Abstract: A system to calcine crushed carbonate, discharge alkaline oxide, and deliver an enhancing fluid having CO2, comprising: a pressurized insulated calciner having descendingly, a crushed alkaline carbonate feeder, a calciner fluid outlet manifold, a heated sideflow calciner fluid intake manifold, a preheated sideflow calciner fluid outtake manifold, a fluid inlet manifold to recirculate calciner fluid from the outlet manifold, and an alkaline oxide discharger; a pressurizer to repressurize sideflow calciner fluid, connected to intake and outtake manifolds; pressurizers to recirculate calciner outlet fluid to the inlet manifold, pressurize the calciner and deliver enhancing fluid comprising CO2; delivery and combustion systems to form a combustion fluid; a recuperating or regenerating refractory heat exchanger to heat sideflow calciner fluid with combustion fluid connected to the sideflow pressurizer, and fluid outtake and intake manifolds; and a controller operable to control combustion, heat exchange, calciner

Abstract: A method of supplying crushed alkaline carbonate from a carbonate resource to a first calcining site having a design calcining capacity; solar calcining crushed carbonate within a prescribed carbon dioxide (CO2) delivery distance from a first enhancement location within a first hydrocarbon resource, whereby generating CO2 with a local CO2 generating capacity and an alkaline oxide; forming a first enhancing fluid comprising generated CO2 and delivering it into the first enhancement site having an injector well weighted first enhancement location, whereby mobilizing hydrocarbon in the first enhancement site; producing a produced fluid comprising mobilized hydrocarbon and enhancing fluid; recovering liquid hydrocarbon from the produced fluid; wherein the prescribed CO2 delivery distance is less than 67% of a remote CO2 delivery distance, to the first enhancement location from a remote calcining site having an equal or greater design calcined CO2 generating capacity.

Abstract: A system to calcine crushed carbonate, discharge alkaline oxide, and deliver an enhancing fluid having CO2, comprising: a pressurized insulated calciner having descendingly, a crushed alkaline carbonate feeder, a calciner fluid outlet manifold, a heated sideflow calciner fluid intake manifold, a preheated sideflow calciner fluid outtake manifold, a fluid inlet manifold to recirculate calciner fluid from the outlet manifold, and an alkaline oxide discharger; a pressurizer to repressurize sideflow calciner fluid, connected to intake and outtake manifolds; pressurizers to recirculate calciner outlet fluid to the inlet manifold, pressurize the calciner and deliver enhancing fluid comprising CO2; delivery and combustion systems to form a combustion fluid; a recuperating or regenerating refractory heat exchanger to heat sideflow calciner fluid with combustion fluid connected to the sideflow pressurizer, and fluid outtake and intake manifolds; and a controller operable to control combustion, heat exchange, calciner

Abstract: A method of supplying crushed alkaline carbonate from a carbonate resource to a first calcining site having a design calcining capacity; calcining the crushed carbonate within a prescribed carbon dioxide (CO2) delivery distance from a first enhancement location within a first hydrocarbon resource, whereby generating CO2 with a local CO2 generating capacity and an alkaline oxide; forming a first enhancing fluid comprising generated CO2 and delivering it into the first enhancement site having an injector well weighted first enhancement location, whereby mobilizing hydrocarbon in the first enhancement site; producing a produced fluid comprising mobilized hydrocarbon and enhancing fluid; recovering liquid hydrocarbon from the produced fluid; wherein the prescribed CO2 delivery distance is less than 67% of a remote CO2 delivery distance, to the first enhancement location from a remote calcining site having an equal or greater design calcined CO2 generating capacity.

Abstract: Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface.

Abstract: Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface.

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

Abstract: The invention relates to Radio Frequency (RF) antennas suitable for receiving and/or transmitting digital signals in the Ultra High Frequency (UHF) and/or Very High Frequency (VHF) ranges. The invention comprises a modular driven DUV antenna comprising a driven DUV element, an RF signal line RF communicatively connected to the driven DUV element, and an antenna mount supporting the DUV element; and a modular RF signal enhancer, supported by the antenna mount and selected from: an RF amplifier and a passive RF enhancer positioned to enhance the RF performance of the DUV antenna and comprising one of: an RF director, an RF reflector, and an RF booster.

Abstract: The invention comprises a Digital UHF/VHF (DUV) Antenna with a driven DUV antenna preferably boosted by an amplifier mounted close to the DUV dipole and a DUV signal line with antenna, amplifier, and signal line contacts being conductively bonded. The DUV dipole is preferably enhanced by a VHF enhancer and/or by a UHF enhancer comprising one of a reflective and a directive element. The UHF/VHF enhancer preferably includes an RF booster with a reflective element displaced from the longitudinal axis and near the driven antenna to enhance VHF signals. The DUV antenna is preferably configured for DTV reception in the VHF high band range of 174 MHz to 216 MHz, and in the UHF range of 470 MHz to 698 MHz.

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a thruster mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of the thruster, and a second control surface kinematically coupled to the aircraft at a position downstream of the thruster, the second control surface being differentially movable with respect to the first control surface such that a portion of the thrusted air from the thruster generates a first vector force on the first control surface and another portion of the thrusted air generates a second vector force on the second control surface, so that the first and the second vector forces provide a net roll moment about the Y-Roll axis.