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    • 1. 发明申请
    • AIRCRAFT HYBRID PROPULSION
    • 飞机混合推进
    • WO2010020199A1
    • 2010-02-25
    • PCT/CZ2009/000102
    • 2009-08-19
    • VYCITAL, JiriMORAVEC, Tomas
    • VYCITAL, JiriMORAVEC, Tomas
    • B64D27/08B64D27/14B64D27/24
    • B64D27/08B64D27/24B64D2027/026Y02T50/64
    • The invention relates to the aircraft hybrid propulsion, consisting of two propeller propulsion units, one of which is based on the principle of an internal combustion engine (1). with a propeller and the second one on the principle of an electric motor (2) with a propeller characterized in that the propulsion units are installed without an interdependent mechanical coupling in the push-pull configuration in the direction of flight on the aircraft fuselage, so that one of the propulsion units (1, 2) is located in the forward fuselage and generates a propulsion effect using a tractor propeller and the second one of the propulsion units (1, 2) is located in the rear fuselage and generates a propulsion effect using a pusher propeller and the batteries supplying the energy to the electric motor are rechargeable by recuperation during flight. From the electric motor with a propeller (2) and/or from a generator installed on the internal combustion engine (1).
    • 本发明涉及由两个螺旋桨推进装置组成的飞机混合动力推进装置,其中之一是基于内燃机(1)的原理。 具有推进器,第二个是具有螺旋桨的电动机(2)的原理,其特征在于,推进装置在飞行器机身上的飞行方向上的推拉构造中没有相互依赖的机械联接而安装,因此 推进单元(1,2)中的一个位于前机身中并且使用拖拉机螺旋桨产生推进效果,并且第二推进单元(1,2)位于后机身中并且产生推进效应 使用推动螺旋桨,并且向电动机供应能量的电池可以通过在飞行期间的恢复来充电。 从具有螺旋桨(2)的电动机和/或来自安装在内燃机(1)上的发电机。