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1. 发明授权

US2926732A Control apparatus for helicopter power units 失效
标题翻译：直升机动力装置的控制装置
公开(公告)号：US2926732A
公开(公告)日：1960-03-01
申请号：US48766155
申请日：1955-02-11
申请人： NAPIER & SON LTD
发明人： DOUGLAS CHAMBERLIN REGINALD HE
IPC分类号： B64D31/08
CPC分类号： B64D31/08

2. 发明申请

US20180043780A1 METHOD FOR PROCESSING THROTTLE CONTROL SIGNAL, ELECTRONIC SPEED REGULATOR, CONTROLLER, AND MOBILE PLATFORM 审中-公开
公开(公告)号：US20180043780A1
公开(公告)日：2018-02-15
申请号：US15725863
申请日：2017-10-05
申请人： SZ DJI TECHNOLOGY CO., LTD.
发明人： Qiu LAN , Changxing ZHOU , Wanqi LIU
IPC分类号： B60L3/00 , B60L3/04 , B60K31/00 , F16H61/12 , B60W10/08
CPC分类号： B60L3/0084 , B60K31/0058 , B60L3/0092 , B60L3/04 , B60W10/08 , B60W2050/0043 , B64D31/00 , B64D31/06 , B64D31/08 , F16H61/12
摘要： A method for processing a throttle control signal includes monitoring a signal transmission state of a throttle signal interface of an electronic speed regulator, determining that the signal transmission state is abnormal, and receiving the throttle control signal via a communication interface of the electronic speed regulator if the signal transmission state is determined to be abnormal.

3. 发明授权

US07949440B2 Aircraft cruise speed control 有权
标题翻译：飞机巡航速度控制
公开(公告)号：US07949440B2
公开(公告)日：2011-05-24
申请号：US12550878
申请日：2009-08-31
申请人： Domingos Candido Wong Ramos , Alex Sander Ferreira Da Silva , Celso Valerio Bastos Casagrande , Salvatore Calandra , Keith Morgan
发明人： Domingos Candido Wong Ramos , Alex Sander Ferreira Da Silva , Celso Valerio Bastos Casagrande , Salvatore Calandra , Keith Morgan
IPC分类号： G06F19/00 , B64D31/08
CPC分类号： B64D31/08 , F02C9/44
摘要： The present invention provides an alternative to the auto-throttle integrated in an aircraft autopilot by restricting the conditions in which the system operates. The proposed system removes the auto-throttle function from the autopilot system and gives it directly to the Full Authority Digital Engine Control (FADEC). A cruise control mode is available to the pilot only under stable flight conditions.
摘要翻译：本发明通过限制系统操作的条件来提供集成在飞行器自动驾驶仪中的自动调节器的替代方案。所提出的系统从自动驾驶仪系统中去除自动油门功能，并将其直接提供给全权限数字引擎控制（FADEC）。飞行员只有在稳定的飞行条件下才能使用巡航控制模式。

4. 发明申请

US20180079519A1 Precision Operator for an Aircraft Autothrottle or Autopilot System 审中-公开
公开(公告)号：US20180079519A1
公开(公告)日：2018-03-22
申请号：US15554642
申请日：2016-08-01
申请人： INNOVATIVE SOLUTIONS & SUPPORT, INC.
发明人： Geoffrey S.M. HEDRICK
IPC分类号： B64D31/14 , B64D31/12 , B64D31/10 , B64C13/10 , B64D31/04
CPC分类号： B64D31/02 , B64C13/10 , B64D31/04 , B64D31/06 , B64D31/08 , B64D31/10 , B64D31/12 , B64D31/14 , B64D45/00 , G07C5/0816
摘要： An autothrottle system for an aircraft includes a motor, actuator assembly, and position sensor operatively connected between the motor and a moving portion of the actuator assembly. An electronic controller is configured to control the motor to move the actuator assembly to actuator positions based at least on position information from the position sensor to move the throttle lever to lever positions. The actuator assembly includes a bearing assembly having a plurality of bearings to contact a surface of a shaft for converting rotational movement of the shaft into linear motion of the bearing assembly along the shaft. The actuator assembly further includes a shuttle arm having at one end a mounting surface to attach to the bearing assembly and at the other end a linkage arm operatively coupled to the attachment end of the lever.

