• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Aircraft The invention provides an aircraft (10) having the following characteristics: the aircraft (10) comprises electrical components (12, 13) and a fan casing with a cooling coil (14); and the aircraft (10) is provided to discharge the heat from the electrical components (12, 13) to the cooling coil. Figure to be published with the abstract: Fig. 1
    公开号:FR3083519A1
    申请号:FR1907240
    申请日:2019-07-01
    公开日:2020-01-10
    发明作者:Thomas Warbeck
    申请人:Dr Ing HCF Porsche AG；
    IPC主号:
    专利说明:

    Description
    Title of invention: Aircraft
    The present invention relates to an aircraft, in particular a fully electric aircraft, with vertical take-off and landing (VTOL).
    VTOL, in aerospace technology, goes beyond linguistic definitions to designate all types of aircraft, drones or rockets which have the capacity to take off and land again essentially vertically and without a take-off and landing strip. This global term is used below in the broad sense which includes not only fixed-wing airplanes with bearing surfaces, but also rotorcraft such as helicopters, gyroplanes and rotorcraft and hybrids such as hybrid or combined helicopters as well than convertiplanes. Also included are aircraft with the ability to take off and land on particularly short runways (short take-off and landing, STOL), take off on short runways but land vertically (short take-off and vertical landing, STOVL) or take off vertically but land horizontally (verticaltake-off and horizontal landing, VTHL).
    Document US20160273448A1 discloses a turbine engine with a shrouded fan. The engine includes an oil circuit with an air / oil cooler. In order to increase the capacity of the cooler, the cooler is provided with a device for injecting water. The thermal capacity of the water amplifies the cooling while the suction of the water increases the thrust of the turbine engine.
    Document CN206939095U seems to disclose a similar device.
    The invention provides an aircraft, in particular a fully electric aircraft capable of taking off and landing vertically in the above sense, characterized by the following characteristics:
    • the aircraft comprises electrical components and a fan casing with a cooling coil; and • the aircraft is designed to discharge heat from the electrical components to the cooling coil.
    An advantage of this solution lies in the possibility offered of efficient cooling without aerodynamic losses.
    Other advantageous configurations of the invention are characterized in that:
    • the aircraft comprises a fuselage and a bearing surface;
    • the electrical components are placed in the fuselage and • the fan casing is placed in the bearing surface;
    • electrical components include an inverter and a battery;
    • the aircraft has a fully electric drive;
    • the aircraft includes folded or foldable bearing surfaces;
    • the aircraft includes a rapidly rechargeable battery system;
    • the aircraft includes a horizontal fixed streamlined fan for takeoff and landing;
    • the aircraft has slats; and • horizontal fairing blowers can be selectively covered by the slats;
    • the aircraft comprises a vertical fixed streamlined fan to generate a thrust; and • the aircraft can be controlled entirely independently, as desired. Thus, the aircraft can for example be provided with folded bearing surfaces, or even that can be folded selectively. A corresponding variant increases the effective flight surface in horizontal flight without, however, increasing the surface area of the aircraft.
    [0009] In addition, the aircraft may have a rapidly rechargeable battery system which provides drive energy for vertical start and landing as well as horizontal flight and which enables rapid recharging of the aircraft. on the ground.
    For the training of the aircraft, it is possible in this case to use, instead of automatically guided rotors, several ducted fans also of different sizes, which are known not only in the aerospace technique, but for example in air cushion vehicles or hydrofoils. The cylindrical casing surrounding the propeller makes it possible, in such an embodiment, to considerably reduce the losses of thrust due to swirling at the tips of the blades. Appropriate faired blowers can be oriented horizontally or vertically, can be made so that they can pivot between two positions, or, for aerodynamic reasons in horizontal flight, can be covered by louvers. In addition, it is possible to envisage a purely horizontal thrust generation by means of a fixed faired fan.
    Finally, in addition to preferably fully autonomous operation of the aircraft, it is conceivable to provide manual control by a sufficiently qualified human pilot, which gives the device according to the invention a very great flexibility of maneuver. .
    An embodiment of the invention is illustrated in the drawing and will be explained in more detail below.
    [Fig.l] illustrates a partial cross section of an aircraft according to the invention.
