高升力装置相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
61	Stress detection device for vehicle for high lift work	JP2002376117	2002-12-26	JP2004203574A	2004-07-22	MOROTA TAKASHI; NAKAZAWA SHUNICHI
PROBLEM TO BE SOLVED: To provide a stress detection device for a vehicle for high lift work capable of improving precision in determining fatigue. SOLUTION: A stress detection device 60 is taken into a boom operation controller 40 controlling operation of boom actuators 15, 21, 23. The stress detection device 60 is provided with a strain gage 61 attached to a basic part of a turn base and an elapse time signal generation circuit 69 outputting an elapse time signal at a predetermined interval from the time of drive of at least any of running operation of the vehicle and boom operation to receive the elapse time signal from the elapse time signal generation circuit 69. The stress detection device 60 has a stress value taking-in circuit 73 taking in a stress value calculated by a stress computing circuit 71 in accordance with a detected value from the strain gage 61 when receiving the elapse time signal and a memory 75 storing a work base position calculated by a position calculation circuit 49 in accordance with the elapse time signal, a stress value taken in by the stress value taking-in circuit 73, and a detected value from a work base position sensor 41 by letting it correspond to the elapse time signal. COPYRIGHT: (C)2004,JPO&NCIPI
62	Retractable infill panel for high-lift device	EP13193183.4	2013-11-15	EP2733062A3	2018-01-31	Hodkisson, Mark; Wilson, James; Evans, Samuel
The present invention provides an aircraft assembly with a fixed structure and a high-lift device. The fixed structure has a spar, a forward part which provides a foremost edge of an aircraft wing, and a lower part which provides a lower surface of the aircraft wing. A high-lift device is downwardly movable relative to the fixed structure from a stowed configuration to a deployed configuration. The high-lift device has a forward part which provides a foremost edge of the aircraft wing and a lower part which provides a lower surface of the aircraft wing. Downward movement of the high-lift device causes progressive opening of a lateral gap between the lower part of the high-lift device and the lower part of the fixed structure. A retractable infill panel is arranged to progressively extend from a retracted configuration to an extended configuration to fill the lateral gap.
63	Skew and loss detection system for adjacent high lift devices	US441555	1995-05-15	US5680124A	1997-10-21	Jeffrey C. Bedell; Wayne M. Berta
This invention is a method and apparatus for determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew.
64	Boundary layer control means for obtaining high lift for aircraft	US72986458	1958-04-21	US2951662A	1960-09-06	THEODORE THEODORSEN

