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1. 发明申请

US20230002290A1 METHOD FOR MAKING A PASSIVATING COATING BASED ON ONE OR MORE SILICON COMPOUNDS ON A CERAMIC MATRIX COMPOSITE REINFORCED WITH CARBON FIBRES AND CERAMIC MATRIX COMPOSITE REINFORCED WITH CARBON FIBRES WITH SUCH COATING 有权
公开(公告)号：US20230002290A1
公开(公告)日：2023-01-05
申请号：US17642904
申请日：2020-09-16
申请人： PETROCERAMICS S.P.A. , C.I.R.A. (CENTRO ITALIANO RICERCHE AEROSPAZIALI) S.C.P.A.
发明人： Lorenzo CAVALLI , Massimiliano VALLE , Mario DE STEFANO FUMO , Giuseppe Carmine RUFOLO , Roberto GARDI , Stefania CANTONI , Massimo ROSA
IPC分类号： C04B41/87 , C04B35/83 , C04B41/45 , C04B41/50
摘要： A method makes a silicon compound-based passivating coating on a ceramic matrix composite reinforced with carbon fibers. A piece made in a ceramic matrix composite reinforced with carbon fibers is placed in a closed chamber of an oven. A predefined load of solid silicon is placed in the chamber avoiding direct contact between the silicon and the piece. The oven is heated while maintaining inside the chamber predefined medium/low vacuum conditions, to generate silicon vapors inside the chamber. The vapors react with substances on the surface of the piece to form a surface coating having composites of the substances with the silicon. The partial pressure of the vacuum, temperature inside the chamber and exposure times of the piece to the silicon vapors to obtain a predefined thickness of the surface coating are chosen. The piece is cooled once the predefined thickness of the passivating coating is reached.

2. 发明授权

US09983023B2 System and method for angle of attack indication with no dedicated sensors and aircraft information 有权
公开(公告)号：US09983023B2
公开(公告)日：2018-05-29
申请号：US15093369
申请日：2016-04-07
申请人： Aspen Avionics, Inc. , Centro Italiano Ricerche Aerospaziali S.c.p.A.
发明人： Nicola Genito , Federico Corraro , Luca Garbarino , Antonio Vitale , Ettore De Lellis , David Bibby , Sean Rieb , Kevin Glen Jones
IPC分类号： G01C23/00 , G06F9/445 , B64D43/02
CPC分类号： G01C23/00 , B64D43/02 , G06F8/61
摘要： A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

3. 发明申请

US20160298985A1 SYSTEM AND METHOD FOR ANGLE OF ATTACK INDICATION WITH NO DEDICATED SENSORS AND AIRCRAFT INFORMATION 有权
标题翻译：没有专用传感器和飞机信息的攻击指示的系统和方法
公开(公告)号：US20160298985A1
公开(公告)日：2016-10-13
申请号：US15093369
申请日：2016-04-07
申请人： Aspen Avionics, Inc. , Centro Italiano Ricerche Aerospaziali S.c.p.A.
发明人： NICOLA GENITO , FEDERICO CORRARO , LUCA GARBARINO , ANTONIO VITALE , ETTORE DE LELLIS , DAVID BIBBY , SEAN RIEB , KEVIN GLEN JONES
IPC分类号： G01C23/00 , G06F9/445 , B64D45/00
CPC分类号： G01C23/00 , B64D43/02 , G06F8/61
摘要： A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.
摘要翻译：提供了一种指示飞机的迎角的系统和方法。该系统利用现有飞行器传感器的测量结果，不需要专用的攻角传感器。该系统通过独特的方法实现并获益，包括在校准飞行期间执行标准飞行操作。该系统不需要飞机的任何空气动力学模型，因为它利用来自校准飞行的信息来开发特定飞机的估计空气动力学模型。该系统利用空气动力学模型和其他信息来估计飞行中飞机的迎角。最后，该系统利用附加信息来指示飞机相对于飞机的最佳迎角和/或飞机的临界迎角的估计迎角。该系统还能够重新校准，以适应飞机的空气动力学修改。

