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1. 发明公开

EP0708726A1 MECHANICALLY LINKED ACTIVE SIDESTICKS 失效
标题翻译：与机械连接ACTIVE缺搭
公开(公告)号：EP0708726A1
公开(公告)日：1996-05-01
申请号：EP94923545.0
申请日：1994-07-19
申请人： HONEYWELL INC.
发明人： HEGG, Jeffrey, W.
IPC分类号： B64C13 , G05G9
CPC分类号： B64C13/12 , B64C13/0421 , B64C13/10 , B64C13/30 , B64C13/503 , B64C13/505 , G05G2009/04766 , Y02T50/44
摘要： Conventional column controls for aircraft flight control systems are replaced by active sidesticks which are connected to port and starboard aircraft mechanical, electrical or hydraulic systems by means of servo motors and cables. Movement of the active sidestick handles is detected and a signal generated to drive a servo motor in manner corresponding thereto, which in turn will drive cable assemblies which control aircraft flight control surfaces. Two sidesticks are provided, preferably with an electrical cross-cockpit interconnect to cause movement of one sidestick to result in a signal being transmitted to a second sidestick to cause the motor thereof to force the sidestick to track the movement of the first sidestick. In an alternative implementation, the sidesticks are employed in a fly-by-wire system with a conventional cable system as backup. The cable system is disengaged from the sidesticks by means of a disengage clutch whereupon failure of the fly-by-wire system, the clutch will engage the cable system and provide a mechanical backup to the fly-by-wire system in the event of failure thereof.

2. 发明公开

EP4371873A1 FAILSAFE ELECTRO-MECHANICAL ACTUATOR 审中-公开
公开(公告)号：EP4371873A1
公开(公告)日：2024-05-22
申请号：EP23209866.5
申请日：2023-11-14
申请人： Hamilton Sundstrand Corporation
发明人： BALSIGER, Derick S. , BLOXHAM, Keith A.
IPC分类号： B64C13/28 , F16H25/18 , B64C13/34
CPC分类号： F16H49/001 , F16H25/2204 , F16H25/186 , F16H25/205 , B64C13/505 , B64C13/341
摘要： A failsafe electro-mechanical actuator (130), the actuator having: an output shaft (250) having a first and second ends (250A, 250B) spaced apart from each other along a shaft axis, and outwardly facing helical grooves (360) formed along the first end; a motor shaft (180) surrounding the output shaft (250); a harmonic drive (270) between the motor and output shafts that transfers motion between these shafts in a first mode of operation; ball bearings (200D) seated at the first end (180A) of the motor shaft (180) and project inwardly from the motor shaft; in the first mode of operation: the ball bearings (200D) are disengaged from the output shaft (250) and the output shaft rotates with the motor shaft (180), and in a second mode of operation, the motor shaft axially moves toward the first end of the output shaft; the motor shaft is rotationally fixed; and the ball bearings engage the helical grooves in the output shaft, whereby the output shaft rotates.

3. 发明授权

EP3998200B1 FAULT TOLERANT AIRCRAFT FLIGHT CONTROL SYSTEM 有权
公开(公告)号：EP3998200B1
公开(公告)日：2024-04-24
申请号：EP21158264.8
申请日：2021-02-19
IPC分类号： B64C13/50 , B64D31/14 , B64C9/08 , B64C29/00 , B64C39/12 , B64C15/12 , H04L12/40 , G05D1/08
CPC分类号： B64C13/503 , B64C13/505 , B64D31/14 , B64C9/08 , B64C29/0033 , B64C39/12 , B64C15/12 , H04L2012/4021520130101 , H04L2012/402820130101 , G05D1/0077 , H04L12/40006

4. 发明授权

EP2479629B1 Aircraft motor drive control apparatus and aircraft motor drive control system 有权
公开(公告)号：EP2479629B1
公开(公告)日：2024-04-24
申请号：EP12151029.1
申请日：2012-01-13
IPC分类号： G05B19/414 , B64C13/40 , H02P27/08
CPC分类号： G05B19/414 , H02P27/085 , G05B2219/4223920130101 , B64C13/505

5. 发明公开

EP3255437A1 FAULT SOURCE PARAMETER IDENTIFICATION 有权
标题翻译：故障源参数识别
公开(公告)号：EP3255437A1
公开(公告)日：2017-12-13
申请号：EP17175478.1
申请日：2017-06-12
申请人： Simmonds Precision Products, Inc.
发明人： ATALLA, Mauro J. , WIEGELE, Thomas G. , ANDERSON, Kaare Josef , LYNCH, Michael A.
IPC分类号： G01P5/16 , G01P13/02 , G01P21/02 , B64C13/50
CPC分类号： G07C5/0808 , B64C13/505 , B64D43/00 , G01P5/16 , G01P13/025 , G01P21/025
摘要： A first air data value is generated based on a first set of parameters. A second set of parameters that does not include any of the first set of parameters is processed through an artificial intelligence network to generate a second air data value. The second set of parameters is processed through a plurality of diagnostic artificial intelligence networks to generate a plurality of diagnostic air data values. Each of the plurality of diagnostic artificial intelligence networks excludes a different one of the second set of parameters. One of the second set of parameters is identified, based on the first air data value and the plurality of diagnostic air data values, as a fault source parameter that is associated with a fault condition.
摘要翻译：基于第一组参数生成第一空气数据值。通过人工智能网络处理不包括任何第一组参数的第二组参数以生成第二空气数据值。通过多个诊断人工智能网络处理第二组参数以生成多个诊断空气数据值。多个诊断人工智能网络中的每一个都排除了第二组参数中的不同的一个。基于第一空气数据值和多个诊断空气数据值，将第二组参数中的一个识别为与故障状况相关联的故障源参数。