65	Skew and loss detection system for individual high lift devices	US442208	1995-05-15	US5686907A	1997-11-11	Jeffrey C. Bedell; Wayne M. Berta
This invention is a method and apparatus for determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew.
66	航空機用高揚力装置と共に使用するためのトルク管組立体	JP2016085946	2016-04-22	JP2017030725A	2017-02-09	ダグラス・ジョン・シュワルツ; マーク・ロバート・マイヤー
【課題】航空機用高揚力装置と共に使用するためのトルク管組立体を提供する。【解決手段】航空機用高揚力装置と共に使用するための例示的なトルク管組立体が、本明細書に記載されている。例示的な装置は、第1のヨークを有するスプライン結合器と、第2のヨークを有する摺動スプラインシャフトと、第1の端部および該第1の端部の反対側の第2の端部を有するトルクチューブとを含む。第3のヨークを有する第1の取付具は、トルクチューブの第1の端部に結合され、第4のヨークを有する第2の取付具は、トルクチューブの第2の端部に結合される。第3のヨークは、第1のU継手を形成するために第1のヨークに結合され、第4のヨークは、第2のU継手を形成するために第2のヨークに結合される。スプライン結合器は、第1の高揚力装置駆動シャフトに結合されるようになっており、摺動スプラインシャフトは、第2の高揚力装置駆動シャフトに結合されるようになっている。【選択図】図3
67	High-lift device track having a U-shaped to H-shaped cross-section	US12914545	2010-10-28	US08628045B2	2014-01-14	Guy Lauwereys; Frédéric Paulis; Miguel Ramirez Garcia; Juan-Carlos Ramirez Ramirez; Stijn Vandegaer; Yvon Vandenbulcke
A high-lift device track 5 comprising a first track end 6 comprising attachment points for the high-lift device 4, two vertical flanges 16 connected by a horizontal web 17, a set of raceways 10,11,12 for guiding rollers 13 or glide pads, and a gear rack 7 installed between said flanges 16 over a first track segment 18. This first track segment 18 presents an inverted-U, or cross-section. However, between said first track segment 18 and a second track end 20 opposite to said first track end 6, the track 5 comprises a second track segment 21 presenting a depth d between the horizontal web 17 and lower edges 25 of the vertical flanges 16 which decreases towards said second track end 20, so that, at said second track end, the track presents an H cross-section. FIG. 4.
68	Systems and methods for providing differential motion to wing high lift device	US12352447	2009-01-12	US07726610B2	2010-06-01	Mark S. Good; Paul M. Vijgen; Seth E. Gitnes; Glynn Michael Thomas
Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together. In a second configuration, the drive link is operatively coupled to at least the first deployable lift device and operatively decoupled from the second deployable lift device, so that actuation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.
69	High-lift device, wing, and noise reduction structure for high-lift device	EP12178247.8	2008-05-20	EP2520488B1	2013-12-18	Hirai, Makoto; Maeda, Ichiro
The present invention provides a high-lift device (3), a wing (1), and a noise reduction structure for high-lift devices capable of suppressing the occurrence of aerodynamic noise while restricting an increase in airframe weight. A high-lift device (3) comprises a slat main body (4) that is disposed so as to be able to extend from and retract into a main wing (2), a concave part (5) that is formed on the slat main body (4) at a location that faces the main wing (2), so as to be able to accommodate at least a part of a leading edge of the main wing (2), and a lower-surface plate (7) that is a plate-like member extending toward the main wing (2) from an edge line at which the lower surface of the slat main body (4) and the concave part (5) meet, and whose angle with respect to the central axis can be deflected, wherein at the trailing edge of the lower-surface plate (7), serrations are provided along the longitudinal direction of the lower-surface plate (7).
70	Vorrichtung zur Erfassung von Gleichlauffehlern von Hochauftriebsflächen an Flugzeugen	EP05020261.3	2005-09-16	EP1637453B1	2011-07-06	Schievelbusch, Bernd

71	Systems and methods for providing differential motion to wing high lift devices	US10935846	2004-09-08	US20060049308A1	2006-03-09	Mark Good; Paul Viigen; Seth Gitnes; Glynn Thomas
Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together. In a second configuration, the drive link is operatively coupled to at least the first deployable lift device and operatively decoupled from the second deployable lift device, so that actuation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.
72	Mechanism for supporting and extending a high lift device for aircraft wings	US193786	1988-05-13	US4838503A	1989-06-13	George H. Williams
A mechanism for supporting and extending a high lift device relative to an aerofoil, comprises one or more support beams (10) connected to the aerofoil, a pair of spaced apart chordwise extending wing ribs (20) bounding the support beam, a set of cylindrical rollers (23) mounted between the wing ribs for supporting the support beam (10) with their rotational axes aligned transversely with respect to the support beam (10), the support beam (10) including a gear rack (12) with gear teeth facing downwardly and a pinion gear (13) lying in meshing engagement with the gear rack (12), and an actuator (14) in driving engagement with the pinion gear (13) to extend and retract the high lift device (2-6) relative to the aerofoil (1). Bearings (45, 47) are provided for rotatably supporting the pinion gear (13) between the wing ribs (20) about a generally transverse axis of rotation, and there are splined engaging means (42, 43) between the actuator (14) and the pinion gear (13).
73	Vorrichtung zur Erfassung von Gleichlauffehlern von Hochauftriebsflächen an Flugzeugen	EP05020261.3	2005-09-16	EP1637453A3	2008-06-25	Schievelbusch, Bernd
Die vorliegende Erfindung betrifft eine Vorrichtung zur Erfassung von Gleichlauffehlern von Hochauftriebsflächen (2) wie Landeklappen oder Vorflügeln an Flugzeugen, mit einem optischen Leiter, der über zumindest zwei nebeneinander angeordnete Hochauftriebsflächen (2) hinweg verlegt ist, einer Lichtquelle (6) und einem Lichtempfänger (7), die verschiedenen Enden des optischen Leiters zugeordnet sind, sowie einer Auswerteeinheit zur Bestimmung eines Gleichlauffehlers der Hochauftriebsflächen (2) anhand des vom Lichtempfänger (7) empfangenen Lichtsignals. Erfindungsgemäß zeichnet sich die Vorrichtung dadurch aus, dass der optische Leiter derart verlegt ist, dass der optische Leiter durch Gleichlauffehler eine bruchfreie Verformung erfährt und demzufolge eine Veränderung übertragener Lichtsignale bewirkt, und dass die Auswerteeinheit die Signalform des vom Lichtempfänger (7) empfangenen Lichtsignals bzw. eines daraus abgeleiteten Lichtempfängerausgabesignals mit einer Soll-Signalform vergleicht und das Vorliegen eines Gleichlauffehlers anhand der Formabweichung zwischen dem empfangenen Lichtsignal bzw. dem daraus abgeleiteten Lichtempfängerausgabesignal und dem Soll-Signal bestimmt.
74	Method for controlling a high-lift device or a flight control surface, system and aircraft or spacecraft	US13707033	2012-12-06	US08903569B2	2014-12-02	Ina Ruckes; Marc Fervel; Tobias Sebastian Rumpf
The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft.
75	METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT	PCT/EP2006011867	2006-12-08	WO2007068413A3	2007-08-02	FLEDDERMANN ANDREAS; HARTWIG WOLFGANG; DARBOIS ALEXANDRE; RICHTER MARTIN
Described are a method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device (31, 32, 35) at least one high lift surface (11, 12, 21), which is actuated by means of a local mechanical final control element (16, 26), is brought to a predetermined position by a central drive unit (13, 23) that is connected by way of a rotary shaft arrangement (15, 25) to the local final control element (16, 26) by means of generating a torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25). According to the invention, if a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25) is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.
76	Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft	US12086467	2006-12-08	US08256718B2	2012-09-04	Andreas Fleddermann; Wolfgang Hartwig; Alexandre Darbois; Martin Richter
A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.
77	Method and system for controlling a high-lift device or a flight control surface, and air- or spacecraft comprising such system	EP11193054.1	2011-12-12	EP2604515B1	2017-11-08	Rumpf, Tobias Sebastian; Fervel, Marc; Ruckes, Ina