4. 发明申请

WO2016164624A1 SYSTEM AND METHOD FOR ANGLE OF ATTACK INDICATION WITH NO DEDICATED SENSORS AND AIRCRAFT INFORMATION 审中-公开
标题翻译：没有专用传感器和飞机信息的攻击指示的系统和方法
公开(公告)号：WO2016164624A1
公开(公告)日：2016-10-13
申请号：PCT/US2016/026503
申请日：2016-04-07
申请人： ASPEN AVIONICS, INC. , CENTRO ITALIANO RICERCHE AEROSPAZIALI S.C.P.A.
发明人： GENITO, Nicola , CORRARO, Federico , GARBARINO, Luca , VITALE, Antonio , DE LELLIS, Ettore , BIBBY, David , RIEB, Sean , JONES, Kevin
IPC分类号： B64D43/00 , B64D43/02 , B64D45/00 , B64C13/02
CPC分类号： G01C23/00 , B64D43/02 , G06F8/61
摘要： A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.
摘要翻译：提供了一种指示飞机的迎角的系统和方法。该系统利用现有飞行器传感器的测量结果，不需要专用的攻角传感器。该系统通过独特的方法实现并获益，包括在校准飞行期间执行标准飞行操作。该系统不需要飞机的任何空气动力学模型，因为它利用来自校准飞行的信息来开发特定飞机的估计空气动力学模型。该系统利用空气动力学模型和其他信息来估计飞行中飞机的迎角。最后，该系统利用附加信息来指示飞机相对于飞机的最佳迎角和/或飞机的临界迎角的估计迎角。该系统还能够重新校准，以适应飞机的空气动力学修改。

5. 发明申请

WO2022167875A1 HYBRID INFLATABLE AIRCRAFT OF THE UNMANNED TYPE 审中-公开
公开(公告)号：WO2022167875A1
公开(公告)日：2022-08-11
申请号：PCT/IB2022/050246
申请日：2022-01-13
申请人： C.I.R.A. (CENTRO ITALIANO RICERCHE AEROSPAZIALI) S.C.P.A.
发明人： PERSECHINO, Giuseppe , BARANIELLO, Vincenzo Rosario , BORSA, Roberto
IPC分类号： B64C3/10
摘要： There is described a hybrid aircraft (1) of the unmanned type, configured for the joint and optimized use of aerostatic and aerodynamic force, comprising an inflatable body (10) including an outer shell (11) and a load-bearing structure (20) inside said outer shell (11), said inflatable body (10) being adapted to assume a closed wing operating configuration.

6. 发明申请

WO2021053528A1 METHOD FOR MAKING A PASSIVATING COATING BASED ON ONE OR MORE SILICON COMPOUNDS ON A CERAMIC MATRIX COMPOSITE REINFORCED WITH CARBON FIBRES AND CERAMIC MATRIX COMPOSITE REINFORCED WITH CARBON FIBRES WITH SUCH COATING 审中-公开
公开(公告)号：WO2021053528A1
公开(公告)日：2021-03-25
申请号：PCT/IB2020/058604
申请日：2020-09-16
申请人： PETROCERAMICS S.P.A. , C.I.R.A. (CENTRO ITALIANO RICERCHE AEROSPAZIALI) S.C.P.A.
发明人： CAVALLI, Lorenzo , VALLE, Massimiliano , DE STEFANO FUMO, Mario , RUFOLO, Giuseppe Carmine , GARDI, Roberto , CANTONI, Stefania , ROSA, Massimo
IPC分类号： C04B41/00 , C04B41/45 , C04B41/87
摘要： The invention relates to a method for making a silicon compound-based passivating coating on a ceramic matrix composite reinforced with carbon fibres. The method comprises the following steps: a) providing at least one piece made in a ceramic matrix composite reinforced with carbon fibres; b) placing the piece to be coated in a closed chamber of an oven; c) placing in the closed chamber a predefined load of solid silicon avoiding direct contact between the silicon and the piece to be coated; d) heating the oven, maintaining inside the chamber predefined medium vacuum or low vacuum conditions, so as to generate from the silicon load vapours of silicon inside the closed chamber, which react with one or more substances present on the surface of the piece leading to the formation of a surface coating comprising composites of said one or more substances with the silicon; e) choosing the partial pressure of the vacuum, the temperature inside said closed chamber and the exposure times of the piece to the vapours of silicon so as to obtain a predefined thickness of the surface coating on said piece; and f) cooling the piece once the predefined thickness of the passivating coating has been reached.

7. 发明公开

EP4288338A1 HYBRID INFLATABLE AIRCRAFT OF THE UNMANNED TYPE 审中-公开
公开(公告)号：EP4288338A1
公开(公告)日：2023-12-13
申请号：EP22704794.1
申请日：2022-01-13
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： PERSECHINO, Giuseppe , BARANIELLO, Vincenzo Rosario , BORSA, Roberto
IPC分类号： B64C3/10

