204results about How to "Sufficient electricity" patented technology

A transcutaneous recharging system for providing power to an implantable medical device comprises a primary side circuit for transmitting power in the form of magnetic flux; and a secondary side circuit integral to the implantable medical device for receiving the power transmitted from the primary side circuit and for providing the received power to recharge a battery in the implantable medical device, wherein the primary and secondary side circuits are not physically coupled. A variety of attachment configurations are disclosed for attaching and shielding the secondary circuit directly onto the housing of the implantable medical device, inclusive of flexible printed circuit coils and wire coils recessed into helical notches.

A light-emitting diode (“LED”) based strobe may be used in automated system to provide a visual alert to occupants and/or building personnel if an emergency condition exists. A LED based strobe provides an even distribution of light having a sharp, bright pulse of light desired for emergency evacuation using lower power consumption.

A system is provided for treating fatty tissue sites of a patient. At least first and second mono-polar electrodes are configured to be introduced at or near the fatty tissue site of the patient. A voltage pulse generator is coupled to the first and second mono-polar electrodes. The voltage pulse generator is configured to apply sufficient electrical pulses between the first and second mono-polar electrodes to induce electroporation of cells in the fatty tissue site, to create necrosis of cells of the fatty tissue site, but insufficient to create a thermal damaging effect to a majority of the fatty tissue site. The system can be incorporated into standard liposuction devices or used simultaneously to treat and remove the tissue.

A main generator delivers an AC voltage to an electricity network on board an aircraft via a main line having at least one line contactor mounted therein, the voltage being regulated by a regulator. An engine electricity network delivers electricity to various loads situated in the zone of an engine fitted to the aircraft and to an engine control computer, the engine electricity network having a first fed input connected to the main electricity power supply line via a secondary electricity power supply line, upstream from the line contactor in order to receive directly electricity derived from the main generator without transiting via the electricity network on board the aircraft. The voltage regulator regulating the voltage delivered by the main generator may be situated in the engine zone and is powered by the engine electricity network.

An operative instrument includes forceps having a treating section for treating an anatomy at an extremity and being provided with a heat-generating body for generating heat to be provided to the anatomy and a power supply unit for supplying electric power to the heat-generating body of the forceps. The operative instrument raises the temperature of the heat-generating body by supplying substantially constant electric power to the heat-generating body. Therefore, coagulation and incision of the anatomy can be performed satisfactorily.

A safety arrangement (1) for a motor vehicle having an electric battery (2) and an occupant safety device (6) such as an airbag (7) or seat-belt pre-tensioner. The arrangement (1) having a crash sensor (10) responsive to acceleration, a battery sensor (13-17) arranged to monitor a battery parameter indicative of the condition of the battery, an actuator (8) for activating the occupant safety device (6), and a control unit (9) operable to receive and process signals (x,b) from both the crash sensor (10) and the battery sensor (13-17). The control unit (9) is operable to issue an actuating command to the actuator (8) to activate the occupant safety device (6) in response to a signal x from the crash sensor. In a preferred embodiment, there is provided a second actuator (23,24,25) for activating a battery safety device (20,21,22); the control unit (9) being operable to issue an actuating command to the second actuator to activate the battery safety device upon receipt of both: i) a signal (x) from the crash sensor exceeding a predetermined threshold value X₁ and a ii) a signal b from the battery sensor satisfying a predetermined criterion.

A rotating electrical machine, such as an aircraft starter-generator, includes an exciter that has its stator windings divided into a number of sections. A plurality of switches are electrically coupled to the exciter stator winding sections and are configured and controlled so that the exciter stator winding sections may be selectively coupled in series or in parallel with one another, and selectively coupled to receive either DC or AC power.

A chopper regulator circuit has: a power output portion for a first and a second load; a first output detection portion detecting the output to the first load; a second output detection portion detecting the output to the second load; a first and a second reference voltage generation portion; an output control portion controlling the amount of outputted electric power based on a result of comparison between two input voltages; and a switching control portion switching which of the first and second loads to supply electric power to and switching what voltages to handle as the input voltages. The input voltages are so switched that, when electric power is supplied to the first load, the detected voltage detected by the first output detection portion and the reference voltage generated by the first reference voltage generation portion are handled as the input voltages and, when electric power is supplied to the second load, the detected voltage detected by the second output detection portion and the reference voltage generated by the second reference voltage generation portion are handled as the input voltages. Thus, a chopper regulator circuit is realized that can easily supply two loads with adequate electric power with minimum disadvantages such as an increase in the total number of components needed.

