Patent application number | Description | Published |
20130269313 | PROPULSION SYSTEM FOR FLYING MACHINE, PARTICULARLY FOR A MISSILE - A propulsion system including: a booster; a turbojet engine; the booster including a chamber which is fixed to a rear casing of the turbojet engine by being arranged along the longitudinal axis thereof, which chamber includes at a rear a jet pipe and includes at least one charge and a mechanism initiating the charge; and gas bleed tubes connected to the booster and which are configured either for igniting the combustion chamber of the turbojet engine on for starting the turbine of the turbojet. | 10-17-2013 |
20130333365 | CONTROLLING METHOD AND SYSTEM FOR COMPRESSED AIR SUPPLY TO A PNEUMATIC NETWORK, IN PARTICULAR IN AN AIRCRAFT - A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor. | 12-19-2013 |
20150089921 | AUXILIARY POWER SUPPLY METHOD THROUGH AN AUXILIARY POWER UNIT AND CORRESPONDING ARCHITECTURE - An auxiliary power supply architecture includes one APU and a fuel supply basic circuit with a common fuel storage tank, a primary circulation conduct and secondary conducts for injecting such fuel into the combustion chambers of the APU unit through appropriate injectors. Such architecture also includes another independent fuel supply circuit to supply the APU unit with an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chambers through appropriate injectors. | 04-02-2015 |
20150122944 | METHOD AND ARCHITECTURE FOR THE OPTIMIZED TRANSFER OF POWER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER - A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines. | 05-07-2015 |
20150246733 | DEVICE AND METHOD FOR SUPPLYING NON-PROPULSIVE POWER FOR AN AIRCRAFT - Method for supplying non-propulsive power for an aircraft, comprising the driving of a shaft ( | 09-03-2015 |
20150333527 | METHOD FOR MANAGING THE ELECTRIC POWER NETWORK OF AN AIRCRAFT - A method for managing an electrical power supply system ( | 11-19-2015 |
20150360630 | METHOD AND SYSTEM FOR SUPPLYING AN AIRCRAFT WITH ELECTRICAL POWER - A method and a system for supplying electrical energy to an aircraft that is equipped with a plurality of loads to be powered, said power supply system comprising a plurality of power sources and an on-board energy management module, the energy management module being electrically connected to said power sources and to said loads to be powered. The energy management module is arranged so as to control a supply of power to at least one of said loads using at least two different power sources in parallel in the event of increased energy requirements, said load being initially powered by a single power source. | 12-17-2015 |
20150367952 | STRUCTURE FOR FEEDING AIR TO AN AUXILIARY POWER UNIT IN AN AIRCRAFT - The invention concerns a structure ( | 12-24-2015 |