    The single figure illustrates the constructive characteristics of a flying machine 10 capable of taking off and landing vertically, which is provided with a shrouded fan 14 integrated in the bearing surface 15. The need for maximum power and therefore the maximum cooling requirement exists during vertical flight; however, it is in this flight phase by means of convection at the level of the external coating of the flying object 10 that the lowest cooling power is obtained, since the relative speed between the surrounding air and the flying machine 10 is weak. According to the invention, the high air speeds are therefore used in the region of the faired fan 14 active during takeoff and landing by incorporating a cooling structure in the casing structure. The surface can here be made of composite fibers by laminating the cooling structure, in an essentially smooth and therefore aerodynamically optimal form, or with cooling fins to maximize the cooling power. Through the cooling structure flows heat exchange liquid which receives heat from fluid cooled components such as the HV battery 13, the inverter 12 and any electric motors, and which supplies it again to the cooler of the housing.
    In horizontal flight, the liquid is not guided by the fan casing 14 but is guided over a large area by the fuselage 11 or the wings 15 of the flying object 10. As a result, the transfer surface thermal is maximized and the waste heat produced in horizontal flight is released into the atmosphere. The cooling structure used for this purpose can also be incorporated by rolling or be bonded by thermal contact with filling materials or other interface materials on the inner lining of the fuselage 11 or wings 15. During the transition to vertical landing flight, we switch again to the cooling of the casing.
    Cooling adapted to the need without significant increase in air resistance can thus be produced.
    Of course, the invention is not limited to the embodiment described and shown in the accompanying drawing. Modifications remain possible, in particular from the point of view of the constitution of the various elements or by substitution of technical equivalents, without thereby departing from the scope of protection of the invention.
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    claims [Claim 1] Aircraft (10), characterized by the following characteristics:The aircraft (10) comprises electrical components (12, 13) and a fan casing with a cooling coil (14) and• the aircraft (10) is designed to evacuate the heat from the electrical components (12, 13) to the cooling coil. [Claim 2] Aircraft (10) according to claim 1, characterized by the following characteristics:The aircraft (10) comprises a fuselage (11) and a bearing surface (15),The electrical components (12, 13) are arranged in the fuselage (11) and• the fan casing (14) is arranged in the bearing surface (15). [Claim 3] Aircraft (10) according to claim 1 or 2, characterized by the following characteristics:• the electrical components (12, 13) include an inverter(12) and a battery (13). [Claim 4] Aircraft (10) according to any one of claims 1 to 3, characterized by the following characteristic:• the aircraft (10) has a fully electric drive. [Claim 5] Aircraft (10) according to any one of claims 1 to 4, characterized by the following characteristics:The aircraft (10) comprises folded bearing surfaces (15) orcan be folded.
    [Claim 6] Aircraft (10) according to any one of claims 1 to 5, characterized by the following characteristic:• the aircraft (10) comprises a battery system quicklyloadable. [Claim 7] Aircraft (10) according to any one of claims 1 to 6, characterized by the following characteristic:• the aircraft (10) comprises a fixed faired fan ho-horizontal for takeoff and landing. [Claim 8] Aircraft (10) according to claim 7, characterized by the following characteristics:• the aircraft (10) has slats and• the horizontal fairing blowers can be selectively covered by the slats. [Claim 9] Aircraft (10) according to any one of claims 1 to 8, characterized by the following characteristic:• the aircraft (10) comprises a vertical fixed streamlined fanto generate a push. [Claim 10] Aircraft (10) according to any one of claims 1 to 9, characterized by the following characteristic:• the aircraft (10) can be controlled as desired in a mannerfully autonomous.
    1/1
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3083519A1|2020-01-10|Aircraft
    RU2704771C2|2019-10-30|Aircraft capable of vertical take-off
    US9862486B2|2018-01-09|Vertical takeoff and landing aircraft
    EP3294624B1|2021-03-31|Convertible airplane with exposable rotors
    US20140103158A1|2014-04-17|AirShip Endurance VTOL UAV and Solar Turbine Clean Tech Propulsion
    US20040094662A1|2004-05-20|Vertical tale-off landing hovercraft
    FR2864030A1|2005-06-24|Convertiplane, has two tilt fans arranged on both sides of fuselage, another fan arranged between two tail booms, and openings evacuate exhaust gas from two engines on top of fuselage
    FR2864029A1|2005-06-24|Convertiplane, has two tilt fans arranged on both sides of fuselage, fan fixed vertically in fuselage, and two engines disposed at back of passenger compartment of plane for driving fans
    FR3083520A1|2020-01-10|Aircraft
    EP2181036B1|2012-11-07|Aerial device
    CA2908469A1|2014-10-09|System for recovering and converting kinetic energy and potential energy into electrical energy for an aircraft
    FR3030453A1|2016-06-24|REMOVABLE AUXILIARY POWER DEVICE FOR AN AIRCRAFT AND AN AIRCRAFT SUITABLE FOR USE AT LEAST ONE SUCH DEVICE.