78	Method and system for controlling a high-lift device or a flight control surface, and air- or spacecraft comprising such system	EP11193054.1	2011-12-12	EP2604515A1	2013-06-19	Rumpf, Tobias Sebastian; Fervel, Marc; Ruckes, Ina
The present invention discloses a method for controlling a high-lift device or a flight control surface of an air- or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an air- or spacecraft.
79	机翼组件、机翼及飞行器	CN202310996253.8	2023-08-09	CN117585145A	2024-02-23	弗洛里安·洛伦茨
本发明涉及机翼组件、机翼及飞行器。机翼组件包括：固定机翼部分；第一高升力装置；第一连接组件，其将第一高升力装置以可移动的方式连接至固定机翼部分，使得第一高升力装置能够在缩回位置与至少一个伸出位置之间移动；第二高升力装置；第二连接组件，其将第二高升力装置以可移动的方式连接至第一高升力装置，使得第二高升力装置能够在缩回位置与至少一个伸出位置之间移动；驱动单元，其附接至固定机翼部分；以及驱动组件，其包括附接至驱动单元的第一部分和与第二高升力装置的一部分附接的第二部分，并且其中，驱动单元适于通过驱动组件来驱动第二高升力装置从缩回位置移动至至少一个伸出位置以及从至少一个伸出位置移动至缩回位置。
80	一种飞机增升装置控制方法	CN201310196160.3	2013-05-23	CN103287574A	2013-09-11	朱妍; 安刚
本发明属于航空飞行控制领域，特别是涉及到一种飞机增升装置控制方法。本发明在传统简单的高升力装置控制方法基础上，增加高升力装置偏角与当前飞机飞行速度匹配性的检测，避免出现不正确的高升力装置偏角。本发明不仅可使飞行员在负担较大的起降阶段，无忧虑地对高升力装置进行操纵。即使出现误操作，也可及时对飞行员的操作进行自动纠正，减轻飞行员飞行负担，提高飞行性能，避免飞机出现危机飞行安全的情况。本发明不需要对任何飞机操纵机构或高升力装置进行改造，可直接在高升力装置控制器中增加该算法，节约改造成本、缩短研发周期。

1 2 3 4 5 6 7 8 9 10

IPRDB

热门服务

关于我们

友情链接

联系方式