Abstract: The present invention provides a method of engineering a cell, comprising the steps of introducing into the cell: i) a site-directed nuclease which is capable of cleaving a target nucleotide sequence at the 3?-end of Intron 1 of a Cytotoxic T-Lymphocyte Associated Protein 4 gene (CTLA4); and ii) a nucleic acid construct which comprises a nucleic acid sequence comprising one or more of exon 2, exon 3 and exon 4 of CTLA4, or a sequence with at least 70% identity to exon 2, exon 3 and/or exon 4 of the CTLA4 gene, and 5?- and 3?-homology arms, wherein each of the 5? and '3 homology arms is essentially complementary to a sequence flanking the target nucleotide sequence at the 3?-end of Intron 1 of CTLA4.

Abstract: A breakable shooting target formed from a composition comprising: a binder component, a binder modifier, a viscosity modifier, and a filler. Carbon black or other pigments can be added for color. The binder can be selected from one or more natural fatty acids. The binder modifier can be selected from one or more metal oxides. The viscosity modifier can be selected from one or more plant based or other natural resins. The filler component can be selected from various powders, such as powdered limestone, other sources of calcium carbonate, talc and so forth.

Abstract: Control surface actuator assemblies, aircraft hydraulic systems including the same, and associated aircraft and methods. A control surface actuator assembly includes a flight control surface operatively coupled to a support structure, a torque-generating hydraulic actuator configured to apply a torque to pivot the flight control surface, and a variable horn radius (VHR) hydraulic actuator configured to vary an actuator moment arm length for pivoting the flight control surface. In some examples, an aircraft hydraulic system includes such control surface actuator assemblies, and an aircraft includes such aircraft hydraulic systems. In some examples, a method of operating one or more flight control surfaces of an aircraft includes controlling a selected flight control surface by adjusting, with a VHR hydraulic actuator, an actuator moment arm length corresponding to the selected flight control surface and pivoting, with a torque-generating hydraulic actuator, the selected flight control surface.

Abstract: Technologies for dynamic forecasting, aggregation, and validation may include circuitry configured to collect data indicative of power flows at multiple locations in an electrical grid, to receive one or more parameters for generation of a customized forecast indicative of predicted power flows associated with one or more of the multiple locations over a defined time period, to select a subset of the collected data that satisfies the one or more parameters, to produce a model to predict power flows in the electrical grid associated with the one or more locations, to determine whether the model is validated by determining whether a predicted production of power minus predicted losses is within a predefined range of a predicted consumption of power at the one or more locations, and to produce the customized forecast of predicted power flows associated with the one or more locations for the defined time period.

Abstract: A propulsion system for an aircraft is disclosed, and includes a first propeller, a second propeller, a first hybrid propulsion system, a second hybrid propulsion system, and a cross-connecting clutch. The first hybrid propulsion system includes a first motor coupled to a first engine by a first overrunning clutch, where the first hybrid propulsion system is operably coupled to drive the first propeller. The second hybrid propulsion system includes a second motor coupled to a second engine by a second overrunning clutch, where the second hybrid propulsion system is operably coupled to drive the second propeller. The cross-connecting clutch is operably coupled to both the first hybrid propulsion system and the second hybrid propulsion system and configured to actuate into an engaged position.

Abstract: The present application discloses various cementitious compositions that incorporate waste materials therein. In some embodiments, the waste materials incorporated in the compositions are mixed construction and demolition fines, including but not limited to small pieces of glass, wood, metal, drywall, cardboard, masonry, and other architectural material and waste materials. Various methods for using said compositions are also disclosed.

Abstract: Inerters with friction disk assemblies, and aircraft hydraulic systems and aircraft including the same. An inerter comprises an inerter housing containing an inerter fluid, a threaded shaft extending within the inerter housing and fixed relative to the first terminal, and an inerter rod extending at least partially within the inerter housing and fixed relative to the second terminal. The inerter further includes a friction disk assembly that, together with the inerter fluid, is configured to damp a motion of the second terminal relative to the first terminal. The friction disk assembly includes a fixed portion and a rotating portion, and is configured such that rotation of the rotating portion generates a frictional torque that opposes the rotation of the rotating portion. In some examples, the inerter is a component of a hydraulic actuator, an aircraft hydraulic system including the hydraulic actuator, and/or an aircraft including the aircraft hydraulic system.

Abstract: Inerters with friction disk assemblies, and aircraft hydraulic systems and aircraft including the same. An inerter comprises an inerter housing containing an inerter fluid, a threaded shaft extending within the inerter housing and fixed relative to the first terminal, and an inerter rod extending at least partially within the inerter housing and fixed relative to the second terminal. The inerter further includes a friction disk assembly that, together with the inerter fluid, is configured to damp a motion of the second terminal relative to the first terminal. The friction disk assembly includes a fixed portion and a rotating portion, and is configured such that rotation of the rotating portion generates a frictional torque that opposes the rotation of the rotating portion. In some examples, the inerter is a component of a hydraulic actuator, an aircraft hydraulic system including the hydraulic actuator, and/or an aircraft including the aircraft hydraulic system.

