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1. 发明授权

US08820673B2 Rotary-wing and fixed-wing aircraft 有权
标题翻译：旋翼和固定翼飞机
公开(公告)号：US08820673B2
公开(公告)日：2014-09-02
申请号：US13526899
申请日：2012-06-19
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C27/22 , B64C39/06 , B64C27/26
CPC分类号： B64C27/26 , B64C39/062
摘要： An aircraft (1) having a fuselage (2), the aircraft (1) comprising a rotary wing (9) above the fuselage (2) and an extra fixed wing (10), the rotary wing (9) being above both the fuselage (2) and the fixed wing (10), said fixed wing (10) comprising at least one closed wing (20) comprising a first half-wing (21) and a second half-wing (22). Each half-wing (21, 22) is provided with a top lift portion (30) and a bottom lift portion (40), said bottom lift portion (40) of a half-wing being arranged in the wake (S) of the top lift portion (30) of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing (9) and impacting against the top face (30′) of the top lift portion (30) when said aircraft (1) has a forward speed less than a predetermined threshold.
摘要翻译：具有机身（2）的飞机（1），飞行器（1）包括在机身（2）上方的旋转翼（9）和额外的固定翼（10），旋转翼（9）在机身上方（2）和所述固定翼（10），所述固定翼（10）包括至少一个包括第一半翼（21）和第二半翼（22）的封闭翼（20）。每个半翼（21,22）设置有顶部提升部分（30）和底部提升部分（40），所述半部翼的所述底部提升部分（40）布置在所述尾部的尾部（S）中所述半翼的顶部提升部分（30），所述尾部（S）由来自所述旋转翼（9）的空气流（F）产生并且撞击所述顶部提升部分的顶面（30'）（30）当所述飞行器（1）具有小于预定阈值的前进速度时。

2. 发明申请

US20090101756A1 MONOLITHIC SELF-STIFFENED PANELS 有权
标题翻译：单一自强度面板
公开(公告)号：US20090101756A1
公开(公告)日：2009-04-23
申请号：US11996302
申请日：2006-07-12
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C1/12
CPC分类号： B64C25/16 , B64C1/12 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).
摘要翻译：一种复合面板，其具有形成面板外壁的第一皮肤，称为下表面（1），以及形成面板内壁部分的第二皮肤。第二皮肤形成为中空的，以产生半框结构（3）形式的内部加强框架（2），其与第一皮肤一起形成箱体部件。上述框架配备有用于固定到第一皮肤的边缘（4a，4b），称为上表面（5）的表面和连接侧壁（6,6a，6b，6c，6d，6e，7）之间的边缘边缘（4a，4b）和上表面（5），第一和第二表皮形成一体的自加强板。半框框架（2）具有由形成半框框架（2）的中空梁部分限定的穿孔部分（8）。

3. 发明授权

US10150553B2 Device and method for assembling two sections of aircraft fuselage 有权
公开(公告)号：US10150553B2
公开(公告)日：2018-12-11
申请号：US13533266
申请日：2012-06-26
申请人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Hélène Cazeneuve , Marc-Antoine Castanet
发明人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Hélène Cazeneuve , Marc-Antoine Castanet
IPC分类号： B64C1/06 , B64F5/10 , B64C1/00
摘要： A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

4. 发明申请

US20130181092A1 DEVICE AND METHOD FOR ASSEMBLING TWO SECTIONS OF AIRCRAFT FUSELAGE 审中-公开
标题翻译：用于组装飞机熔接两段的装置和方法
公开(公告)号：US20130181092A1
公开(公告)日：2013-07-18
申请号：US13533266
申请日：2012-06-26
申请人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Helene Cazeneuve , Marc-Antoine Castanet
发明人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Helene Cazeneuve , Marc-Antoine Castanet
IPC分类号： B64C1/06 , B64F5/00
CPC分类号： B64C1/069 , B64C1/068 , B64C2001/0081 , B64F5/10 , Y10T29/49622
摘要： Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.Set of fuselage sections assembled by means of a device of the type described above.Method of assembling two fuselage sections by means of a device of the type described above.
摘要翻译：用于组装两个飞行器机身部分的装置，每个飞行器机身部分各自包括皮肤和纵向加强件，该装置包括分别属于所述部分的相互对齐的纵向加强件的鱼板钓鱼钩，每个鱼板包括两个鱼板块，每个鱼板包括至少一个用于固定的纵向底板纵向加强件和横向支撑头以及能够相互夹紧所述鱼板片的相应支撑头的至少一个可拆卸连接件，以允许在这些鱼片之间传递纵向力。通过上述类型的装置组装的机身部分组。通过上述类型的装置组装两个机身部分的方法。

