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1. 发明授权

EP3305653B1 AIRFRAME FOR CERTIFIED ULTRALIGHT AND / OR LIGHT AIRCRAFT 有权
公开(公告)号：EP3305653B1
公开(公告)日：2020-04-01
申请号：EP17194817.7
申请日：2017-10-04
申请人： C.A.I. Confident Aircraft Industry S.R.L.
发明人： LICCARDO, Giuseppe , LICCARDO, Domenico , LICCARDO, Rosario
IPC分类号： B64C1/08 , B64C1/26 , B64C13/06 , B64C13/14 , B64D45/00

2. 发明公开

EP3778385A1 HYBRID ENGINE SYSTEM FOR LIGHT AIRCRAFT 有权
公开(公告)号：EP3778385A1
公开(公告)日：2021-02-17
申请号：EP19191892.9
申请日：2019-08-15
申请人： C.A.I. Confident Aircraft Industry S.R.L.
发明人： LICCARDO, Domenico , LICCARDO, Giuseppe , LICCARDO, Rosario
IPC分类号： B64C11/48 , F02K3/072 , B63H5/10
摘要： The present invention relates to a system comprising at least two counter-rotating propellers independent one another, in which the main propeller is actuated by a thermal primary engine and the secondary propeller is actuated by a secondary electric motor parallel with respect to said first thermal primary engine, in which the system also includes a traction belt able to transmit the motion to said secondary propeller.
In this way it is possible to exploit in many ways the fact that the two propellers are placed in order to be actuated by two different engines.
In fact, it is possible to improve the efficiency in phase of take-off, landing or for return operations or with full power, so as to have a safety increase by counting on the thrust of the secondary electric motor, which can also be used as current generator for recharging the auxiliary batteries.
Furthermore, the traction belt is very light with respect to the gear transmissions, and is able to transmit very high power with the advantage of being silent without requiring lubrication.

3. 发明公开

EP3305653A1 AIRFRAME FOR CERTIFIED ULTRALIGHT AND / OR LIGHT AIRCRAFT 有权
标题翻译：用于认证超轻型和/或轻型飞机的机身
公开(公告)号：EP3305653A1
公开(公告)日：2018-04-11
申请号：EP17194817.7
申请日：2017-10-04
申请人： C.A.I. Confident Aircraft Industry S.R.L.
发明人： LICCARDO, Giuseppe , LICCARDO, Domenico , LICCARDO, Rosario
IPC分类号： B64C1/08 , B64C1/26 , B64C13/06 , B64C13/14 , B64D45/00
摘要： The airframe for certified ultralight and/or light aircraft comprises a fuselage (1) having a metal truss structure, wings (2) having a structure with ribs (2.1) and spars (2.2) and a cockpit (3).
The airframe is characterized in that the interior space of the cockpit (3) has a truss structure defined by:
- a central compartment (3.1) for housing at least two seats (4) in side-by-side relationship, that cannot be displaced along the longitudinal axis A-A of the aircraft,
- a rear compartment (3.2) having a fixed size and located behind said seats (4),
- a front compartment (3.3) for housing adjustable rudder pedals (6).
Two appendages (1.1) extend laterally from the fuselage (1) along the transverse axis B-B of the aircraft, and can be connected with the wing couplings (2.3) of the wings (2) thereby forming a single structure with the fuselage.
The rear compartment (3.2) of the cockpit (3) having a fixed size, located behind said seats (4) and delimited by longitudinal beams and vertical and transverse rods, intersecting at nodes, forms a service compartment for housing the batteries pack (5) for powering the auxiliary electric motor of a certified hybrid electric-thermal propulsion ultralight and/or light aircraft.
摘要翻译：用于认证的超轻型和/或轻型飞机的机身包括具有金属桁架结构的机身（1），具有肋（2.1）和翼梁（2.2）和驾驶舱（3）的结构的机翼（2）。该机身的特征在于，驾驶舱（3）的内部空间具有由以下限定的桁架结构： - 用于容纳至少两个并排关系的座椅（4）的中央隔室（3.1），其不能移动沿着飞行器的纵向轴线AA， - 具有固定尺寸并位于所述座椅（4）后面的后部舱室（3.2）， - 用于容纳可调节方向舵踏板（6）的前部舱室（3.3）。两个附件（1.1）从机身（1）沿着飞机的横向轴线B-B横向延伸，并且可以与机翼（2）的机翼联接器（2.3）连接，从而与机身形成单一结构。驾驶舱（3）的后舱（3.2）具有固定的尺寸，位于所述座椅（4）的后面并且由纵梁和垂直和横向杆限定，在节点处相交，形成用于容纳电池组（5 ）用于为经认证的混合动力电动推进超轻型和/或轻型飞机的辅助电动机提供动力。

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