To recover in situ viscous oil from an underground reservoir, electricity is conducted through the underground reservoir by at least two electrodes in an amount that would, in the absence of solvent injection, cause water in the reservoir to vaporize adjacent to the electrodes, and injecting solvent into the reservoir to mitigate water vaporization adjacent to the electrodes by vaporizing solvent in this region. Oil and solvent are produced through one or more production wells.

The invention relates to a novel energy-saving glass curtain wall, wherein the shortcoming of natural wind is compensated through mechanical assisted air supply mode, and the problem of unsustainable and unstable airflow is solved. An air inlet is arranged on the windward side, an air outlet is arranged on the leeward side, the air inlet and the air outlet are connected through a ventilating duct or 'an architectural layer ventilating duct' to ensure the air flow smoothly. The distance between the air inlet and the air outlet is increased, the differential pressure of air can be realized, and the effect of 'a chimney effect' is improved. A fireproof grade of an outside curtain wall is lower than a fireproof grade of an inside curtain wall, and the fireproof capacity of a double layer curtain wall is basically same as a single layer curtain wall, the fireproof capacity can be improved through a smoke detector and a spray system. In summer, the invention adopts the mode of spray desuperheating through a fire-fighting spray system, and in daytime pollution-free power supply is supplied to an air supply system and a draught fan through solar energy. According to the improvement, the integrated effect of the double layer glass curtain wall and 'a climate adaptive capacity' is hoped to be improved, and a new idea is provided to the development of the curtain wall and the technological innovation.

An output of a resonant circuit 60 which electromagnetically couples with an external communications apparatus is rectified and taken out, and a resultant output voltage V is monitored by a switch control circuit 61. After the output voltage V has risen to or beyond a threshold Vth1, a switch element SW is turned on and off, and a state of the switch element SW in which the output voltage V becomes higher is determined. While holding the switch element SW in the state thus determined, a power supply switch element PSW is turned on when the output voltage V has further risen. As a result, even when a plurality of noncontact IC cards 6 overlaid with one another are brought close to the communications apparatus, the individual noncontact IC cards 6 can carry out data communication.

A controlled-release fuel cell comprising (a) a proton exchange membrane having a first surface and a second surface, a fuel electrode or anode being coupled to the first surface, and an oxidant electrode or cathode being coupled to the second surface; (b) a fuel flow field plate having surface channels positioned in front of the anode with the channels containing therein a controlled-release material that retains a liquid fuel at or below an ambient temperature, but releases the fuel at a temperature higher than an activation temperature to deliver a fuel vapor to the anode; (c) heating means in heat-supplying relation to the controlled-release material to activate fuel vapor release on demand at a desired rate; and (d) fuel supply means that feeds the liquid fuel to the controlled-release material. The invented fuel cell is compact and lightweight, with significantly reduced fuel crossover and improved fuel utilization efficiency. The fuel cell is particularly useful for powering small vehicles and portable devices such as a notebook computer, a personal digital assistant, a mobile phone, and a digital camera.

The invention discloses a cargo cabin component for an unmanned aerial vehicle and the unmanned aerial vehicle with the same. The unmanned aerial vehicle comprises a vehicle body, the vehicle body is provided with a power supply battery, the cargo cabin component is detachably arranged on the vehicle body, the cargo cabin component comprises a cargo cabin, a cabin door and a rechargeable battery, wherein the cargo cabin has an entrance and an exit, and a chamber used for loading cargoes is limited in the cargo cabin; the cabin door is arranged on the cargo cabin and used for opening or closing the exit; the rechargeable battery is arranged on the cargo cabin and comprises a charging port suitable for connecting with an external power supply, and the rechargeable battery is suitable for matching with the power supply battery to charge the power supply battery. The cargo cabin component is capable of providing enough electricity for the unmanned aerial vehicle, and the cyclic utilization rate of the cargo cabin is improved.