5. 发明授权

US08302909B2 Splicing of omega-shaped stiffeners at a circumferential joint in an aircraft fuselage 有权
标题翻译：在飞机机身的圆周接头处接合Ω形加强件
公开(公告)号：US08302909B2
公开(公告)日：2012-11-06
申请号：US12738594
申请日：2008-10-15
申请人： Helene Cazeneuve , Bruno Cacciaguerra
发明人： Helene Cazeneuve , Bruno Cacciaguerra
IPC分类号： B64C1/00
CPC分类号： B64C1/06 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.
摘要翻译：通过在周向接头处组装至少两个部分，每个部分包括涂层和至少一个加强件的至少一个元件而制造的飞行器机身，上述两个元件具有闭合的横截面并且由拼接件组装。加强件和拼接件的元件由复合材料制成。具有两个凸缘的上述拼接片通过仅位于上述拼接件的凸缘上的工作紧固件固定到涂层和加强件上。

6. 发明申请

US20130175383A1 ROTARY-WING AND FIXED-WING AIRCRAFT 有权
标题翻译：旋转和固定式飞机
公开(公告)号：US20130175383A1
公开(公告)日：2013-07-11
申请号：US13526899
申请日：2012-06-19
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C27/26
CPC分类号： B64C27/26 , B64C39/062
摘要： An aircraft (1) having a fuselage (2), the aircraft (1) comprising a rotary wing (9) above the fuselage (2) and an extra fixed wing (10), the rotary wing (9) being above both the fuselage (2) and the fixed wing (10), said fixed wing (10) comprising at least one closed wing (20) comprising a first half-wing (21) and a second half-wing (22). Each half-wing (21, 22) is provided with a top lift portion (30) and a bottom lift portion (40), said bottom lift portion (40) of a half-wing being arranged in the wake (S) of the top lift portion (30) of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing (9) and impacting against the top face (30′) of the top lift portion (30) when said aircraft (1) has a forward speed less than a predetermined threshold.
摘要翻译：具有机身（2）的飞机（1），飞行器（1）包括在机身（2）上方的旋转翼（9）和额外的固定翼（10），旋转翼（9）在机身上方（2）和所述固定翼（10），所述固定翼（10）包括至少一个包括第一半翼（21）和第二半翼（22）的封闭翼（20）。每个半翼（21,22）设置有顶部提升部分（30）和底部提升部分（40），所述半部翼的所述底部提升部分（40）布置在所述尾部的尾部（S）中所述半翼的顶部提升部分（30），所述尾部（S）由来自所述旋转翼（9）的空气流（F）产生并且撞击所述顶部提升部分的顶面（30'）（30）当所述飞行器（1）具有小于预定阈值的前进速度时。

7. 发明申请

US20120080558A1 UNDERCARRIAGE, AN AIRCRAFT INCLUDING SAID UNDERCARRIAGE, AND A METHOD OF LANDING SAID AIRCRAFT 有权
标题翻译：航空公司，航空公司，包括所谓的航空公司，以及登陆飞机的方法
公开(公告)号：US20120080558A1
公开(公告)日：2012-04-05
申请号：US13240817
申请日：2011-09-22
申请人： André Barbieri , Bruno Cacciaguerra
发明人： André Barbieri , Bruno Cacciaguerra
IPC分类号： B64C25/18
CPC分类号： B64C25/00 , B64C25/14 , B64C2025/125 , B64C2025/325
摘要： An undercarriage (6) provided with an undercarriage leg (10) and a shock absorber (20), said undercarriage (6) including an actuator-shock absorber (30), said undercarriage leg (10) comprising both a first element (11) carrying contact means (13) and a second element (12), which elements are hinged to each other. The undercarriage (6) includes pivot means (40) enabling said undercarriage leg (10) to pivot firstly in a first direction (S1) in order to retract said undercarriage leg (10) into said housing (4) under drive from said actuator-shock absorber (30), and secondly, during an emergency landing, in a second direction (S2) opposite to the first direction (S1) in order to move said undercarriage leg (10) away from said housing (4) while stressing said actuator-shock absorber (30).
摘要翻译：一种具有起落架脚架（10）和减震器（20）的起落架（6），所述起落架（6）包括致动器减振器（30），所述起落架腿部（10）包括第一元件（11）承载接触装置（13）和第二元件（12），所述元件彼此铰接。起落架（6）包括枢转装置（40），其使得所述起落架腿（10）首先在第一方向（S1）枢转，以便在所述致动器（10）的驱动下将所述起落架腿（10）缩回到所述壳体（4）减震器（30），其次，在紧急着陆期间，在与所述第一方向（S1）相反的第二方向（S2）上移动所述起落架腿（10）以远离所述壳体（4），同时将所述致动器 - 减震器（30）。

