There is provided a DC-DC converter which converts an input voltage into an output voltage for supply to a load, in which an input terminal receives the input voltage, an output terminal outputs the output voltage, power stages each includes: a high side switch, a low side switch and an inductor, the control unit executes a first mode and a second mode wherein the first mode controls the high side switch and the low side switch in each of the power stages so that a ratio of an output current in each of the power stages to a load current flowing through the load becomes a set value and the second mode controls the high side switch and the low side switch in each of the power stages so that duty ratios of the high side switch and the low side switch are equalized among the power stages.

A power control circuit for a power supply system including a control unit, a driving circuit and a power supply unit is disclosed. The power control circuit includes a current detection unit, a voltage detection unit and a power detection unit. The current detection unit is used for detecting a current signal. The voltage detection unit is used for detecting a voltage signal. The power detection unit is connected with the current detection unit, the voltage detection unit and the control unit for acquiring a power signal according to the current signal and voltage signal. By comparing an adjustable power reference signal with the power signal, the control unit issues a control signal to the driving circuit. In response to the control signal, the power supply unit is driven by the driving circuit to output an adjusted power to the load according to the adjustable power reference signal.

A mode controller shifts, along with increase in an electric power in first and second of chopper circuits and, operation modes of the first and the second of the chopper circuits from a first mode to a third mode via a second mode. An operation controller causes, in the first mode, the first of chopper circuit to perform an chopping operation, and the second of chopper circuit to suspend the chopping operation, in the second mode, causes the first and the second of chopper circuits to alternatively perform the chopping operations, and in the third mode causes both of the first and the second of chopper circuits to perform the chopping operations.

A device for accommodating objects, in particular for use in an airplane, comprises at least one panel. The panel has at least one outer edge which is provided with a rim in order to form a shock-absorbing edge. The rim comprises plastic that is integrally molded onto the outer edge of the panel. The device can be an airplane trolley, folding trolley, container or galley.

In a method for reducing the impact of a force upon a person seated in a safety seat of a motor vehicle at least a seat unit of the safety seat is restrained at least in part by at least one support strap. The support strap is formed with an extension piece configured to lengthen when exposed to a load as a result of an accident or explosion. A winding unit holds the support strap to shorten an effective length of the support strap and to build up a force to maintain the support strap under tension after the support strap underwent a lengthening in an area of the extension piece as a result of a load caused by a force resulting from an accident or explosion so as to reestablish an effective length of the support strap for lengthening during a subsequent force impact.

An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.

A method and apparatus for lighting a flight deck on an aircraft. A status of the aircraft is identified by a processor unit. The processor unit controls the lighting on the flight deck in response to the status of the aircraft to indicate the status of the aircraft.

Systems and methods for performing airport surface collision-avoidance. A wingtip-mounted camera allows the pilot to positively ascertain that the wingtip will clear objects located in the video. An exemplary system implemented on an aircraft includes a wingtip module having a camera that generates a video stream and a communication device that transmits the generated video stream. A processor receives the video stream and generates a reticule for the video stream. A display device simultaneously presents the video stream and the reticule. The reticule includes a horizon line and is based on a focal length of a lens of the camera and height of the camera above ground. The reticule includes curved and/or straight distance lines and curved or straight travel lines. The travel line(s) correspond to at least one aircraft component or a zone of importance and are based on location of the camera and trajectory of the aircraft.

The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Methods are disclosed for modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed. Surfaces interfacing between the swashplate and the mast and between control rods and the swashplate or pitch horn may bear a solid lubricant layer.

An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. The electrical motor does not have enough power to sustain flight of the vehicle.

A passively torque-balanced device includes (a) a frame; (b) a drivetrain including a drive actuator mounted to the frame and configured for reciprocating displacement, an input platform configured for displacement by the drive actuator, a plurality of rigid links, including a proximate link and remote links, wherein the rigid links are collectively mounted to the frame, and a plurality of joints joining the rigid links and providing a plurality of non-fully actuated degrees of freedom for displacement of the rigid links, the plurality of joints including a fulcrum joint that is joined both to the input platform and to the proximate rigid link; and (c) at least two end effectors respectively coupled with the remote links and configured for displacement without full actuation.

Individually operable ailerons pivotable to extend a forward end below a bottom wing surface and a rearward end above a top wing surface. The extended aileron forward end increases drag and subsumes the rudder function in the turn, while the aileron rear end produces drag and airflow redirection to reduce lift on the wing. The advantage of the safety ailerons is that habitual or instinctive pilot inputs to the yoke will recover from a dropped-wing stall at low speed and altitude, while conventional ailerons require counter-intuitive pilot actions to avoid crashing in such conditions.

