# US 9,828,110 B2 · System for recovering and converting kinetic energy and potential energy as electrical energy for an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,828,110 B2 - Document ID: US9828110B2 - Status: Granted - Kind: B2 - Application number: 14/781,894 - Filed: 2014-04-01 - Published: 2016-02-04 - Granted: 2017-11-28 - Earliest claimed: 2013-04-02 - Assignees: Labinal Power Systems - Applicants: Labinal Power Systems - Inventors: Serge Roques - Web page: https://patentgrep.com/patent/US9828110B2 ## CPC - B64D 41/007: {Ram air turbines} - B60K 16/00: Arrangements in connection with power supply of propulsion units in vehicles from forces of nature, e.g. sun or wind (electric propulsion with power supply from forces of nature, e.g. sun or wind, B60L8/00; wind motors specially adapted for installation on vehicles F03D9/32) - B64D 41/00: Power installations for auxiliary purposes - F03D 1/04: having stationary wind-guiding means, e.g. with shrouds or channels (F03D9/35 takes precedence) - F03D 1/06: Rotors - F03D 9/10: Combinations of wind motors with apparatus storing energy - F03D 9/11: storing electrical energy - F03D 9/25: the apparatus being an electrical generator (F03D9/22 takes precedence) - F03D 9/32: on moving objects, e.g. vehicles - B64D 2041/002: {Mounting arrangements for auxiliary power units (APU's)} - F05B 2220/31: in ram-air turbines ("RATS") - Y02E 10/72: Wind turbines with rotation axis in wind direction - Y02E 10/728: Onshore wind turbines - Y02E 70/30: Systems combining energy storage with energy generation of non-fossil origin - Y02T 50/50: On board measures aiming to increase energy efficiency - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B60K: ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES - F03D: WIND MOTORS - F05B: INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An electrical energy generator system for an aircraft, the system including a streamlined fairing containing at least one turbine housed in the front portion of the fairing, and an electrical energy generator connected to said turbine. The front portion of the fairing is fitted with air admission means that are movable between an open position in which the turbine is exposed to the stream of air outside the fairing and a closed position in which the turbine is masked inside the fairing. The system may serve to reduce the aerodynamic drag caused by turbulence present at a wing tip for a conventional wing having sharp edges during stages of takeoff, climbing, and cruising; and during stages of descent it makes it possible to recover the kinetic and potential energy that has been accumulated by the aircraft during its stages of climbing and cruising. ## Claims ### Claim 1 An electrical energy generator system for an aircraft, wherein the system comprises: a shell having the shape of a wing tip tank, wherein the shell comprises a front portion, a body, and a rear portion; at least one turbine housed in the front portion of the shell; and an electrical energy generator connected to the at least one turbine, wherein the electrical energy generator is configured to generate electrical energy, wherein the front portion of the shell includes flaps that are movable between an open position in which the at least one turbine is exposed to the air stream outside the shell, and a closed position in which the at least one turbine is masked inside the shell, and wherein the flaps are movably fastened between a nose of the shell and the body of the shell, wherein the flaps are hingedly fastened to the nose, the flaps being lowered inside and/or into the shell in the open position, and the flaps being held in alignment with the body of the shell in the closed position. ### Claim 2 (depends on 1) A system according to claim 1, characterized in that the system further comprises a storage means configured to store the electrical energy generated by the electrical energy generator. ### Claim 3 (depends on 2) A system according to claim 2, characterized in that the storage means includes at least one electrical energy storage means selected from at least one of the following: a battery; a supercapacitor; and a flywheel. ### Claim 4 (depends on 1) A system according to claim 1, characterized in that the system includes airflow openings in the rear portion of the shell. ### Claim 5 (depends on 1) A system according to claim 1, characterized in that the at least one turbine has variable pitch blades. ### Claim 6 (depends on 1) An aircraft including at least one electrical energy generator system according to claim 1. ### Claim 7 (depends on 6) An aircraft according to claim 6, characterized in that the aircraft includes a control device and actuators connected to the flaps via a linkage system to cause the flaps to open. ### Claim 8 (depends on 6) An aircraft according to claim 6, characterized in that the aircraft includes a control device and actuators connected to the flaps via a linkage system, enabling the flaps to be opened manually in the event of an urgent need for electrical energy. ### Claim 9 An electrical energy generator system for an aircraft, wherein the system comprises: a shell having the shape of a wing tip tank, wherein the shell comprises a front portion, a body, and a rear portion; at least one turbine housed in a front portion of the shell; and an electrical energy generator connected to the at least one turbine, wherein the electrical energy generator is configured to generate electrical energy, wherein the front portion of the shell includes slats that are movable between an open position in which the at least one turbine is exposed to the air stream outside the shell, and a closed position in which the at least one turbine is masked inside the shell, wherein the slats are pivotally fastened between a nose of the front portion of the shell and the body, and wherein the slats extend perpendicularly relative to a surface of the shell in the open position and are held parallel with the surface of the shell in the closed position. ### Claim 10 (depends on 9) A system according to claim 9, characterized in that the at least one turbine has variable pitch blades. ### Claim 11 (depends on 9) A system according to claim 9, wherein the system further comprises a storage means configured to store the electrical energy generated by the electrical energy generator. ### Claim 12 (depends on 11) A system according to claim 11, wherein the storage means includes at least one electrical energy storage means selected from at least one of the following: a battery; a supercapacitor; and a flywheel. ### Claim 13 (depends on 9) A system according to claim 9, wherein the system includes airflow openings in the rear portion of the shell. ### Claim 14 (depends on 9) An aircraft including at least one electrical energy generator system according to claim 9. ### Claim 15 (depends on 14) An aircraft according to claim 14, wherein the electrical energy generator system includes a control device and actuators connected to a pivot shaft and links to cause the slats to open. ### Claim 16 (depends on 14) An aircraft according to claim 14, wherein the electrical energy generator system includes a control device and actuators connected to a pivot shaft and links enabling the slats to be opened manually in the event of an urgent need for electrical energy.