Abstract: The invention provides a membrane structure suitable for a sand production test of a rock sample provided with a hollow cylinder shape, the membrane structure comprising a main body with a housing configured to confine the rock sample within; a watertight outer wall adapted to withstand external hydrostatic pressure exerted by a first fluid; a permeable inner wall limiting the housing and configured to exert pressure on the rock sample and, to inject a second fluid into the outer surface of said rock sample; a plurality of internal hollow chambers located between the watertight outer wall and the permeable inner wall, wherein each one of the plurality of internal hollow chambers includes a plurality of rigid particles filling the inner space of each hollow chamber for transmitting the external pressure exerted from the outer wall to the inner wall.

Abstract: In a method for enhancing accuracy and efficiency in automated visual inspection of vessels, a vessel containing a sample is oriented such that a line scan camera has a profile view of an edge of a stopper of the vessel. A plurality of images of the edge of the stopper is captured by the first line scan camera while spinning the vessel, where each image of the plurality of images corresponds to a different rotational position of the vessel. A two-dimensional image of the edge of the stopper is generated based on at least the plurality of images, and pixels of the two-dimensional image are processed, by one or more processors executing an inference model that includes a trained neural network, to generate output data indicative of a likelihood that the sample is defective.

Abstract: The invention provides a membrane structure suitable for a sand production test of a rock sample provided with a hollow cylinder shape, the membrane structure comprising a main body with a housing configured to confine the rock sample within; a watertight outer wall adapted to withstand external hydrostatic pressure exerted by a first fluid; a permeable inner wall limiting the housing and configured to exert pressure on the rock sample and, to inject a second fluid into the outer surface of said rock sample; a plurality of internal hollow chambers located between the watertight outer wall and the permeable inner wall, wherein each one of the plurality of internal hollow chambers includes a plurality of rigid particles filling the inner space of each hollow chamber for transmitting the external pressure exerted from the outer wall to the inner wall.

Abstract: A spacecraft includes a propulsion subsystem including at least two electric thrusters, an electrical interface assembly that couples electrical conductors from the thrusters to a spacecraft harness, a pneumatic interface assembly that controls flow rate of propellant to the thrusters and a thruster support module (TSM) including a pointing arrangement and a mounting arrangement. A proximal portion of the mounting arrangement is coupled with a distal portion of the pointing arrangement; the at least two electric thrusters are disposed on a distal portion of the mounting arrangement; the electrical interface assembly and the pneumatic interface assembly are disposed on the proximal portion of the mounting arrangement. The mounting arrangement is configured to limit heat transfer between the thrusters and (b) one or more of the proximal portion of the mounting arrangement, the electrical interface assembly and the pneumatic interface assembly.

Abstract: A spacecraft includes a power train that includes a solar array, an electric propulsion subsystem, and a power conversion module. The power conversion module receives power from the solar array at a voltage, Vi; and delivers power to the electric propulsion subsystem at a voltage, Vo. The spacecraft is configured to operate at a varying distance, D, from the sun within the range of Dmin to Dmax, Dmax being at least 1.3×Dmin. The solar array is configured to deliver power to the power conversion module at a voltage approximately equal to Vo when the spacecraft is proximate to Dmax.

Abstract: A spacecraft propulsion system includes at least one chemical thruster operable with a liquid propellant, at least one electric thruster operable with an inert gas, and a first quantity ‘n’ of pressurant tanks, each of the ‘n’ pressurant tanks having a substantially identical volume. The propulsion system results from assembling a plurality of subassemblies, such that a first selectable number ‘e’ of the first quantity of pressurant tanks are manifolded together with the at least one electric thruster, and a second selectable number ‘c’ of the first quantity of pressurant tanks are manifolded together with the at least one chemical thruster. The first selectable number ‘e’ is an integer in the inclusive range of 1 to ‘n’, and c=n?e.

Abstract: The present disclosure discloses a liquid cooler having separable and portable components. The liquid cooler has a liquid cooling section and a refrigerating system section. In an operative liquid cooling configuration, the components present in the liquid cooling section and the refrigerating system section are connected with each other with a first and second releasing coupler. In an operative defrosting configuration, the components of present in the liquid cooling section and the refrigerating system section are separated with each other by releasing the first and second releasing coupler and hence are easily portable. The separated liquid cooling section and the refrigerating system section enables easy periodic maintenance or replacement of faulty components in less time, labor and cost. Further, the liquid cooler is powered by power received from power mains or by power storage device such as battery.

Abstract: A heating and cooling system that can efficiently and effectively heat a pool and cool a home simultaneously or independently with one compressor and one condenser. The present invention uses a combination of four-way valves to selectively activate the system's components depending on instructions sent by the home or pool thermostats.

Abstract: A system for practicing an intussusception reduction procedure includes a flexible tube. The flexible tube can include an open end and a closed end A source of fluid pressure can be configured to be fluidly connected with the open end. The system can also include an imaging machine for obtaining real-time images of the flexible tube. Moreover, the system can include a visual barrier surrounding at least one portion of the flexible tube. A method for practicing an intussusception reduction procedure can include connecting a flexible tube to a source of fluid pressure, and insufflating the flexible tube with a fluid from the source of fluid pressure until the tube expands.

Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile.

Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile.