| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 用于控制飞行器机翼襟翼运动的系统和方法 | CN201710228710.3 | 2017-04-10 | CN107303946A | 2017-10-31 | M·R·芬; P·麦考密克; G·莫伊; R·T·源 |
| 本申请涉及用于控制飞行器机翼襟翼运动的系统和方法。其包括：从联接至相应的第一致动器(112)和第二致动器(114)的相应的第一传感器(120)和第二传感器(122)接收第一传感器信号和第二传感器信号。第一传感器信号和第二传感器信号与相应的第一致动器和第二致动器的位置或速度中的一个或两个有关。该系统和方法还包括：比较第一传感器信号与第二传感器信号，以确定第一传感器信号与第二传感器信号之间的差异，并且基于该差异来调节第一致动器或第二致动器中的一个或两个的速度。该系统和方法包括：确定第一襟翼(102)和第二襟翼(108)的速度或位置中的一个或两个之间的差异，并且基于该差异来调节第一襟翼和第二襟翼中的一个或两个的速度。 | ||||||
| 2 | Display system | JP2004187687 | 2004-06-25 | JP4523346B2 | 2010-08-11 | キース・デーヴィッド・スティックルズ |
| 3 | 航空機の翼のフラップ動作を制御するためのシステム及び方法 | JP2017081856 | 2017-04-18 | JP2017197173A | 2017-11-02 | マイケル レイモンド フィン; パトリック マコーミック; ジョージ モイ; ルネ トアン グエン |
| 【課題】航空機用フラップシステムの翼間の非対称性を排除、最小化、又は低減するシステム及び方法を提供する。 【解決手段】該方法は、航空機106の第1翼104の第1フラップ102に取り付けられた第1及び第2のアクチュエータ112、114のそれぞれに接続された第1及び第2のセンサ120、122から、第1及び第2センサ信号を受信する。第1及び第2のセンサ信号は、第1及び第2のアクチュエータ112、114のそれぞれの位置又は速度の一方又は両方に関連する。上記方法は、第1及び第2のセンサ信号を比較して差異を特定し、それに基づいて、第1又は第2のアクチュエータ112、114の一方又は両方の速度を調整する。上記方法は又、第1及び第2のフラップ102、108の速度又は位置の一方又は両方の間の差異を特定し、それに基づいて、第1及び第2のフラップ102、108の一方又は両方の速度を調整する。 【選択図】図1 |
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| 4 | Helicopter collective control device | JP23197087 | 1987-09-16 | JP2585293B2 | 1997-02-26 | SUCHUAATO KYAMETSUTO RAITO; ROOREN SUTEIRUZU JUNIA; DON RUISU ADAMUSU |
| 5 | Controller for cockpit of airship | JP11323793 | 1993-05-14 | JPH0656095A | 1994-03-01 | DEIITAA KURITSUKE; TEIRO RIIBIITSUHI |
| PURPOSE: To prevent erroneous operation and oversight of important information in case of an emergency in which a plurality of displays should be caught by integrating an input member with an output member of a controller for airship cockpit. CONSTITUTION: This controller for airship cockpit is formed by an input member 1 and an output member 2 within the range of a flat operation unit 3. The operation unit 3 has a coating sensitive to a contact within at least its surface, and the coating is connected to an evaluation unit, detects respective contact coordinates, and transfers them to a sequence unit 9. The sequence unit 9 registers the initiation of contact as primary selection and activates a control function immediately before the contact finishes in association with contact position adjustment. | ||||||
| 6 | Collective controller for helicopter | JP23197087 | 1987-09-16 | JPS6382898A | 1988-04-13 | SUCHIYUAATO KIYAMETSUTO RAITO; ROOREN SUTEIRUZU JIYUNIA; DON RUISU ADAMUSU |
| 7 | Method and apparatus for aircraft maneuvering during taxiing | JP2008516374 | 2006-06-12 | JP4997232B2 | 2012-08-08 | ベルアール、レミ; ミュレ、ジャン |
| 8 | Method and apparatus for aircraft maneuvering during taxiing | JP2008516374 | 2006-06-12 | JP2008543646A | 2008-12-04 | ベルアール、レミ; ミュレ、ジャン |
| 本発明の方法は、左右のブレーキ指令(ＦＧ， ＦＤ)間の差異(Ｄ１)を形成することと、前記差異(Ｄ１)を方向舵(１６)と操縦可能な前輪(４)のための追加の制御指令(Ｄ２)に変換することと、前記追加の制御指令(Ｄ２)を次の２つの条件、すなわち、その差異(Ｄ１)が第１の閾値より大きく、方向舵バーにより方向舵と操縦可能な前輪(４)に伝達された、組み合わせられた制御指令が第２の閾値より小さいという条件に従って、方向舵(１６)と操縦可能な前輪(４)に与えることからなる。
【選択図】 図４ |
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| 9 | Display system | JP2004187687 | 2004-06-25 | JP2005014903A | 2005-01-20 | STICKELS KEITH DAVID |
| <P>PROBLEM TO BE SOLVED: To provide a layout of an operating part capable of meeting the required specification of different operators without repeatedly performing trial manufacture. <P>SOLUTION: This display system 10 used for displaying the layout of the operating part including at least one of information displays 21 and 28 for vehicle, switches, and monitor devices comprises a touch screen 11 most of the area thereof is generally transparent and a plurality of projectors 12, 13, and 14 projecting the image of the vehicle operation part on the rear surface of the screen 11. Each of the projectors 12, 13, and 14 is connected to a computer controller 18 so as to be operated, and the computer controller 18 changes display so as to simulate the actual results of the operation of the corresponding vehicle operation part in response to a touch on the front face of the screen 11 at a position where the delineation operation part is displayed. <P>COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 10 | JPS5611639B1 - | JP3432072 | 1972-04-05 | JPS5611639B1 | 1981-03-16 | |
| 11 | JPS5018280B1 - | JP2348370 | 1970-03-20 | JPS5018280B1 | 1975-06-27 | |
| 12 | 디스플레이 시스템 | KR1020040047261 | 2004-06-23 | KR101008584B1 | 2011-01-17 | 스틱켈스케이스데이비드 |
| 적어도 하나의 정보 표시부(information display), 토글(toggle) 또는 푸쉬버튼(push-button) 스위치와 같은 스위치, 그리고 지시계 또는 계기와 같은 모니터링 장치를 구비하는 제어기기들의 레이아웃을 표시하기 위한 운송수단용 디스플레이 시스템에 있어서, 그 디스플레이 시스템은 대부분의 면적이 전체적으로 투명한 터치 스크린, 그리고 스크린의 후방부 상으로 운송수단 제어기기들의 이미지들을 투영시키는 복수의 프로젝터들을 포함하며, 그 프로젝터들 각각은, 묘사된 제어기기가 표시되며 만져지는 스크린의 전방부에 응답하는 컴퓨터 콘트롤러(controller)에 효과적으로 연결되어서 작동 중인 실제 운송수단 제어기기에 대응되는 결과를 모방하는 방식으로 디스플레이부를 변화시킨다. | ||||||
| 13 | SYSTEM AND METHOD FOR CONTROLLING AIRCRAFT WING FLAP MOTION | EP17167104.3 | 2017-04-19 | EP3239043B1 | 2018-11-28 | FINN, Michael Raymond; McCORMICK, Patrick; MOY, George; NGUYEN, Rene Toan |
| A system and method of controlling one or more flaps (102, 108) of an aircraft (106) may include receiving first and second sensor signals from respective first and second sensors (120, 122) coupled to respective first and second actuators (112, 114) that are moveably secured to a first flap (102) of a first wing (104) of the aircraft (106). The first and second sensor signals relate to one or both of the position or the speed of the respective first and second actuators (112, 114). The system and method may also include comparing the first and second sensor signals to determine a difference between the first and second sensor signals, and adjusting the speed of one or both of the first or second actuators (112, 114) based on the difference between the first and second sensor signals. A system and method may include determining a difference between one or both of speed or position of the first and second flaps (102, 108), and adjusting the speed of one or both of the first and second flaps (102, 108) based on the difference between one or both of the speed or the position of the first and second flaps (102, 108). | ||||||
| 14 | RECONFIGURABLE UNMANNED AIRCRAFT SYSTEM | EP15864636.4 | 2015-12-01 | EP3227181A1 | 2017-10-11 | CHAN, Alistair K.; CHEATHAM, Jesse R. III; CHIN, Hon Wah; DUNCAN, William David; HYDE, Roderick A.; ISHIKAWA, Muriel Y.; KARE, Jordin T.; PAN, Tony S.; PETROSKI, Robert C.; TEGREENE, Clarence T.; TUCKERMAN, David B.; WEAVER, Thomas Allan; WOOD, Lowell L., Jr. |
| A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission. | ||||||
| 15 | ACTUATOR CONTROL SYSTEM | EP12710780.3 | 2012-03-22 | EP2691298A1 | 2014-02-05 | WHITE, Nicholas, James; MORGAN, Stephen, Richard; CLARKSTONE, John, Kenneth |
| An actuator control system for coupling to one or more flight control computers (FCCs); comprising: apparatus for controlling an aerodynamic control surface in response to commands received from one or more FCCs, and, integrated with the controlling apparatus, a failure protection system comprising apparatus arranged to provide at least one of the following functionalities: a servo monitor functionality, a command monitor functionality, and a loop closure functionality. Thus, in the overall flight control system, some or all of the elements of the failure protection system are located in the actuator control stage. | ||||||
| 16 | PROCEDE ET DISPOSITIF POUR LA CONDUITE D'UN AERONEF ROULANT SUR LE SOL | EP06764770.1 | 2006-06-12 | EP1890935A1 | 2008-02-27 | BELLOUARD, Rémi; MULLER, Jean |
| The inventive method consists in forming a difference (D1) between left and right braking commands (FG, FD), in converting said difference (D1) into an additional control command (D2) for a rudder (16) and for a steerable nose gear (4) and in applying said additional control command (D2) to said rudder (16) and steerable nose gear (4) according to both following conditions: the difference (D1) is greater than a first threshold and the combined control command transmitted to the rudder and steerable nose gear (4) by a rudder bar is less than a second threshold. | ||||||
| 17 | Display system for a vehicle | EP04012067.7 | 2004-05-21 | EP1491444A1 | 2004-12-29 | Stickels, Keith David |
A display system (10) for displaying a layout of controls including at least one of an information display (21,28), a switch such as a toggle or push-button switch (25,29), and a monitoring device such as an indicator (22,24), or a gauge (23), for a vehicle, the display system (10) including a touch sensitive screen (11) which is generally transparent over a significant portion of its area, and a plurality of projectors (12,13,14) which project onto a back of the screen (11), images of the vehicle controls, the projectors (12,13,14) each being operatively connected to a computer controller (18) which responds to the front of the screen (11) being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated. |
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| 18 | Steuervorrichtung für Cockpits von Flugzeugen | EP93105543.8 | 1993-04-03 | EP0570690A3 | 1995-04-26 | Kricke, Dieter; Liebig, Thilo |
Die Steuervorrichtung für Cockpits von Flugzeugen wird durch Eingabeelemente und Ausgabeelemente im Bereich einer flächigen Bedieneinheit gebildet. Die Bedieneinheit weist mindestens in einem Bereich ihrer Oberfläche eine berührungssensitive Beschichtung auf, die mit einer Auswertungseinheit verbunden ist und die jeweiligen Berührungskoordinaten ermittelt sowie zu einer Ablaufeinheit überträgt. Die Ablaufeinheit registriert einen Berührungsbeginn als eine Vorauswahl und löst in Abhängigkeit von einer Berührungspositionierung unmittelbar vor einer Beendigung des Berührungskontaktes eine Steuerfunktion aus. |
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| 19 | Steuervorrichtung für Cockpits von Flugzeugen | EP93105543.8 | 1993-04-03 | EP0570690A2 | 1993-11-24 | Kricke, Dieter; Liebig, Thilo |
Die Steuervorrichtung für Cockpits von Flugzeugen wird durch Eingabeelemente und Ausgabeelemente im Bereich einer flächigen Bedieneinheit gebildet. Die Bedieneinheit weist mindestens in einem Bereich ihrer Oberfläche eine berührungssensitive Beschichtung auf, die mit einer Auswertungseinheit verbunden ist und die jeweiligen Berührungskoordinaten ermittelt sowie zu einer Ablaufeinheit überträgt. Die Ablaufeinheit registriert einen Berührungsbeginn als eine Vorauswahl und löst in Abhängigkeit von einer Berührungspositionierung unmittelbar vor einer Beendigung des Berührungskontaktes eine Steuerfunktion aus. |
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| 20 | SYSTEM AND METHOD FOR CONTROLLING AIRCRAFT WING FLAP MOTION | EP17167104.3 | 2017-04-19 | EP3239043A1 | 2017-11-01 | FINN, Michael Raymond; McCORMICK, Patrick; MOY, George; NGUYEN, Rene Toan |
A system and method of controlling one or more flaps (102, 108) of an aircraft (106) may include receiving first and second sensor signals from respective first and second sensors (120, 122) coupled to respective first and second actuators (112, 114) that are moveably secured to a first flap (102) of a first wing (104) of the aircraft (106). The first and second sensor signals relate to one or both of the position or the speed of the respective first and second actuators (112, 114). The system and method may also include comparing the first and second sensor signals to determine a difference between the first and second sensor signals, and adjusting the speed of one or both of the first or second actuators (112, 114) based on the difference between the first and second sensor signals. A system and method may include determining a difference between one or both of speed or position of the first and second flaps (102, 108), and adjusting the speed of one or both of the first and second flaps (102, 108) based on the difference between one or both of the speed or the position of the first and second flaps (102, 108).
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