8. 发明公开

EP3280645A1 SYSTEM AND METHOD FOR ANGLE OF ATTACK INDICATION WITH NO DEDICATED SENSORS AND AIRCRAFT INFORMATION 审中-公开
标题翻译：用于没有专用传感器和飞机信息的角度攻击指示的系统和方法
公开(公告)号：EP3280645A1
公开(公告)日：2018-02-14
申请号：EP16777305.0
申请日：2016-04-07
申请人： Aspen Avionics, Inc. , Centro Italiano Ricerche Aerospaziali S.C.P.A.
发明人： GENITO, Nicola , CORRARO, Federico , GARBARINO, Luca , VITALE, Antonio , DE LELLIS, Ettore , BIBBY, David , RIEB, Sean , JONES, Kevin
IPC分类号： B64D43/00 , B64D43/02 , B64D45/00 , B64C13/02
CPC分类号： G01C23/00 , B64D43/02 , G06F8/61
摘要： A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

9. 发明公开

EP2727825A1 Device for modifying the airfoil geometry 有权
标题翻译： Vorrichtung zum Modifizieren derTragflächengeometrie
公开(公告)号：EP2727825A1
公开(公告)日：2014-05-07
申请号：EP12425175.2
申请日：2012-10-30
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： Ameduri, Salvatore
IPC分类号： B64C3/50 , B64C3/48
CPC分类号： B64C3/48 , B64C3/50 , Y02T50/14
摘要： A device (1) for varying a geometry of a wing profile for leading edges of wings (2) of aircraft (100) comprising an exposed surface (8) extending parallel to the longitudinal development direction of the wing (2); the exposed surface (8) defines a front portion of the wing profile (9) of the wing (2), exhibits a first and a second engaging portion (6, 7) constrained stably to the wing (2) and a deformable portion (5) interposed between the first and the second engaging portions (6, 7) and mobile in relation to the wing (2) such as to enable variations in shape of the portion of wing profile (9) of the wing (2), The device (1) comprises a mechanism (10), arranged internally of a housing compartment (9a) of the wing profile, configured such as to move relatively to the wing along at least a plane that is transversal to the main development direction thereof and such as to generate a deformation of the deformable portion (5). The device (1) comprises an activating element (13) configured such as to move the mechanism (10) and provided with an actuator (14) configured such as to generate a push (S) and a kinematic mechanism (28) receiving the push (S) generated by the actuator (14) and configured such as to move the mechanism (10). The actuator (14) is positioned and configured such as to generate a push (S) in a transversal direction to the movement plane of the mechanism (10) and the kinematic mechanism (28) generates a corresponding action on the mechanism (10) such as to move the mechanism (10) in the movement plane thereof transversal to the main development direction (A).
摘要翻译： 1.一种用于改变飞行器（100）的翼（2）的前缘的翼型的几何形状的装置（1），包括平行于所述翼（2）的纵向展开方向延伸的暴露表面（8）。暴露表面（8）限定翼（2）的翼型（9）的前部，其表现出稳定地约束到翼（2）的第一和第二接合部分（6,7）和可变形部分 5），其插入在第一和第二接合部分（6,7）之间并相对于机翼（2）可移动，以使得翼（2）的翼型（9）的部分的形状能够变化。装置（1）包括机构（10），其布置在机翼轮廓的壳体隔室（9a）的内部，其被构造为沿着至少沿其主显影方向横切的平面相对于翼移动，以产生可变形部分（5）的变形。所述装置（1）包括一个致动元件（13），其构造成使所述机构（10）移动并设置有致动器（14），所述致动器构造成用于产生推动件（S）和运动机构（28）（14）产生并且构造成使得所述机构（10）移动。致动器（14）的定位和构造使得沿着横向于机构（10）的运动平面的方向产生推动（S），并且运动机构（28）产生对机构（10）的相应作用，以使机构（10）沿其移动平面横向于主显影方向（A）移动。

10. 发明公开

EP4095033A1 STRUCTURAL MODULE FOR FIXED OR ROTARY WING 审中-公开
公开(公告)号：EP4095033A1
公开(公告)日：2022-11-30
申请号：EP21425028.4
申请日：2021-05-28
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： Ameduri, Salvatore , Ciminello, Monica , Concilio, Antonio , Dimino, Ignazio , Galasso, Bernardino , Guida, Mariano
IPC分类号： B64C11/20 , B64C3/52 , B64C27/473 , B64C3/18
摘要： A fixed or rotary wing structural module (1) comprises a leading edge structure (2), a torsional actuator (23) mounted on the leading edge structure (2) and comprising a torsion bar (24) and actuating devices (25) operatively coupled to the torsion bar (24). The torsion bar (24) is mounted or mountable on the leading edge structure (2) with a preload torsion, so as to give the structural module (1) a respective predefined twist. The actuation devices (25) are configured to vary a torsional stiffness and/or an angular geometry of the torsion bar (24) so as to vary the twist of the structural module (1) with respect to the predefined twist.

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