8. 发明申请

US20080093503A1 STRUCTURAL FRAME FOR AN AIRCRAFT FUSELAGE 有权
标题翻译：用于飞机熔接的结构框架
公开(公告)号：US20080093503A1
公开(公告)日：2008-04-24
申请号：US11718845
申请日：2005-11-07
申请人： Bruno CACCIAGUERRA
发明人： Bruno CACCIAGUERRA
IPC分类号： B64C1/06
CPC分类号： B64C1/18 , B64C1/061 , B64C1/062 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A structural frame for a fuselage including a lower arched structure (1), a cross-piece (2), supporting a floor element (3) and a connecting lattice (4) between the lower arch (1) and the cross-piece (2), the connecting lattice (4) more particularly may comprise bars (4a, 4b) the ends of which are spliced to the cross-piece (2) and the lower arch (1).
摘要翻译：一种用于机身的结构框架，包括下弓形结构（1），横梁（2），支撑地板元件（3）和下弓（1）与横梁（1）之间的连接格（4）更具体地说，连接格子（4）可以包括杆（4a，4b），其端部被接合到横梁（2）和下弓（1）。

9. 发明申请

US20080073931A1 WINDSCREEN FRAME AND A METHOD OF PRODUCTION FOR A WINDSCREEN FRAME 有权
标题翻译： WINISCREEN框架和一种生产框架的方法
公开(公告)号：US20080073931A1
公开(公告)日：2008-03-27
申请号：US11854677
申请日：2007-09-13
申请人： Benjamin Mahieu , Bruno Cacciaguerra , Louis Peltier
发明人： Benjamin Mahieu , Bruno Cacciaguerra , Louis Peltier
IPC分类号： B60J1/00
CPC分类号： B64C1/1476 , Y02T50/43
摘要： A windscreen frame, and a method of production for a windscreen frame, designed to hold a windscreen in an opening in a wall, the frame including at least one upper horizontal frame section element, at least one lower horizontal frame section element and at least one vertical mounting, characterised in that it is a single unit in composite material.
摘要翻译：一种挡风玻璃框架和用于挡风玻璃框架的生产方法，其被设计成将挡风玻璃保持在壁的开口中，所述框架包括至少一个上部水平框架部分元件，至少一个下部水平框架部分元件和至少一个垂直安装，其特征在于它是复合材料中的单个单元。

10. 发明授权

US09033275B2 Aircraft undercarriage 有权
标题翻译：飞机起落架
公开(公告)号：US09033275B2
公开(公告)日：2015-05-19
申请号：US13240817
申请日：2011-09-22
申请人： André Barbieri , Bruno Cacciaguerra
发明人： André Barbieri , Bruno Cacciaguerra
IPC分类号： B64C25/18 , B64C25/00 , B64C25/14 , B64C25/12 , B64C25/32
CPC分类号： B64C25/00 , B64C25/14 , B64C2025/125 , B64C2025/325
摘要： An undercarriage (6) provided with an undercarriage leg (10) and a shock absorber (20), said undercarriage (6) including an actuator-shock absorber (30), said undercarriage leg (10) comprising both a first element (11) carrying contact means (13) and a second element (12), which elements are hinged to each other. The undercarriage (6) includes pivot means (40) enabling said undercarriage leg (10) to pivot firstly in a first direction (S1) in order to retract said undercarriage leg (10) into said housing (4) under drive from said actuator-shock absorber (30), and secondly, during an emergency landing, in a second direction (S2) opposite to the first direction (S1) in order to move said undercarriage leg (10) away from said housing (4) while stressing said actuator-shock absorber (30).
摘要翻译：一种具有起落架脚架（10）和减震器（20）的起落架（6），所述起落架（6）包括致动器减振器（30），所述起落架腿部（10）包括第一元件（11）承载接触装置（13）和第二元件（12），所述元件彼此铰接。起落架（6）包括枢转装置（40），其使得所述起落架腿（10）首先在第一方向（S1）枢转，以便在所述致动器（10）的驱动下将所述起落架腿（10）缩回到所述壳体（4）减震器（30），其次，在紧急着陆期间，在与所述第一方向（S1）相反的第二方向（S2）上移动所述起落架腿（10）以远离所述壳体（4），同时将所述致动器 - 减震器（30）。

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