An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

A space efficient lavatory module for commercial aircraft includes an aft facing concave wall recess that provides a greater distance from an upper, forward facing portion of a cabin structure, such as an aircraft passenger seat to avoid having a passenger's head impact the aft facing lavatory or enclosure wall in a sudden aircraft deceleration. The aft facing concave wall recess also provides space for mounting of a protective cushion, in order to reduce a passenger's risk of head trauma in a sudden deceleration, as well as other items, such as a video monitor, a bassinet or infant bed, without inhibiting passenger movement.

In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

A headrest assembly (1) for an ejection seat, comprising: a support mounting (2); and a pair of inflatable side beams (3), each attached at one end to the support mounting and spaced apart from one another, the side beams (3) being configured to be inflated from a stowed configuration to a deployed configuration in which the side beams extend from the support panel, the side beams (3) configured to deploy through: a capturing phase, during which the side beams are partially inflated from the stowed configuration such that they extend outwardly and upwardly from the support mounting and away from one another to surround the head of an occupant of the ejection seat toward a central location with respect to the support mounting.

An assembly for shielding an aircraft from electromagnetic energy may include a window mounting configured to be conductively coupled to an aperture in a fuselage of an aircraft. The window mounting may include a window pane having an electromagnetically-reflective coating for reflecting electromagnetic energy. The window pane may remain electrically isolated from the fuselage prior to the electromagnetic energy exceeding a frequency of approximately 1 GHz. The window mounting may further include a capacitive gasket capacitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz.

An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies.

A method and apparatus comprising a refueling controller. The refueling controller is configured to receive data about a current rate of movement of a refueling boom while the refueling boom is in contact with a receiver aircraft during flight. The refueling controller is further configured to disconnect the refueling boom from the receiver aircraft based on the current rate of movement of the refueling boom and a current position of the refueling boom.

A system has a plurality of spacecraft in orbit around the earth for collecting energy from the Sun in space, using stimulated emission to configure that energy as well defined states of the optical field and delivering that energy efficiently throughout the region of space surrounding Earth.

Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

A system and method for mitigating an aircraft incident is provided. The invention includes an aircraft panic component coupled to a terminal component. The aircraft panic component facilitates identification of a panic situation and communicates information associated with the panic situation to the terminal component. The aircraft panic component is further operative to at least partially disable a navigation system and/or operational system of an aircraft. The aircraft can then be sent to a safe zone, navigated remotely and/or a course of action for the aircraft can be determined. A safe zone component is adapted to facilitate identification of a course of action for the aircraft based at least in part upon aircraft positional information, aircraft condition information and/or aircraft resource(s). Further, aircraft navigational information and/or aircraft operational information can be sent via an aircraft communication component to a remote system having a remote communication component and a remote analyzing component facilitating transfer of information related to navigational and/or operational system(s) of the aircraft.

An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.

The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.

A projectile control system includes a plurality of fins, a drive mechanism coupled to each of the plurality of fins to enable the plurality of fins to be independently retracted or deployed, and a control mechanism in communication with the drive mechanisms to independently control the deployment or retraction of the plurality of fins. A projectile having the projectile control system and a method of operating a projectile are also described herein.

A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed.

An actuation system and method includes a tubular defining a passage, and an assembly disposed with the tubular. The assembly includes a restriction operatively arranged to receive a restrictor for enabling actuation of the assembly. The restriction includes a degradable material with a protective layer thereon, the degradable material degrading upon exposure to a fluid in the passage and the protective layer isolating the degradable material from the fluid.

Systems and methods for activating a down hole tool in a wellbore. A piston is moveable from a first position to a second position for activating the down hole tool. The piston includes a first side exposed to a first chamber, and a second side exposed to a second chamber. A rupture member has a first side exposed to the first chamber and a second side exposed to a third chamber. The rupture member is configured to rupture when a pressure differential between the first chamber and the third chamber reaches a predetermined threshold value, at which point the rupture member allows fluid communication between the first chamber and the third chamber. When the rupture member is intact, the piston is in the first position, and when the rupture member ruptures, the piston moves to the second position and activates the down hole tool.

A system for securing a first tubular to a second tubular including a housing having at least one group of at least one window therein. A gripping assembly is disposed in the housing and has at least one member operatively arranged for selectably extending through the at least one window for internally gripping the first tubular. A coupling unit is included having a first clamping mechanism and a second clamping mechanism. The first clamping mechanism is operatively arranged for externally clamping the housing, and the second clamping mechanism is operatively arranged for externally clamping the second tubular component. A method of securing together two tubular components is also included.

