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1. 发明授权

EP4082898B1 CONTROL SYSTEM FOR AN AIRCRAFT 有权
公开(公告)号：EP4082898B1
公开(公告)日：2024-07-17
申请号：EP21171623.8
申请日：2021-04-30
IPC分类号： B64C13/40
CPC分类号： B64C13/40

2. 发明授权

EP2412629B1 Damping test method, control apparatus, hydraulic system, and program 有权
公开(公告)号：EP2412629B1
公开(公告)日：2018-12-12
申请号：EP11175545.0
申请日：2011-07-27
申请人： Nabtesco Corporation
发明人： Fukui, Atsushi , Suzuki, Kazuyuki , Ogawa, Toshiaki , Mori, Atsushi
IPC分类号： B64F5/60 , B64C13/40
CPC分类号： B64C13/40 , B64F5/60 , Y02T50/44
摘要： The control apparatus acquires an ideal velocity characteristic of a control surface(104,105), and the temperature of pressure oil of the actuator (11,12) to be tested and the operating speed of the control surface (104,105) when the actuator is attached to the control surface. The control apparatus corrects the ideal velocity characteristic of the control surface by using the pressure oil temperature and the control surface operating speed. The control apparatus sets an upper limit and a lower limit by using a predicted value for a fluctuation range for a fluctuation factor that causes a fluctuation of the control surface operating speed, with reference to the corrected ideal velocity characteristic, measures the pressure oil temperature and the operating speed by actuating the control surface (104,105), with the actuator to be tested placed in a damping mode, and determines whether the measured value falls within the range between the upper limit and the lower limit.

3. 发明公开

EP3378763A1 AIRCRAFT HYDRAULIC SYSTEMS HAVING SHARED COMPONENTS 有权
公开(公告)号：EP3378763A1
公开(公告)日：2018-09-26
申请号：EP18155552.5
申请日：2018-02-07
申请人： Bell Helicopter Textron Inc.
发明人： ELVING, Carl Theodore , REYNOLDS, Robert Paul , HAWTHORNE, David Alan , FENNY, Carlos Alexander
IPC分类号： B64C13/40 , B64D41/00 , B64C13/42 , F15B18/00 , B64C29/00 , B64C27/28
CPC分类号： F15B11/17 , B64C13/36 , B64C13/40 , B64C13/42 , B64C27/28 , B64C29/0033 , B64D29/02 , B64D41/00 , F15B1/26 , F15B2211/20576 , F15B2211/7142 , Y02T50/44
摘要： A hydraulic system (100) for an aircraft having an engine (108) and an auxiliary power unit (122) includes a first hydraulic subsystem (102) including a first hydraulic pump (106) and a first set of hydraulic-powered components (112, 114, 116) in fluid communication with the first hydraulic pump (106). The first hydraulic pump (106) is powered by the engine (108) to pump shared hydraulic fluid to the first set of hydraulic-powered components (112, 114, 116). The hydraulic system (100) includes a second hydraulic subsystem (104) including a second hydraulic pump (120) and a second set of hydraulic-powered components (126, 128, 130) in fluid communication with the second hydraulic pump (120). The second hydraulic pump (120) is powered by the auxiliary power unit (122) to pump the shared hydraulic fluid to the second set of hydraulic-powered components (126, 128, 130). A shared return line subsystem (134) and reservoir (136) is in fluid communication with the first and second hydraulic subsystems (102, 104) to return the shared hydraulic fluid to the first and second hydraulic pumps (106, 120).

4. 发明公开

EP3335987A1 INTEGRATED STABILITY AND CONTROL AUGMENTATION SYSTEM 有权
公开(公告)号：EP3335987A1
公开(公告)日：2018-06-20
申请号：EP16204826.8
申请日：2016-12-16
申请人： Microtecnica S.r.l.
发明人： Maino, Franco , Molinelli, Dario , Artoni, Ettore
IPC分类号： B64C13/40
CPC分类号： F16K31/1225 , B64C13/18 , B64C13/40 , B64C13/42 , B64C13/44 , G05D1/0816
摘要： Disclosed herein is a SCAS module (20) comprising one or more SCAS actuators (201,202) wherein each SCAS actuator comprises a piston (2013) arranged for linear motion within a hydraulic chamber in response to a flow of hydraulic fluid metered by a valve. The piston comprises a flexible rod or quill (2012) for providing a linear output along the first axis, the flexible rod or quill (2012) being mounted internally within an annular portion of the piston (2013) so that a space is defined around the flexible rod or quill (2012). The flexible rod or quill (2012) is capable of deforming into the surrounding space in order to accommodate movement of the flexible rod or quill (2012). The SCAS actuator may be mechanically integrated into an actuator system for a main or tail rotor of a helicopter. The actuator system may comprise a hydraulic actuator (10) for providing an output to a main or tail rotor of the helicopter; the SCAS module (20); a control valve (11) for controlling the flow of hydraulic fluid to the hydraulic actuator to vary the output provided to the main or tail rotor; and a linkage mechanism connecting the control valve to the hydraulic actuator, the linkage mechanism comprising a plurality of interconnected levers including a first lever (15) for receiving an input from a pilot, and a second input (16) arranged to receive an output from the SCAS module, wherein the linkage mechanism is configured to sum or otherwise combine the outputs from the first and second levers into a composite command and to transmit the composite command to the control valve (11) to control the flow of hydraulic fluid to the hydraulic actuator (10). Also disclosed is a helicopter comprising such an actuator system or SCAS module (20).

