Abstract: The present invention relates to a process for extracting a crude oil from a rock formation containing it, comprising the following steps: (i) a first step of forced injection of a modified alkylphenol-aldehyde resin into the rock formation containing a crude oil, then (ii) a second step of extracting the crude oil from the rock formation.

Abstract: The invention relates to a lubricity additive for fuel, particularly for diesel fuel, directly obtained from the acidification of a soapstock produced by a method for refining at least one vegetable and/or animal oil. The lubricity additive according to the invention is more specifically used for fuels that have a low sulfur content, for example, lower than 500 ppm (by weight).

Abstract: A process for manufacturing a lubricant additive for internal combustion engine fuel, especially for diesel fuel, in which the additive is derived, especially directly, from the esterification of acid oils, such acid oils are especially coming from the acidification of neutralization paste obtained via a process for refining, preferably a process for chemical refining, and especially a process for saponifying, one or more oils chosen from a plant oil and/or an animal oil, and the lubricant additive is more particularly intended for fuels with a low sulfur content, for example less than 500 ppm (weight).

Abstract: The invention relates to a lubricity additive for fuel, particularly for diesel fuel, directly obtained from the acidification of a soapstock produced by a method for refining at least one vegetable and/or animal oil. The lubricity additive according to the invention is more specifically used for fuels that have a low sulfur content, for example, lower than 500 ppm (by weight).

Abstract: A device and method for coupling two parts of a dc network, in which at least two capacitors respectively are installed, particularly onboard an aircraft. The device includes at least one static converter including at least one electronic coupling device, including at least one transistor and one diode, associated with an inductance, arranged between these at least two capacitors.

Abstract: A device and a method for emergency electricity supply on board an aircraft, able to supply a part of the aircraft's electrical power circuit. The device includes a synchronous machine with separate excitation, associated with a flywheel, and an auxiliary device to set the flywheel in rotation and to maintain rotation of the flywheel.

Abstract: A device and a method for emergency electricity supply on board an aircraft, able to supply a part of the aircraft's electrical power circuit. The device includes a synchronous machine with separate excitation, associated with a flywheel, and an auxiliary device to set the flywheel in rotation and to maintain rotation of the flywheel.

Abstract: A device and method for coupling two parts of a dc network, in which at least two capacitors respectively are installed, particularly onboard an aircraft. The device includes at least one static converter including at least one electronic coupling device, including at least one transistor and one diode, associated with an inductance, arranged between these at least two capacitors.

Abstract: The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

Abstract: A device and a method to generate electricity on board an aircraft, including plural generators and plural air-conditioning units having an outside air intake. This device includes a control to command air-conditioning units as emergency generators and a storage device.

Abstract: A system and a power supply method, on board an aircraft, in which the power supply system of an aircraft includes several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aircraft are connected to each of these cores. Each core includes an input driver, several identical power modules, means of placing in parallel several power modules including interconnection inductances between power modules, and a switching matrix including a set of relays, means of piloting the relays of the switching matrix, so as to reconfigure all of these relays in the case of failure of a power module, several output filters, and relays of the switching matrix that may each be connected to at one load.

Abstract: The invention relates to an electrical emergency source device fitted on an aircraft, which comprises an energy source capable of outputting the power necessary for vital electrical loads (10) to operate correctly, wherein there are two types of these loads: first loads, that absorb a constant power with time, second loads, that absorb variable power with time. Wherein this device comprises: a power source (12) sized to output the average power absorbed by all loads, a power source (15) capable of supplying power peaks absorbed by the second loads, and wherein, since the power of several loads is reversible, the power of the said device is also reversible.

Abstract: The invention relates to an electrical emergency source device fitted on an aircraft, which comprises an energy source capable of outputting the power necessary for vital electrical loads (10) to operate correctly, wherein there are two types of these loads: first loads, that absorb a constant power with time, second loads, that absorb variable power with time. Wherein this device comprises: a power source (12) sized to output the average power absorbed by all loads, a power source (15) capable of supplying power peaks absorbed by the second loads, and wherein, since the power of several loads is reversible, the power of the said device is also reversible.

Abstract: The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

Abstract: The invention relates to a system and a power supply method, on board an aircraft. The power supply system of an aircraft comprises several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aeroplane are connected to each of these cores, in which each core comprises: an input driver (40), several identical power modules (CVS1 . . . CVSn), means of placing in parallel several power modules comprising interconnection inductances (41) between power modules, and a switching matrix (42, 44) comprising a set of contactors, means (52) of piloting the contactors of the switching matrix (42, 44), so as to reconfigure all of these contactors in the case of failure of a power module, several output filters (43), contactors (44) of the switching matrix (42, 44) that may each be connected to at one load (Cij).