A stator for a progressive cavity pump comprises a stator housing having a central axis, a first end, and a second end opposite the first end. In addition, the stator comprises a stator liner disposed within the stator housing. The stator liner has a first end and a second end opposite the first end. The first end of the stator liner is axially spaced from the first end of the stator housing. Further, the stator comprises a tag insert positioned in the stator housing between the first end of the stator housing and the first end of the stator liner. The tag insert has a through passage defining a radially inner surface that includes a tag shoulder.

A casing window assembly for completion of a lateral wellbore. The casing window assembly includes a tubular casing sleeve with a casing window and an inner sleeve releasably secured within the casing sleeve at a pre-released position adjacent the casing window.

A tubular anchoring system includes a frustoconical member and a sleeve with at least one first surface that is radially alterable in response to longitudinal movement of the frustoconical member relative to the sleeve. The at least one first surface is engagable with a wall of a structure positioned radially thereof to maintain position of at least the sleeve relative to the structure when engaged therewith. A seal with at least one second surface is radially alterable in response to longitudinal movement of the frustoconical member relative to the seal, and a seat is in operable communication with the frustoconical member having a land which is sealingly engagable with a removable plug runnable thereagainst. The land is longitudinally displaced relative to the sleeve in an upstream direction defined by direction of flow that urges the plug thereagainst.

The well pump flow sleeve assembly provides a method of quickly fitting a flow sleeve to a well pump. The sleeve is made by cutting a pipe normal to the pipe centerline of the pipe surfaces, to a length appropriate for the well pump length. A pump centering bottom cap is inserted into the pipe lower opening and the well pump assembly is then inserted into the pipe upper opening and mates with the bottom cap to align the pump in the sleeve. The pump is now completely within the sleeve with the pump discharge and electrical connection extending through the pipe upper opening. Two flow sleeve cap halves are then fitted around the pump discharge and electrical connection/safety rope to form an upper cap which is inserted into the pipe upper opening. The submersible pump is then ready for service.

Fluid treatment systems and compositions are provided including (a) at least one material including (1) at least one carboxylic acid functional group and (2) at least one sulfur-containing group selected from the group consisting of sulfonyl functional groups, sulfonate functional groups and mixtures thereof; and (b) at least one friction reducing agent selected from the group consisting of guar gums, polyacrylamides, hydratable cellulosic materials, viscoelastic surfactants, and mixtures thereof. The fluid treatment systems and compositions can be used to treat aqueous systems, for example as fracturing fluids for use in fracturing subterranean formations. Methods for inhibiting formation and/or precipitation of metal oxides in an aqueous composition using the fluid treatment systems or compositions also are provided.

Fluid treatment systems and compositions are provided including (a) at least one material including (1) at least one carboxylic acid functional group and (2) at least one sulfur-containing group selected from the group consisting of sulfonyl functional groups, sulfonate functional groups and mixtures thereof; and (b) at least one scale control agent. The fluid treatment systems and compositions can be used to treat aqueous systems, for example as fracturing fluids for treating aqueous compositions found in subterranean formations. Methods for inhibiting formation and/or precipitation of calcium salts in an aqueous composition using the fluid treatment systems or compositions also are provided.

A borehole pump system includes an immersion pump (20) and a riser (15) accommodated in the borehole (10). A water treatment system for cleaning pumped water is disposed in the riser.

An oxygen scavenger for completion brines effective and stable in high temperature subterranean formations. In one embodiment, the scavenger contains erythorbate and alkylhydroxlyamine.

A method of servicing a wellbore that includes, transporting a fluid treatment system to a wellsite, accessing a water source proximate to the wellsite, introducing a water stream from the water source into the fluid treatment system, irradiating at least a portion of the water stream within the fluid treatment system, forming a wellbore servicing fluid from the irradiated water stream, and placing the wellbore servicing fluid into the wellbore. The portion of the water stream is irradiating by exposing the portion of water stream to ultraviolet light emitted from at least one pulsed ultraviolet lamp.

Systems and methods for managing umbilical lines and one or more jumpers are provided. An example of a system includes a deployment platform carrying a winch and spool assembly, a tether management assembly, and an integrated electrical and/or hydraulic umbilical line extending between a spool on the winch and spool assembly and the tether management assembly. The winch and spool assembly is configured to deploy and to support the umbilical line. The tether management assembly includes a winch and spool assembly for deploying a flying lead and/or annulus jumper adapted to connect to an emergency disconnect package of a well control package for a well. A set of buoyant modules are connected to or integral with a portion of the umbilical line to be used to form an artificial heave compensation loop.