The solar powered soffit fan includes an electric fan mounted over a soffit vent. A roof-mounted photovoltaic solar panel aimed at the sun delivers power to the soffit fan. During daylight hours, the photovoltaic solar panel provides sufficient electrical power to activate the soffit fan, which provides forced attic ventilation through the soffit vent. At night, the fan automatically powers down when sunlight no longer impinges the solar panel. A thermostat and/or humistat can be included for additional control of the unit. The fan can accept power from an optional rechargeable battery. Multiple soffit fans can be configured to service larger buildings.

A control system for a hybrid vehicle, in which an engine is connected to a first motor generator and to an output shaft through a power distributing mechanism (12), in which a second motor generator is connected to the output shaft through a transmission (6) wherein a torque capacity is varied in accordance with an oil pressure, and which has an electric oil pump (OPM) for generating an oil pressure, comprising: an oil pressure judging means for judging whether or not the oil pressure established by operating OPM is raised higher than a preset value; an electric oil pump output lowering device for lowering an output of OPM in case the oil pressure judging device judges that the oil pressure is raised higher than the preset value; and a cranking device for carrying out a cranking of E/G by the first motor generator.

A vehicle control system is provided to improve a response of shifting operation of a drive mode while avoiding a shortage of drive force. The control system is applied to a hybrid vehicle having an internal combustion engine and two motors, and configured to select a drive mode from a mode where the vehicle is powered by the engine and a mode where the vehicle is powered by at least one of the motors while stopping the engine. The control system predicts a fact that the engine is expected to be started based on a detection value representing a running condition of the vehicle, during propulsion of the vehicle by the two motors while stopping the engine; shifts a drive mode to a mode where the vehicle is powered by one of the motors without using a power of the other motor to be used to start the engine; and starts the engine upon satisfaction of a condition for propelling the vehicle by the power of the other motor.

According to a liquid crystal display device (1), a gate driver is controlled to (a) scan all of scan signal lines during at least two driving frames contained in a first driving period and (b) not scan any of the scan signal lines during pausing frames in a pausing period which is (i) secured between the first driving period and a second driving period by which the first driving period is followed and (ii) is longer than each of the first and second driving periods.

An aircraft (1) having a rotary wing (2) and turboshaft engines (11, 12, 13) for driving said rotary wing (2). The aircraft then includes two main engines (11, 12) that are identical, each capable of operating at at least one specific rating associated with a main power (maxTOP, OEIcont), and a secondary engine (13) capable of operating at at least one specific rating by delivering secondary power (maxTOP′, OEIcont′) proportional to the corresponding main power (maxTOP, OEIcont) in application of a coefficient of proportionality (k) less than or equal to 0.5, said aircraft having a control system (20) for driving the rotary wing by causing each main engine (11, 12) to operate continuously throughout a flight, and by using the secondary engine (13) as a supplement during at least one predetermined specific stage of flight.

An internal combustion engine has a combustion chamber having a spark plug arranged thereat. A crankcase supports a crankshaft. An intake for introducing fuel and combustion air into the combustion chamber is provided. An exhaust for exhausting combustion gases from the combustion chamber is provided. A piston is connected to the crankshaft and drives the crankshaft in rotation. A wheel member is connected to the crankshaft and rotates with the crankshaft. An alternator driven by the crankshaft supplies electric power to a consumer. The alternator is arranged within a radial boundary of the wheel member and external to the crankcase. The alternator has a stator and a rotor, wherein the crankshaft penetrates the stator and wherein the rotor is fixedly connected to the wheel member.

An electrically driven brake device includes a plurality of brake actuators for generating braking force when driven electrically, a power supply source for storing electric energy and supplying power to the brake actuators, a power source line for connecting the power supply source and the brake actuators, and a power breaker at a position of the power source line at which the brake actuators can be insulated and separated into at least two systems.

An electrically powered HVAC system for electric vehicles with a combined energy recovery powered electric generator is disclosed. The present invention is an improvement in that it incorporates a compact designed turbine and electrical power generator into the AC unit that is driven by energy recovered within the Rankine cycle loop. The unit's compact design yields a favorable power to weight ratio—its small turbine and generator package produces a lot of power for its light weight. Additionally, the invention requires no outside power source to drive the generator. Rather, the combined turbine/generator recovers energy from high pressure vapor as it flows through the turbine manifold where it causes the turbine/rotor which incorporates permanent magnets, to spin around the stator thus creating electricity. The electricity created is used to charge the auxiliary battery, operate the compressor and other electrical HVAC components, or power other low voltage systems within the vehicle.