6. 发明公开

EP3076049A2 RHEOLOGIC FLUID COUPLER FOR REDUNDANT LINEAR ELECTROMECHANICAL ACTUATORS 有权转让
标题翻译： KOPPLERFÜRRHEOLOGISCHEFLÜSSIGKEITFÜRREDUNDANTE LINEARE ELEKTROMECHANISCHE AKTUATOREN
公开(公告)号：EP3076049A2
公开(公告)日：2016-10-05
申请号：EP16161881.4
申请日：2016-03-23
申请人： Hamilton Sundstrand Corporation
发明人： HIMMELMANN, Richard A.
IPC分类号： F16H25/20
CPC分类号： B64C13/505 , F16H25/20 , F16H2025/2071 , H01F1/447
摘要： An actuation assembly 10 includes a first shaft 44 comprising a first end 64 disposed opposite a second end 62. The actuation assembly further includes a second shaft 24 with a first end 70 disposed opposite a second end 72. The first end 70 of the second shaft 24 is disposed within the second end 62 of the first shaft 44 such that the first end 70 of the second shaft 24 can move relative the second end 62 of the first shaft 44. A fluid chamber 54 formed between the first shaft 44 and the second shaft 24 at the second end of the first shaft. Magnetorheologic fluid 56 is disposed inside the fluid chamber and a magnetic field generating coil 60 is disposed around the second end of the first shaft 44 and the first end 24 of the second shaft.
摘要翻译：致动组件10包括第一轴44，第一轴44包括与第二端62相对设置的第一端64.致动组件还包括第二轴24，第二轴24具有与第二端72相对设置的第一端70.第二轴的第一端70 24设置在第一轴44的第二端62内，使得第二轴24的第一端70能够相对于第一轴44的第二端62移动。形成在第一轴44和第二轴44之间的流体室54 轴24在第一轴的第二端。磁流变流体56设置在流体室内部，磁场产生线圈60设置在第一轴44的第二端和第二轴的第一端24周围。

7. 发明公开

EP2631171A3 Aircraft actuator hydraulic system 有权
标题翻译：飞机执行器液压系统
公开(公告)号：EP2631171A3
公开(公告)日：2018-01-17
申请号：EP13156715.8
申请日：2013-02-26
申请人： Nabtesco Corporation
发明人： Fukui, Atsushi
IPC分类号： B64C13/40 , B64C13/42
CPC分类号： F15B15/18 , B64C13/504 , B64C13/505 , Y02T50/44
摘要： A plurality of actuators (11a, 11b) operate as a result of pressure oil being supplied thereto from a aircraft central hydraulic power source 104, and drive one control surface 103a. A backup hydraulic pump 18 is installed inside a wing 102a on which a control surface 103a is provided, and is provided so as to be able to supply the pressure oil to the actuators (11a, 11b) if a loss or degradation of the function of a hydraulic power source 104 has occurred. To the actuators (11a, 11b) for driving the one control surface 103a, the pressure oil is supplied from the same aircraft central hydraulic power source 104. The one backup hydraulic pump 18 supplies the pressure oil to the actuators (11a, 11b) for driving the one control surface 103a.
摘要翻译：多个致动器（11a，11b）由于从飞机中央液压动力源104向其供应压力油而操作，并且驱动一个控制表面103a。备用液压泵18安装在设有控制面103a的机翼102a的内部，并且设置成能够向致动器（11a，11b）供给压力油，发生了液压动力源104。向用于驱动一个控制面103a的致动器（11a，11b）从同一飞机中央液压源104供给压力油。一个备用液压泵18向各致动器（11a，11b）供给压力油驱动一个控制表面103a。