5. 发明申请

US20160272336A1 AIRCRAFT PILOTING ASSISTANCE SYSTEM AND METHOD 审中-公开
标题翻译：飞机引导辅助系统和方法
公开(公告)号：US20160272336A1
公开(公告)日：2016-09-22
申请号：US15063940
申请日：2016-03-08
申请人： DASSAULT AVIATION
发明人： Sébastien LEPAGE
IPC分类号： B64D31/08
CPC分类号： G05D1/0066 , B64C13/16 , B64C19/02 , B64D31/08 , G01C23/00 , G05D1/0055 , G05D1/0816
摘要： A piloting assistance system for an aircraft during manual piloting is provided. The piloting assistance system includes a monitoring module, configured to compare an acceleration of the aircraft to an authorized acceleration that depends on a speed of the aircraft, an acceleration control module, able to be switched between an activated state and a deactivated state, and configured so as, in the activated state, excluding the deactivated state, to generate a control signal of at least one control device of the acceleration of the aircraft to push the acceleration of the aircraft toward the authorized acceleration range, in order to keep or push the speed of the aircraft in a predefined usage speed range, the monitoring module being configured to activate the acceleration control module when the acceleration of the aircraft is not comprised in the authorized acceleration range.
摘要翻译：提供了在手动驾驶期间为飞机提供驾驶辅助系统。驾驶辅助系统包括监视模块，其被配置为将飞行器的加速度与取决于飞行器速度的授权加速度进行比较，加速控制模块能够在激活状态和停用状态之间切换，并配置在激活状态下，除了去激活状态之外，为了产生飞行器的加速度的至少一个控制装置的控制信号，将飞行器的加速度推向授权的加速度范围，以便保持或推动所述监视模块被配置为当所述飞机的加速度不包括在所述授权的加速度范围内时激活所述加速控制模块。

6. 发明授权

US08798810B2 Energy protecting device for aircraft 有权
标题翻译：飞机能量保护装置
公开(公告)号：US08798810B2
公开(公告)日：2014-08-05
申请号：US12066599
申请日：2006-09-12
申请人： Franck Delaplace , Didier Ronceray , Jean Muller
发明人： Franck Delaplace , Didier Ronceray , Jean Muller
IPC分类号： G01C23/00 , B64D31/08 , B64D31/06 , B64D31/10 , G05D1/00 , B64D27/02
CPC分类号： B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
摘要： An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.
摘要翻译：用于三发射机和四发射机的能量保护装置包括：检测单元，被配置为检测每个发动机的故障。控制单元被配置为通过控制每个发动机的最大推力来提供保护功能。触发单元被配置为监视多个参数并且触发控制单元以在所监视的参数的预定条件下提供最大推力。禁止单元连接到触发单元并且被配置为当飞行器的机翼上的发动机中的至少一个发生故障时禁止保护功能。控制单元还被配置为控制未失效的发动机以最小化推力不平衡。

7. 发明申请

US20080208398A1 Energy Protecting Device for Aircraft 有权
标题翻译：飞机能量保护装置
公开(公告)号：US20080208398A1
公开(公告)日：2008-08-28
申请号：US12066599
申请日：2006-09-12
申请人： Franck Delaplace , Didier Ronceray , Jean Muller
发明人： Franck Delaplace , Didier Ronceray , Jean Muller
IPC分类号： B64D31/10
CPC分类号： B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
摘要： The invention concerns a device (1) comprising control means (3) for activating a protective function which consists in automatically controlling the engines (M1 to M4) so that they supply maximum power when the triggering conditions are fulfilled, and inhibiting means (8) for inhibiting the protective function solely when all the engines which are arranged on a common wing of the aircraft have simultaneously broken down.
摘要翻译：本发明涉及一种装置（1），包括用于启动保护功能的控制装置（3），该保护功能包括自动控制发动机（M 1至M 4），使得它们在触发条件满足时提供最大功率;以及禁止装置 8）用于仅当布置在飞机的共同翼上的所有发动机已经同时分解时才抑制保护功能。

