacturing techniques allows for injectors and thrust chambers with complex geometries that provide for more efficient engine operation, including, for example, thrust chambers with varying surface roughness within cooling passages thereof and injectors with multiple annular plenums.

Abstract: This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomized and then ignited. The atomization step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidizers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion while doing so.

Abstract: A method is provided for mapping a pin location related to a choice factor weighed by a plurality of customers when deciding what brands, products or services to purchase. The pin is mapped on a three circle Venn diagram including a plurality overlapping and non-overlapping zones. The illustrated method includes analyzing survey data obtained from the plurality of customers related the choice factor; determining in which zone of the three circle Venn diagram to place the pin associated with the choice factor; and positioning each pin in the determined zone to provide a visual indication of a level of importance of the choice factor associated with the pin.

Abstract: A method is provided for mapping a pin location related to a choice factor weighed by a plurality of customers when deciding what brands, products or services to purchase. The pin is mapped on a three circle Venn diagram including a plurality overlapping and non-overlapping zones. The illustrated method includes analyzing survey data obtained from the plurality of customers related the choice factor; determining in which zone of the three circle Venn diagram to place the pin associated with the choice factor; and positioning each pin in the determined zone to provide a visual indication of a level of importance of the choice factor associated with the pin.

Abstract: A speculum having first and second arms beginning at a proximal point and ending at a distal end and having a cup positioned at the distal end, an attachment portion positioned on the first arm and proximal to the cup, and a user manipulation element positioned within the attachment portion. In another embodiment the speculum has a generally U-shaped frame having a proximal point and pair of distal ends, a pair of cups attached to the distal ends, a pair of user manipulation elements attached to the frame and positioned between the cups and the proximal point so that the user manipulation elements can rotate relative to the frame.

Abstract: This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so.

Abstract: Apparatus for forming high temperature superconductor (HTS) continuous conductor elements from a substrate, comprises a punch cutting tool for punching from a continuous strip material at successive operations of the punch cutting tool successive parts of the length of each of a plurality of continuous serpentine conductor elements; a feed system for feeding in steps the continuous strip material through the punch cutting tool between operations of the punch cutting tool; and a plurality of synchronized take-up spools for taking up each of the conductor elements from the punch cutting tool.

Abstract: A speculum having first and second arms beginning at a proximal point and ending at a distal end and having a cup positioned at the distal end, an attachment portion positioned on the first arm and proximal to the cup, and a user manipulation element positioned within the attachment portion. In another embodiment the speculum has a generally U-shaped frame having a proximal point and pair of distal ends, a pair of cups attached to the distal ends, a pair of user manipulation elements attached to the frame and positioned between the cups and the proximal point so that the user manipulation elements can rotate relative to the frame.

Abstract: A UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.

Abstract: A speculum having a generally U-shaped frame with a pair of arms, each arm having a free end, a pair of cups, each cup coupled with the free end of one of the arms, and a pair of surfaces, each surface coupled with one of the cups and having a portion extending upward at an angle from the frame.