    US10669019B2|2020-06-02|Manned and unmanned aircraft
    FR3083518A1|2020-01-10|Aircraft
    FR3039134A1|2017-01-27|AIRCRAFT WITH A PROPULSIVE ASSEMBLY COMPRISING A BLOWER AT THE REAR OF THE FUSELAGE
    FR3083521A1|2020-01-10|Aircraft
    EP2066564A1|2009-06-10|Vertical take-off and landing vehicle which does not have a rotary wing
    FR3004699A1|2014-10-24|AIRCRAFT COMPRISING A HYBRID ENGINE
    FR2532272A1|1984-03-02|FLYING ENGINE WITH RIGID WING
    US3488018A|1970-01-06|Ducted propulsion units for vtol aircraft
    FR3036377A1|2016-11-25|VERTICAL TAKE-OFF AND FIXED FLYING AIRCRAFT DEVICE CAPABLE OF PROVIDING TRANSITION IN HORIZONTAL FLIGHT AND TRACKING IN SPACE WITHOUT GOVERNMENT ASSISTANCE
    FR3083523A1|2020-01-10|Power supply for aircraft and corresponding aircraft
    US20200354054A1|2020-11-12|A vertical take off and landing flying machine
    EP3817978A1|2021-05-12|Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage
    WO2007010682A1|2007-01-25|Rotor with shroud storable into and extendable from outside of bottom plate and aircraft having the rotor with shroud
    同族专利:
    公开号 | 公开日
    CN110683043A|2020-01-14|
    US20200010210A1|2020-01-09|
    DE102018116144A1|2020-01-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB0323993D0|2003-10-14|2003-11-19|Rolls Royce Plc|Engine cooling|
    DE202010016892U1|2010-12-21|2011-08-26|Walter Pahling|Amphibious ultralight aircraft of recent design|
    DE102011105880B4|2011-06-14|2014-05-08|Eads Deutschland Gmbh|Electric drive device for an aircraft|
    EP2774853A1|2013-03-07|2014-09-10|Siemens Aktiengesellschaft|Drive nacelle for an airplane|
    BE1024081B1|2015-03-20|2017-11-13|Safran Aero Boosters S.A.|COOLING TURBOMACHINE BY EVAPORATION|
    DE202015003815U1|2015-05-27|2015-07-22|Maximilian Salbaum|Vertical launching and landing aircraft with electric ducted propellers|
    DE202015007089U1|2015-10-10|2015-11-12|Maximilian Salbaum|Launching and landing vertically blended wing body aircraft with electric ducted propellers|
    CN206939095U|2017-05-26|2018-01-30|深圳光启合众科技有限公司|Cooling system for aircraft engine|
    DE202018000856U1|2018-02-19|2018-03-06|Christian Danz|Protection system for flight systems|DE102020121032A1|2020-08-10|2022-02-10|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Aircraft and its manufacture|
    DE102020127041B3|2020-10-14|2021-09-16|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Aircraft ducted propellers and aircraft|
    DE102020127029B3|2020-10-14|2021-09-30|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Aircraft ducted propellers and aircraft|
    DE102020133449B3|2020-12-15|2021-12-30|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Ducted propeller of an aircraft, aircraft and component thereof|
    法律状态:
    2020-07-22| PLFP| Fee payment|Year of fee payment: 2 |
    2021-07-28| PLFP| Fee payment|Year of fee payment: 3 |
    2021-11-05| PLSC| Publication of the preliminary search report|Effective date: 20211105 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018116144.1|2018-07-04|
    DE102018116144.1A|DE102018116144A1|2018-07-04|2018-07-04|aircraft|
    [返回顶部]