8. 发明授权

US06186447B1 Autothrottle retard rate control system 失效
标题翻译：自动延迟率控制系统
公开(公告)号：US06186447B1
公开(公告)日：2001-02-13
申请号：US09107340
申请日：1998-06-30
申请人： Arvinder S. Virdee
发明人： Arvinder S. Virdee
IPC分类号： G05D112
CPC分类号： B64D31/08 , F02C9/00 , F02C9/28
摘要： In an autothrottle system having the capability to reduce engine throttle setting from a first position to an idle position, an improvement including calculating a rate of throttle reduction as a function of the combination of a nominal retard rate value (10) and a retard rate adjustment value (12). In one embodiment, the nominal retard rate value (10) is equal to the angular difference between a current engine throttle control lever position (TRA) and an idle engine throttle control lever position (TRAIDLE), the difference being divided by an amount in the range of about 3 seconds to about 10 seconds. The retard rate adjustment value (12) is calculated as a function of the difference between current airspeed (VC) and a commanded airspeed (VCMD). During an underspeed condition, the retard rate adjustment signal decreases the rate of throttle reduction from the nominal retard rate value (10). During an overspeed condition, the retard rate adjustment signal increases the rate of throttle reduction from the nominal retard rate value (10).
摘要翻译：在具有将发动机节气门设定从第一位置减小到空闲位置的能力的自动油门系统中，改进包括计算作为标称延迟率值（10）和延迟速率调整（10）的组合的节气门减小速率值（12）。在一个实施例中，标称延迟率值（10）等于当前发动机节气门控制杆位置（TRA）和怠速发动机节气门控制杆位置（TRAIDLE）之间的角度差，该差除以范围约3秒至约10秒。延迟率调整值（12）根据当前空速（VC）和指令空速（VCMD）之间的差值来计算。在低速条件下，延迟率调节信号会从标称延迟率值（10）降低节气门减速的速度。在超速状态下，延迟率调节信号会从标称延迟率值（10）上提高节气门减速率。

9. 发明申请

US20170297731A1 System and method for controlling the thrust of the engines of an aircraft 审中-公开
公开(公告)号：US20170297731A1
公开(公告)日：2017-10-19
申请号：US15478765
申请日：2017-04-04
申请人： Airbus Operations SAS
发明人： Fabien Guingnard , Priteche Venilal
IPC分类号： B64D31/08 , G05B15/02
CPC分类号： B64D31/08 , F02C9/44 , F05D2270/051 , F05D2270/122 , G05B15/02 , G05D1/063
摘要： A system for controlling the thrust of the engines of an aircraft comprises a processing unit configured to receive an aircraft speed setting, to determine a control setting for at least one engine of the aircraft as a function of the speed setting and to transmit a setting to a controller of the at least one engine of the aircraft as a function of the control setting. The processing unit is further configured to receive a current turbulence level measurement information item and to add an additional speed setting, as a function of the turbulence level, to the speed setting.

10. 发明申请

US20100125378A1 AUTOMATIC THROTTLE ROLL ANGLE COMPENSATION 有权
标题翻译：自动曲轴角度补偿
公开(公告)号：US20100125378A1
公开(公告)日：2010-05-20
申请号：US12274756
申请日：2008-11-20
申请人： Frederick Charles Henry Blechen
发明人： Frederick Charles Henry Blechen
IPC分类号： G05D1/00
CPC分类号： B64D31/08 , B64C13/00 , G05D1/042 , G05D1/0607 , G05D1/0808 , G05D1/101
摘要： A method, apparatus, and computer program product for adjusting a thrust for an aircraft. A level of thrust is dynamically identified using a drag on the aircraft needed to substantially maintain a speed of the aircraft in a turn to form an identified level of thrust during turning of the aircraft. The turn of the aircraft is performed using the identified level of thrust.
摘要翻译：一种用于调整飞行器的推力的方法，装置和计算机程序产品。使用飞机上的拖曳来动态地确定推力水平，所述拖曳需要大幅度地维持飞行器的转速，以在飞行器转动期间形成确定的推力水平。使用确定的推力水平来执行飞机的转弯。

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