• 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 comprising a body (1) of the aircraft, an upper propeller (2) mounted on top of the body (1) of the aircraft and three rotors; a tail or main rotor (5) and two side rotors (4) mounted on the ends of supports (6) where the lateral rotors (4) and the tail rotor (5) rotate about a horizontal axis, even to get to stand upright. The wings (3) can be retractable or foldable, which will be folded or collected according to the flight conditions or the like, the upper propeller (2) can have a system of inclination thereof in order to avoid excessive rotation and propulsion of the aircraft can be by a combustión engine or by a hybrid engine equipped with a clutch. Electric motors being powered by batteries or similar rechargeable by the rotation of the propellers or by other means. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2604711A1
    申请号:ES201730123
    申请日:2017-02-02
    公开日:2017-03-08
    发明作者:Alberto ADARVE LOZANO
    申请人:Defensya Ingenieria Internacional SL；
    IPC主号:
    专利说明:

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    achieve the starting torque of the upper propeller. The rotors can be driven either by combustion or electric motors. Electric motors are powered from batteries, rechargeable by the rotation of the propellers or other means such as a ground charger.
    5
    An aircraft like the one described can have a GPS navigation system, a centralized control system, a noise reduction system, ground steering servo control, possibility of 3 and up to six passengers, retractable landing mechanism, can have a maximum load of
    10 600 Kg, reach a speed above 250 km / h and an autonomy of at least 500 km.
    Describing sufficiently the nature of the present invention, as well as the way of putting it into practice, it is stated that, within its essentiality,
    15 may be put into practice in other embodiments that differ in detail from that indicated by way of example, and which will also achieve the protection sought, provided it does not alter, change or modify its fundamental principle.
    8
    权利要求:
    Claims (1)
    [1]
    image 1
    类似技术:
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    同族专利:
    公开号 | 公开日
    ES2604711B1|2017-12-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3241791A|1964-04-03|1966-03-22|Frank N Piasecki|Compound helicopter with shrouded tail propeller|
    US20050045762A1|2003-01-09|2005-03-03|Pham Roger N.|High performance VTOL convertiplanes|
    US20050133662A1|2003-12-23|2005-06-23|Eric Magre|Convertible aircraft provided with two tilt fans on either side of the fuselage and with a third tilt fan arranged on the tail of the aircraft|
    WO2007014531A1|2005-08-02|2007-02-08|Peizhou Han|A vtol aircraft with tilt front rotors|
    US20080184906A1|2007-02-07|2008-08-07|Kejha Joseph B|Long range hybrid electric airplane|
    WO2013105094A1|2012-01-12|2013-07-18|Israel Aerospace Industries Ltd.|System, method and computer program product for maneuvering of an air vehicle with tiltable propulsion unit|
    EP2690012A1|2012-07-27|2014-01-29|Eurocopter Deutschland GmbH|Semi-convertible rotorcraft|
    WO2014206058A1|2013-06-28|2014-12-31|Li Hongsheng|Helicopter with forward tilting main airscrew|CN108516083A|2018-03-27|2018-09-11|西北工业大学|Double disengaging type stoppable rotor aircraft drive systems and change operating mode method|
    EP3656668A3|2018-11-26|2020-07-29|Bell Textron Inc.|Tilting duct compound helicopter|
    法律状态:
    2017-12-18| FG2A| Definitive protection|Ref document number: 2604711 Country of ref document: ES Kind code of ref document: B1 Effective date: 20171218 |
    2021-09-28| FD2A| Announcement of lapse in spain|Effective date: 20210928 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201730123A|ES2604711B1|2017-02-02|2017-02-02|AIRCRAFT|ES201730123A| ES2604711B1|2017-02-02|2017-02-02|AIRCRAFT|
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