8. 发明公开

EP3112698A1 ELECTRO HYDROSTATIC ACTUATORS 有权转让
标题翻译：电动液压驱动器
公开(公告)号：EP3112698A1
公开(公告)日：2017-01-04
申请号：EP15306038.9
申请日：2015-06-30
申请人： Goodrich Actuation Systems SAS
发明人： LESAGE, Emmanuel , GRAND, Serge
IPC分类号： F15B15/18 , F04B49/24 , F04B1/20
CPC分类号： B64C13/504 , B64C13/341 , B64C13/42 , B64C13/505 , F04B1/122 , F04B1/143 , F04B1/145 , F04B1/146 , F04B1/20 , F04B17/03 , F04B49/24 , F15B7/006 , F15B11/024 , F15B20/002 , F15B2011/0243 , F15B2211/20515 , F15B2211/20561 , F15B2211/27 , F15B2211/3058 , F15B2211/31529 , F15B2211/32 , F15B2211/327 , F15B2211/625 , F15B2211/6658 , F15B2211/7054
摘要： An electro hydrostatic actuator (102) comprises a hydraulic pump (106) driven by an electric motor (104) to supply hydraulic fluid to a hydraulic actuator (112). The pump (106) comprises an inlet and an outlet for the hydraulic fluid and an active flow path arranged therebetween such that, in an active mode of operation when the pump (106) is driven by the electric motor (104), hydraulic fluid is actively drawn in through the inlet and exhausted out through the outlet. The pump (106) further comprises a bypass flow path (123) arranged to open between the inlet and outlet such that, in a damping mode of operation when the pump (106) is not driven by the electric motor (104), hydraulic fluid is able to pass through the pump (106) along the bypass flow path (123) between the inlet and outlet.
摘要翻译：一种电动液压致动器（102）包括由电动马达（104）驱动以将液压流体供应到液压致动器（112）的液压泵（106）。泵（106）包括用于液压流体的入口和出口以及设置在它们之间的主动流动路径，使得在泵（106）由电动机（104）驱动时的主动操作模式中，液压流体通过入口主动吸入并通过出口排出。泵（106）还包括布置成在入口和出口之间打开的旁路流动路径（123），使得在泵（106）不被电动机（104）驱动时的减振操作模式中，液压流体能够沿入口和出口之间的旁路流动路径（123）穿过泵（106）。

9. 发明授权

EP0708726B1 MECHANICALLY LINKED ACTIVE SIDESTICKS 失效
标题翻译：与机械连接ACTIVE缺搭
公开(公告)号：EP0708726B1
公开(公告)日：2000-06-28
申请号：EP94923545.1
申请日：1994-07-19
申请人： HONEYWELL INC.
发明人： HEGG, Jeffrey, W.
IPC分类号： B64C13/12
CPC分类号： B64C13/12 , B64C13/0421 , B64C13/10 , B64C13/30 , B64C13/503 , B64C13/505 , G05G2009/04766 , Y02T50/44
摘要： Conventional column controls for aircraft flight control systems are replaced by active sidesticks which are connected to port and starboard aircraft mechanical, electrical or hydraulic systems by means of servo motors and cables. Movement of the active sidestick handles is detected and a signal generated to drive a servo motor in manner corresponding thereto, which in turn will drive cable assemblies which control aircraft flight control surfaces. Two sidesticks are provided, preferably with an electrical cross-cockpit interconnect to cause movement of one sidestick to result in a signal being transmitted to a second sidestick to cause the motor thereof to force the sidestick to track the movement of the first sidestick. In an alternative implementation, the sidesticks are employed in a fly-by-wire system with a conventional cable system as backup. The cable system is disengaged from the sidesticks by means of a disengage clutch whereupon failure of the fly-by-wire system, the clutch will engage the cable system and provide a mechanical backup to the fly-by-wire system in the event of failure thereof.

10. 发明公开

EP3076049A3 RHEOLOGIC FLUID COUPLER FOR REDUNDANT LINEAR ELECTROMECHANICAL ACTUATORS 有权转让
标题翻译：用于冗余线性机电致动器的流变流体联轴器
公开(公告)号：EP3076049A3
公开(公告)日：2016-11-30
申请号：EP16161881.4
申请日：2016-03-23
申请人： Hamilton Sundstrand Corporation
发明人： HIMMELMANN, Richard A.
IPC分类号： F16H25/20 , B64C27/605 , H01F1/44
CPC分类号： B64C13/505 , F16H25/20 , F16H2025/2071 , H01F1/447
摘要： An actuation assembly 10 includes a first shaft 44 comprising a first end 64 disposed opposite a second end 62. The actuation assembly further includes a second shaft 24 with a first end 70 disposed opposite a second end 72. The first end 70 of the second shaft 24 is disposed within the second end 62 of the first shaft 44 such that the first end 70 of the second shaft 24 can move relative the second end 62 of the first shaft 44. A fluid chamber 54 formed between the first shaft 44 and the second shaft 24 at the second end of the first shaft. Magnetorheologic fluid 56 is disposed inside the fluid chamber and a magnetic field generating coil 60 is disposed around the second end of the first shaft 44 and the first end 24 of the second shaft.
摘要翻译：致动组件10包括第一轴44，第一轴44包括与第二端62相对布置的第一端64.致动组件还包括第二轴24，第二轴24具有与第二端72相对布置的第一端70.第二轴的第一端70 24布置在第一轴44的第二端62内，使得第二轴24的第一端70能够相对于第一轴44的第二端62移动。形成在第一轴44和第二轴44之间的流体腔室54 在第一轴的第二端处的轴24。磁流变流体56设置在流体室内，并且磁场产生线圈60设置在第一轴44的第二端和第二轴的第一端24周围。

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