• 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 present invention provides an aircraft (10) with the following characteristics: the aircraft (10) comprises a fuselage and propellers (11); and the propellers (11) can be folded down below the fuselage. Figure to be published with the abstract: Fig. 1
    公开号:FR3083520A1
    申请号:FR1907241
    申请日:2019-07-01
    公开日:2020-01-10
    发明作者:Stefan Bender；Mikel Fauri
    申请人:Dr Ing HCF Porsche AG；
    IPC主号:
    专利说明:

    Description
    Title of the invention: Aircraft The present invention relates to an aircraft, in particular a fully electric aircraft capable of taking off and landing vertically ('vertical take-off and landing [0002] The term VTOL designates in aerospace and aeronautical technique any type of aircraft, drone or rocket with the ability to take off and land again essentially vertically and without a take-off and landing runway. This generic term will be used subsequently in the broad sense including not only rigid wing airplanes with airfoils but also rotorcraft such as helicopters, gyroplanes, gyrodines, and hybrids such as composite or combined helicopters as well as convertible airplanes. '' land on particularly short runways ('short takeoff and landing, STOL), take off on short runways but d land vertically ( 'short take-off and vertical landing, STOVL) or take off vertically but horizontally land (vertical take-off and landing horizontal, Vthl).
    Document W02016200502A2 discloses an aircraft provided with a crew and suitable for takeoff and vertical landing which uses the same reactors for takeoff and landing as for the front flight and which has removable wing sections allowing a new configuration with different types of wing section, allowing configurations adapted to a specific flight profile.
    Document DE102012104783A1 proposes a flying machine comprising a rigid bearing wing allowing aerodynamic horizontal flight. In addition, at least four rotors are provided, driven by adjustable electric motors which can be pivoted using a pivoting mechanism between the horizontal take-off position and the horizontal flight position. In this case, all the electric motors and the rotors are arranged at the level of the rigid bearing wing.
    The invention provides an aircraft, fully electric, capable of taking off and landing vertically in the direction indicated above.
    According to the invention, the aircraft is characterized by the following characteristics:
    • the aircraft includes a fuselage and propellers; and • the propellers can be folded down below the fuselage;
    • the propellers have an axis of rotation parallel to a yaw axis of the aircraft;
    • the propellers are arranged at the nose of the aircraft;
    • the aircraft has a fully electric drive;
    • the aircraft includes bent or bendable bearing surfaces;
    • the aircraft includes a rapidly rechargeable battery system;
    • the aircraft includes horizontally stationary blowers for take-off and landing;
    • the aircraft has slats; and • the horizontal blowers can optionally be covered by the slats;
    • the aircraft includes vertically stationary blowers to produce forward propulsion; and • the aircraft may optionally be controlled entirely independently.
    An advantage of this solution is that the propeller components are only placed in the wind when it is actually necessary. Another advantage is the reduced surface area of the aircraft when the propellers are folded down.
    Other advantageous configurations of the invention are set out below. The aircraft can thus be provided with, for example, bent or even bearing surfaces which can be optionally bent. A corresponding variant enlarges the active wing surface in horizontal flight without, however, extending the surface area of the aircraft.
    The aircraft may also have a rapidly rechargeable battery system providing drive energy for vertical takeoff and landing as well as for horizontal flight and allowing rapid charging of the aircraft to judgment.
    Instead of free-motion rotors, one can use here to drive the aircraft several blowers (ducted fans) also of different sizes, as they are known outside the field of aeronautical technique, for example in air cushion vehicles or hydrofoils. The cylindrical casing surrounding the propeller makes it possible to considerably reduce, in such an embodiment, the losses of thrust due to swirls at the ends of the blades. Suitable blowers can be oriented horizontally or vertically, can be made between the two positions or be covered by strips (louvers) in horizontal flight for aerodynamic reasons. One can also consider a purely horizontal thrust production using fixed blowers.
    Finally, it is envisaged - in addition to preferably entirely autonomous operation of the aircraft - also to entrust manual control to the human pilot in the event of sufficient qualification, which gives the device according to the invention maximum flexibility in the handling of the machine.
    An exemplary embodiment of the invention is illustrated in the drawing and will be described in more detail below.
    [Fig.l] illustrates the perspective view of an aircraft.
    The single figure illustrates the construction features of a preferred embodiment of the aircraft 10 according to the invention. As a characteristic of the invention, the aircraft 10 comprises, at its nose, propellers 11 provided on both sides, in particular deployed on the side for takeoff and landing and which can be folded down under the hull of the aircraft 10 to save place it in the parking position and in operating condition in the upper airspace.