5. 发明公开

EP2722274A3 Flow control actuator with an adjustable frequency 有权
标题翻译：带可调频率的流量控制执行器
公开(公告)号：EP2722274A3
公开(公告)日：2017-11-22
申请号：EP13184675.0
申请日：2013-09-17
申请人： The Boeing Company
发明人： Raghu, Surya
IPC分类号： B64C21/04 , B64C21/08 , B64C13/40 , F15B21/12 , F17D1/02 , F16L55/04
CPC分类号： F15B21/12 , B64C13/40 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , F16L55/04 , F17D1/02 , Y02T50/166 , Y10T137/0318 , Y10T137/0324
摘要： A method and apparatus comprising a structure (204) and a chamber (210) within the structure (204). The structure (204) has an input port (206) and an output port (208). The chamber (204) is configured to channel a fluid (212) from the input port (206) to the output port (208) of the structure (204). A volume (214) of the chamber (210) is configured to change such that a frequency (216) at which the fluid 212) flows out of the output port (208) changes at the output port (208).
摘要翻译：一种方法和装置，包括结构（204）内的结构（204）和腔室（210）。结构（204）具有输入端口（206）和输出端口（208）。腔室（204）构造成将流体（212）从输入端口（206）引导至结构（204）的输出端口（208）。腔室（210）的容积（214）被配置成改变，使得流体212）流出输出端口（208）的频率（216）在输出端口（208）处改变。

6. 发明公开

EP2557034A3 Hybrid power system architecture for an aircraft 有权
标题翻译：飞机的混合动力系统架构
公开(公告)号：EP2557034A3
公开(公告)日：2017-08-02
申请号：EP12179968.8
申请日：2012-08-09
申请人： Hamilton Sundstrand Corporation
发明人： Bruno, Louis J. , Jones, Anthony C. , Spierling, Todd A. , DeFrancesco, Gregory L.
IPC分类号： B64C13/40 , B64C13/42
CPC分类号： B64D41/00 , B64C13/40 , B64C13/42 , B64D2221/00
摘要： A hybrid power distribution system (10) for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus (50) that distributes electrical energy onboard the aircraft, a pneumatic distribution channel (28a,28b) that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines (12a,12b) associated with the aircraft.
摘要翻译：用于飞行器的混合动力分配系统（10）从多个动力源中的一个动力源产生液压动力，基于动力源最有效地提供能量。电源包括分配飞机上的电能的电力分配总线（50），分配飞行器上的气动能量的气动分配通道（28a，28b）以及由一个或多个发动机（12a，12b）提供的机械动力，与飞机相关。

7. 发明公开

EP2412629A3 Damping test method, control apparatus, hydraulic system, and program 有权
标题翻译：阻尼测试方法，控制装置，液压系统和程序
公开(公告)号：EP2412629A3
公开(公告)日：2017-07-05
申请号：EP11175545.0
申请日：2011-07-27
申请人： Nabtesco Corporation
发明人： Fukui, Atsushi , Suzuki, Kazuyuki , Ogawa, Toshiaki , Mori, Atsushi
IPC分类号： B64C13/40 , B64F5/00
CPC分类号： B64C13/40 , B64F5/60 , Y02T50/44
摘要： The control apparatus acquires an ideal velocity characteristic of a control surface(104,105), and the temperature of pressure oil of the actuator (11,12) to be tested and the operating speed of the control surface (104,105) when the actuator is attached to the control surface. The control apparatus corrects the ideal velocity characteristic of the control surface by using the pressure oil temperature and the control surface operating speed. The control apparatus sets an upper limit and a lower limit by using a predicted value for a fluctuation range for a fluctuation factor that causes a fluctuation of the control surface operating speed, with reference to the corrected ideal velocity characteristic, measures the pressure oil temperature and the operating speed by actuating the control surface (104,105), with the actuator to be tested placed in a damping mode, and determines whether the measured value falls within the range between the upper limit and the lower limit.
摘要翻译：控制装置获取控制表面（104,105）的理想速度特性，以及当致动器附接到控制表面（104,105）时待测试的致动器（11,12）的压力油的温度和控制表面（104,105）的操作速度控制面。控制装置通过使用压力油温度和控制表面操作速度来校正控制表面的理想速度特性。控制装置参照修正后的理想速度特性，通过使用引起控制表面操作速度波动的波动因子的波动范围的预测值来设置上限和下限，测量压力油温度并且通过致动控制表面（104,105）的操作速度，待测试的致动器置于阻尼模式，并确定测量值是否落入上限和下限之间的范围内。