Abstract: Control surface actuator assemblies, aircraft hydraulic systems including the same, and associated aircraft and methods. A control surface actuator assembly includes a flight control surface operatively coupled to a support structure, a torque-generating hydraulic actuator configured to apply a torque to pivot the flight control surface, and a variable horn radius (VHR) hydraulic actuator configured to vary an actuator moment arm length for pivoting the flight control surface. In some examples, an aircraft hydraulic system includes such control surface actuator assemblies, and an aircraft includes such aircraft hydraulic systems. In some examples, a method of operating one or more flight control surfaces of an aircraft includes controlling a selected flight control surface by adjusting, with a VHR hydraulic actuator, an actuator moment arm length corresponding to the selected flight control surface and pivoting, with a torque-generating hydraulic actuator, the selected flight control surface.

Abstract: A wire strainer including a drive means having a mounting block with a drum mounted for rotation relative thereto, and an actuation means connected to the drum for selectively causing the drum to rotate relative to the mounting block. A line member is operatively connected to the drum in a manner such that rotation of the drum in one direction causes the drum to pull the line member relative to the mounting block. Locking means is operatively connected to the mounting block and adapted to selectively lock the drum against rotation in the opposite direction. Gripping means is operatively connected to the mounting block, wherein the gripping means is adapted to be releasably attached to a wire to be strained. The line member includes securing means for releasably securing the line member to a strainer post or similar anchor.

Abstract: A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.

Abstract: A propulsion system for an aircraft is disclosed, and includes a first propeller, a second propeller, a first hybrid propulsion system, a second hybrid propulsion system, and across-connecting clutch. The first hybrid propulsion system includes a first motor coupled to a first engine by a first overrunning clutch, where the first hybrid propulsion system is operably coupled to drive the first propeller. The second hybrid propulsion system includes a second motor coupled to a second engine by a second overrunning clutch, where the second hybrid propulsion system is operably coupled to drive the second propeller. The cross-connecting clutch is operably coupled to both the first hybrid propulsion system and the second hybrid propulsion system and configured to actuate into an engaged position.

Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include ports to receive and discharge hydraulic fluid. The dual spool valve may also include first and second valve sections that are selectively positionable to control the flow of hydraulic fluid into and out of the actuator. One position provides for hydraulic fluid to move through closure lines. Method of controlling the dual spool valve may provide for selectively positioning the valve sections to control the flow of hydraulic fluid, and to position the valve sections to move hydraulic fluid through a closure line during certain circumstances.

Abstract: A force balance sensor including a mechanical strain amplification system including a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member, at least one strain sensor coupled to the sensor torsion member between the first and second ends, a first torsional stiffening member coupled to the first end of the sensor torsion member, and a second torsional stiffening member coupled to the second end of the sensor torsion member, wherein the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member.

Abstract: Technologies for dynamic forecasting, aggregation, and validation may include circuitry configured to collect data indicative of power flows at multiple locations in an electrical grid, to receive one or more parameters for generation of a customized forecast indicative of predicted power flows associated with one or more of the multiple locations over a defined time period, to select a subset of the collected data that satisfies the one or more parameters, to produce a model to predict power flows in the electrical grid associated with the one or more locations, to determine whether the model is validated by determining whether a predicted production of power minus predicted losses is within a predefined range of a predicted consumption of power at the one or more locations, and to produce the customized forecast of predicted power flows associated with the one or more locations for the defined time period.

Abstract: The present application discloses various cementitious compositions that incorporate waste materials therein. In some embodiments, the waste materials incorporated in the compositions are mixed construction and demolition fines, including but not limited to small pieces of glass, wood, metal, drywall, cardboard, masonry, and other architectural material and waste materials. Various methods for using said compositions are also disclosed.

Abstract: An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.

Abstract: Methods and devices for adjusting a position of a flight control member relative to a base of an aircraft. The devices and methods include a joint that movably connects the flight control surface to the base. An extension member is connected to the flight control surface and extends through the joint. Adjustable linear members of the base are connected to the extension member and configured to adjust the position of the extension member. This adjustment results in re-orienting the flight control member relative to the base to adjust the flight of the aircraft.

Abstract: A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.

Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include first and second manifolds that each includes a movable spool. Multiple ports are positioned in each of the manifolds. The movable spools are positionable within their respective manifolds to control the movement of the hydraulic fluid that is supplied to and removed from the hydraulic actuator.