    It will be understood that even if the drawing has an axis of rotation of the propellers 11 essentially parallel to the yaw axis Z of the aircraft 10, the basic idea described can be adapted to the propeller arrangements the as diverse as possible without departing from the scope of the present invention.
    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 a fuselage and propellers (11); and• the propellers (11) can be folded down below the fuselage. [Claim 2] Aircraft (10) according to claim 1, characterized by the following characteristic:• the propellers (11) have an axis of rotation parallel to an axisaircraft yaw (10). [Claim 3] Aircraft (10) according to claim 1 or 2, characterized by the following characteristic:• the propellers (11) are arranged at the nose of the aircraft(10). [Claim 4] Aircraft (10) according to any one of claims 1 to 3, characterized by the following characteristic:• the aircraft (10) has a drive entirelyelectric. [Claim 5] Aircraft (10) according to any one of claims 1 to 4, characterized by the following characteristic:• the aircraft (10) comprises angled bearing surfaces orcan be bent. [Claim 6] Aircraft (10) according to any one of claims 1 to 5, characterized by the following characteristic:• the aircraft (10) includes 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 horizontally stationary blowers
    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 blowers can optionally be covered by slats. [Claim 9] Aircraft (10) according to any one of claims 1 to 8, characterized by the following characteristic:• the aircraft (10) includes vertically stationary blowersto produce forward propulsion. [Claim 10] Aircraft (10) according to any one of claims 1 to 9, characterized by the following characteristic:• the aircraft (10) can optionally be controlled sofully autonomous.
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    类似技术:
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    FR2532272A1|1984-03-02|FLYING ENGINE WITH RIGID WING
    US3488018A|1970-01-06|Ducted propulsion units for vtol aircraft
    EP3154856B1|2017-11-08|Aircraft with polygonal wings
    FR2619786A1|1989-03-03|SUPPORT ARRANGEMENT BY DIRECT ACTION OF THE ENGINE FLOW FOR VERTICAL TAKE OFF 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
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    FR2521521A1|1983-08-19|Vertical take=off aeroplane - has three engines, two of which can pivot between vertical and horizontal flight positions
    同族专利:
    公开号 | 公开日
    DE102018116147A1|2020-01-09|
    GB2576251B|2020-08-26|
    GB201909484D0|2019-08-14|
    US20200010186A1|2020-01-09|
    CN110683044A|2020-01-14|
    RU2724006C1|2020-06-18|
    GB2576251A|2020-02-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE3917499A1|1989-05-30|1990-12-06|Herbert Zemann|Vertical take-off aircraft - has front and rear propellers which can be swung through 90 deg.NoAbstract|
    GB2409845A|2004-01-08|2005-07-13|Robert Graham Burrage|Tilt-rotor aircraft changeable between vertical lift and forward flight modes|
    RU98394U1|2010-07-14|2010-10-20|Федеральное государственное учреждение "46 Центральный научно-исследовательский институт Министерства обороны Российской Федерации"|COMBINED UNMANNED AIRCRAFT|
    DE102012104783B4|2012-06-01|2019-12-24|Quantum-Systems Gmbh|Aircraft, preferably UAV, drone and / or UAS|
    ES2524383B1|2013-06-04|2015-09-11|Miguel Ángel ÁLVAREZ ALARIO|Aerial platform with radio frequency control|
    US9457901B2|2014-04-22|2016-10-04|Fatdoor, Inc.|Quadcopter with a printable payload extension system and method|
    US10377482B2|2015-05-01|2019-08-13|Transition Robotics, Inc.|Remotely controlled modular VTOL aircraft and re-configurable system using same|
    CN106428547A|2015-08-12|2017-02-22|刘十|Perpendicular take-off and landing fixed-wing aircraft with multiple automatic retractable rotors|
    CN105035303A|2015-08-19|2015-11-11|无锡觅睿恪科技有限公司|Folding type aerial photography aircraft|
    CN205345315U|2016-01-14|2016-06-29|骅星科技发展有限公司|Novel folding unmanned aerial vehicle|
    RU2627965C1|2016-06-28|2017-08-14|Дмитрий Сергеевич Дуров|High-speed amphibious rotorcraft|
    CN206358357U|2016-12-30|2017-07-28|深圳市大疆创新科技有限公司|Multi-rotor aerocraft|
    CN107021206B|2017-04-11|2020-06-19|深圳智航无人机有限公司|Unmanned plane|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 |
    2022-02-04| PLSC| Publication of the preliminary search report|Effective date: 20220204 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018116147.6|2018-07-04|
    DE102018116147.6A|DE102018116147A1|2018-07-04|2018-07-04|aircraft|
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