A system for diverting fluids from a wellhead in a subsea environment has a capping stack with a connector suitable for connection or interconnection to the wellhead, a flow base fixedly positioned in the subsea environment, and a conduit connected to the outlet of a diverter line of the capping stack and connected to the inlet of an interior passageway of the flow base. The conduit is suitable for passing fluids from the capping stack toward the flow base. The flow base is a modified horizontal Christmas tree. The interior passageway within the horizontal Christmas tree has a plug therein located a level below the level of the inlet to the flow base. The flow base can be attached to a wellhead or to an anchor pile in the subsea environment.

An adapter assembly having a sealing element, a drive bushing, and an adapter flange disposed between the sealing element and the drive bushing. Also, a method of assembling a rotational control device that includes coupling mechanically an adapter flange to a sealing element, coupling mechanically the adapter flange to a drive bushing, and installing the adapter flange, sealing element, and drive bushing in the rotational control device.

A marine riser includes one or more buoyancy modules running along a length of the marine riser, wherein the one or more buoyancy modules are molded such that an umbilical may be secured along a length of the one or more buoyancy modules.

A tensioning apparatus for applying a substantially constant tension to a workover riser (12) includes a first portion (40) adapted to be coupled to a workover riser, a second portion (44) adapted to be coupled to a marine riser (14) and tensioning means (46) for providing relative movement between the first portion and the second portion to, in use, tension the workover riser.

A method and a device for enabling the use of riserless drilling fluid recovery from a seabed-based borehole (1) which is to be drilled by means of a casing (26), the casing (26) being provided with a drill bit (28) at its lower portion and with an inner wellhead (30) at its upper portion, and there being a conductor casing (6), which has an outer wellhead (8), in the seabed (2), the method including: —providing a suction module (12) with a dividable adapter (16) which fits complementarily in the outer wellhead (8); —drilling a length of the borehole (1) by means of the casing (26) extending through the suction module (12), while, at the same time, drilling fluid is flowing via the suction module (12) from the borehole (1); —subsequently pulling the adapter (16) up from the outer wellhead (8) and dividing the adapter (16); and—lowering the casing (26) with the inner wellhead (30) through the suction module (12) and the adapter (16) to its position in the outer wellhead (8).

A hydrocarbon drilling tubulars storage and handling system, said system comprising: —first and second rotary storage racks, each rotary storage rack being rotatable about a vertical axis and having storage slots for storage of multiple tubulars in each rotary storage rack in vertical orientation, the first and second rotary storage rack each including a drive to rotate the storage rack about its vertical axis, —a tubulars racking device positioned between the first and second rotary storage racks, said racking device including a rotary structure that is rotatable about a vertical axis and a drive to rotate the rotary column structure about said vertical axis, the rotary structure supporting at a first side thereof a first tubular racker assembly and at a second side thereof a second tubular racker assembly, each tubular racker assembly including one or more one gripping members adapted to grip a tubular.

An anchoring assembly in a downhole tool, the assembly including a first tubular member, a second tubular member coupled to the first tubular member, and an anchoring block disposed between the first tubular member and the second tubular member. The anchoring block includes a body having a central axis defined therethrough and a central bore formed therethrough, a contact crown, in which at least one annular flow channel is formed between the contact crown and the body, and a contact ring configured to engage at least a portion of the first tubular member.

A technique includes processing seismic data indicative of samples of at least one measured seismic signal in a processor-based machine to, in an iterative process, determine basis functions, which represent a constructed seismic signal. The technique includes in each iteration of the iterative process, selecting another basis function of the plurality of basis functions. The selecting includes based at least in part on the samples and a current version of the constructed seismic signal, determining a cost function; and interpreting the cost function based at least in part on a predicted energy distribution of the constructed seismic signal to select the basis function.

A steam assisted gravity drainage process that includes the addition of oxygen for recovering hydrocarbons from a hydrocarbon reservoir is described. Steam and an oxygen-containing gas are separately and continuously injected into the hydrocarbon reservoir to heat hydrocarbons and water to drain, by gravity, to a horizontal production well. The process can include controlling the ratio of oxygen and steam from about 0.05 to about 1.00 (v/v). The steam assisted gravity drainage process can further include removing non-condensable combustion gases from the reservoir to avoid undesirable pressures in the reservoir. The non-condensable combustion gases can be removed from the reservoir by at least one separate vent-gas well.