Abstract: Aircraft control surface actuation systems and methods are described herein. An example control surface actuation system includes an interface cable, a test interface, and a controller. The test interface is to be disposed in an electrical equipment (EE) bay of an aircraft and operatively coupled to an actuator associated with a control surface of the aircraft. The interface cable is to be connected between the test interface and the controller, and the controller is to transmit a signal via the interface cable to the test interface to control the actuator.

Abstract: Aircraft control surface actuation systems and methods are described herein. An example control surface actuation system includes an interface cable, a test interface, and a controller. The test interface is to be disposed in an electrical equipment (EE) bay of an aircraft and operatively coupled to an actuator associated with a control surface of the aircraft. The interface cable is to be connected between the test interface and the controller, and the controller is to transmit a signal via the interface cable to the test interface to control the actuator.

Abstract: Embodiments of the present disclosure provide an apparatus and method for managing an orientation of a tab of a control surface of an aircraft comprising an elongate structure having a number of members configured to position the elongate structure to a control surface, a bracket located on the elongate structure, a plurality of indicators located along the elongate structure, and a data processor in communication with the plurality of indicators. The bracket may be positioned against an edge of a tab of the control surface. Each of the plurality of indicators may be configured to generate a number of measurements about an orientation of the tab on the control surface. The data processor may be configured to present information about the orientation of the tab on the control surface.

Abstract: A centrifugal propellant depot positioned in outer space for storing and transferring cryogenic liquid propellants to and from transfer space vehicles which are adapted to transport cryogenic liquid propellants to the depot to receive the liquid propellants stored in the depot. The depot includes a plurality of contra-rotatable torus-shaped hollow storage tanks adapted to receive cryogenic liquid oxygen and hydrogen propellants that are carried in gas/liquid phase separation by rotational gravity. Transport rail members transversely bridge the storage tanks. A central docking hub is coupled to the transport rail members and disposed centrally of the rotating storage tanks. The docking hub may receive a transfer space vehicle on either of two opposing sides of the hub for transfer, via a transfer vehicle coupled to the rail members, outwardly to the storage tanks.

Abstract: The purpose integrated aerospike rocket engine and space vehicle aerobrake is to provide for optimum installation and performance of these systems in a space vehicle. By integrating the aerospike engine into the middle of the aerobrake, the engine can be located with its center of gravity toward the face of the aerobrake. This location permits the maximization of the displacement of the aerodynamic center of pressure of the aerobrake relative to the center of gravity of the space vehicle, thereby maximizing the stability of the vehicle upon aerodynamic capture at the earth or another planet. By substituting an aerospike rocket engine for a conventional bell nozzle engine, the doors required to close the aperture in the aerobrake to accommodate the conventional engines can be eliminated. In addition to the unique combination of the aero-spike engine and the aerobrake, an included unique feature of the invention is the extendable nozzle plug.

Abstract: A multi-layer blanket insulation adapted of use in an aerobrake intended to assist in the return of a space vehicle from a higher earth orbit to a low earth orbit for recovery and possible reuse. Between two face sheets of a cloth material highly resistant to elevated temperatures are interposed a layer of a flexible insulative material and a layer of non-porous foil. The insulation is stitched together into a predetermined pattern. A backside stiffener may be secured to the back face by a layer of a suitable cloth material.

Abstract: An endotracheal tube having dual passages provided by the merging of a ventilation tube and a suction tube. The ventilation tube is adapted to project into a patient's trachea to the position of the carina anterior. An inflatable cuff surrounds the ventilation tube and prevents passage of fluids to and from the lungs. The suction passage terminates at the cuff with openings into the suction passage for suctioning secretions that pool around the cuff. The tubes as merged enable entry of the dual passages into the trachea past the vocal cords. As protruded from the patient's mouth, the tubes are separated to be connected to the respective ventilation machine and secretion suction machine.

Abstract: A method for recovering hydrocarbons from a subterranean formation in which steam, for example, is injected into the formation via an injection well to drive the hydrocarbons toward a spaced production well. Water injected via the production well into an upper horizon of the formation is passed downwardly through the formation about the production well and then back into the production well at a lower horizon in the formation. A mixture of displaced hydrocarbons and injected water are then coproduced at the lower horizon thru the production well after which the hydrocarbons are recovered from the mixture. Optionally, a minor amount of a sulfated interfacial tension reducer may be introduced with the steam to promote increased hydrocarbon recovery.

Abstract: A method for recovering hydrocarbons from a subterranean formation in which steam, for example, is injected into the formation via an injection well to drive the hydrocarbons toward a spaced production well. Water injected via the production well into an upper horizon of the formation is passed downwardly through the formation about the production well and then back into the production well at a lower horizon in the formation. A mixture of displaced hydrocarbons and injected water are then coproduced at the lower horizon thru the production well after which the hydrocarbons are recovered from the mixture. Optionally, a minor amount of a sulfated interfacial tension reducer may be introduced with the steam to promote increased hydrocarbon recovery.