8. 发明公开

EP2383181A3 Hydraulic apparatus for aircraft actuators 有权
标题翻译：飞机执行器液压装置
公开(公告)号：EP2383181A3
公开(公告)日：2017-05-31
申请号：EP11164151.0
申请日：2011-04-28
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Fukui, Atsushi
IPC分类号： B64C13/40 , B64C13/50 , B64C13/42 , F15B1/00 , F15B20/00
CPC分类号： B64C13/40 , B64C13/42 , F15B2211/20515 , F15B2211/20576 , F15B2211/62 , F15B2211/8633 , Y02T50/44
摘要： A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.
摘要翻译：提供安装在机翼（100）内的泵单元（12）和构成形成机翼（100）的表面结构的机翼结构部分的一部分的面板体（11）。泵单元12包括备用液压泵13，该备用液压泵13可以在飞机中央液压动力源和驱动该泵的电动机14的功能发生损失或减少时向致动器供应压力油。除了至少面板本体外，翼结构部分由纤维增强塑料形成。面板主体（11）由金属材料形成。

9. 发明授权

EP2806173B1 VENT VALVE 有权
标题翻译：排气阀
公开(公告)号：EP2806173B1
公开(公告)日：2017-03-01
申请号：EP14169043.8
申请日：2014-05-20
申请人： Hamilton Sundstrand Corporation
发明人： WAKEFIELD, David L. , NOREM, Dean A.
IPC分类号： F15B13/04
CPC分类号： F16K11/02 , B64C11/38 , B64C13/40 , B64C27/64 , F15B13/01 , F15B20/004 , Y10T137/0324 , Y10T137/86582

10. 发明公开

EP3109167A1 AUXILIARY POWER UNIT WITH INTERCOOLER 有权
标题翻译： HILFSAGGREGAT MITZWISCHENKÜHLER
公开(公告)号：EP3109167A1
公开(公告)日：2016-12-28
申请号：EP16176139.0
申请日：2016-06-24
申请人： Pratt & Whitney Canada Corp.
发明人： ULLYOTT, Richard , JONES, Anthony , JULIEN, Andre , THOMASSIN, Jean
IPC分类号： B64D41/00 , F02M35/10 , F01C1/22
CPC分类号： B64D41/00 , B64C13/40 , B64D2041/002 , F01C1/22 , F01C21/008 , F01C21/06 , F01C21/08 , F01D5/06 , F01D15/10 , F01D17/20 , F01D25/18 , F02B33/40 , F02B41/10 , F02B55/00 , F02B63/042 , F02C7/06 , F02C7/32 , F02C7/36 , F04D27/009 , F04D29/286 , F04D29/321 , F04D29/462 , F04D29/563 , F04D29/582 , F05D2220/50 , F05D2220/76 , F05D2260/211 , Y02T10/163 , Y02T10/17 , Y02T50/44 , Y02T50/53
摘要： An auxiliary power unit (10) for an aircraft, having a compressor (18), an intercooler (26) including first conduit(s) having an inlet in fluid communication with the compressor outlet (180) and second conduit(s) configured for circulation of a coolant therethrough, an engine core (12) having an inlet (12i) in fluid communication with an outlet of the first conduit(s), and a bleed conduit (74) in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator (14) in driving engagement with the shaft of the engine core (12) to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.
摘要翻译：一种用于飞行器的辅助动力单元（10），具有压缩机（18），中间冷却器（26），包括具有与压缩机出口（180）流体连通的入口的第一导管和第二导管，冷却剂通过其循环，具有与第一导管的出口流体连通的入口（12i）的发动机芯（12）和与第一导管的出口流体连通的排放导管（74） s）通过排气阀。辅助动力单元可以包括与发动机芯（12）的轴驱动接合以提供飞机电力的发电机（14）。还讨论了向飞行器提供压缩空气和电力的方法。

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