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
41	High-lift device, wing, and noise reduction structure for high-lift device	US13557400	2012-07-25	US09010692B2	2015-04-21	Makoto Hirai; Ichiro Maeda
A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is retracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing.
42	High-lift device, wing, and noise reduction structure for high-lift device	US12526800	2008-05-20	US08469316B2	2013-06-25	Makoto Hirai; Ichiro Maeda
A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is refracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing.
43	High-lift device track	EP09174472.2	2009-10-29	EP2316727B1	2013-06-19	Lauwereys, Guy; Paulis, Frédéric; Ramirez Garcia, Miguel; Ramirez Ramirez, Juan-Carlos; Vandegaer, Stijn; Vandenbulcke, Yvon

44	Front end high lift loading device	US36955464	1964-05-22	US3237792A	1966-03-01	BOEHMER THEODORE M

45	Control system for aircraft high lift devices and method for controlling the configuration of aircraft high lift devices	US14630812	2015-02-25	US09415861B2	2016-08-16	Martin Berens
A control system for an aircraft high lift device includes a threshold setting unit configured to output one of a plurality of configuration change thresholds as an active output threshold, a threshold deactivation unit coupled to the threshold setting unit and configured to temporarily increase the active output threshold to a deactivation value, a configuration setting unit coupled to the threshold deactivation unit and configured to set the aircraft high lift device from a first configuration to a second configuration, if a measured value of an angle-of-attack of the aircraft exceeds the active output threshold, and a threshold control unit configured to control the threshold deactivation unit to temporarily increase the active output threshold to the deactivation value while the aircraft high lift device is mechanically moving from a first configuration to a second configuration.
46	HIGH-LIFT DEVICE FOR AIRCRAFT	EP12764943	2012-03-28	EP2692632A4	2014-12-31	ISOTANI KAZUHIDE; HAYAMA KENJI
A high-lift device (3) of a flight vehicle includes: a flap main body (11) provided at a trailing edge portion of a main wing (2) of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing (2); and a vortex suppressing portion (100, 200, 300, 400, 500, or 600) provided at a tip end portion of the flap main body (11) in a wing span direction of the flap main body (11) and configured to suppress a vortex rolling up from a lower surface of a tip end portion (11a) of the flap main body (11) to an upper surface of the tip end portion (11a).
47	Safety and high lift system and apparatus for aircraft	US16484962	1962-01-08	US3121544A	1964-02-18	ALBERTO ALVAREZ-CALDERON

48	Actuation system for leading edge high-lift device	US12733465	2008-10-27	US08967549B2	2015-03-03	Francois Cathelain; Edmund Kay
An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.
49	HIGH-LIFT DEVICE FOR FLIGHT VEHICLE	EP13768891.7	2013-03-29	EP2832638B1	2018-03-07	ISOTANI, Kazuhide; HAYAMA, Kenji
A high-lift device (3) comprises a flap body (11) which is provided at a rear portion of a main wing (2) which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing (2); and a gap increasing section (20, 30) provided at an end portion (11a) of the flap body (11) in an extending direction of the flap body, to increase a gap between the rear portion of the main wing (2) and a front portion of the flap body (11) in a state in which the flap body is deployed.
50	HIGH-LIFT DEVICE FOR AN AIRCRAFT	EP05740546.6	2005-05-09	EP1755946B1	2017-04-19	WHITEHOUSE, Ian, Roy "Jalna"; KAY, Edmund; DODD, Daniel

51	Retractable infill panel for high-lift device	US14084828	2013-11-20	US09254927B2	2016-02-09	Mark Hodkisson; James Wilson; Samuel Evans
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.
52	HIGH-LIFT DEVICE FOR AIRCRAFT	EP12764943.2	2012-03-28	EP2692632A1	2014-02-05	ISOTANI, Kazuhide; HAYAMA, Kenji
A high-lift device (3) of a flight vehicle includes: a flap main body (11) provided at a trailing edge portion of a main wing (2) of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing (2); and a vortex suppressing portion (100, 200, 300, 400, 500, or 600) provided at a tip end portion of the flap main body (11) in a wing span direction of the flap main body (11) and configured to suppress a vortex rolling up from a lower surface of a tip end portion (11a) of the flap main body (11) to an upper surface of the tip end portion (11a).
53	ACTUATION SYSTEM FOR LEADING EDGE HIGH-LIFT DEVICE	EP08806803.6	2008-10-27	EP2214959A1	2010-08-11	CATHELAIN, Francois; KAY, Edmund
An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.
54	ACTUATION SYSTEM FOR LEADING EDGE HIGH-LIFT DEVICE	EP08806803.6	2008-10-27	EP2214959B1	2011-09-14	CATHELAIN, Francois; KAY, Edmund
An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.
55	Accommodation controlling device of vehicle for high lift work	JP2002129724	2002-05-01	JP2003321198A	2003-11-11	OBA TAKAAKI; KUWAJIMA KAZUO; KUBO ATSUSHI; SASAKI TAKASHI
PROBLEM TO BE SOLVED: To provide an accommodation controlling device capable of adjusting offset when either of a boom and an arm is accommodated in an offset position. SOLUTION: This accommodation controlling device 70 comprises a second actuation controlling valve 71 connecting a post leveling cylinder 31 in series with a hoisting cylinder 25, connected with an actuation interlinking oil path 60 for interlinking and actuating the hoisting cylinder 25 and the post leveling cylinder 31 by oil hydraulic supply from a first actuation controlling valve 66, and capable of controlling the working oil pressure supply independently from the oil pressure supply from the first actuation controlling valve 66 to the post leveling cylinder 31; a boom accommodation sensor 80 detecting the accommodation of the boom; an arm accommodation sensor 81 detecting the accommodation of the arm; and a controller 82 controlling the actuation of the second actuation controlling vale 71 for adjusting the position of the arm relative to the boom when either one of the sensors 80, 81 detects an accommodation condition and the other detects a non-accommodation condition. COPYRIGHT: (C)2004,JPO
56	高所作業車のサブブーム装置	JP2014114490	2014-06-03	JP2015227244A	2015-12-17	田上吉夫; 北條努
【課題】サブブーム部材の支持強度を簡単な構造で確保できる高所作業車のサブブーム装置を提供する。【解決手段】サブブーム装置60において、サブブーム支持部材80は、水平方向に延びる揺動軸部71を中心に旋回部材70に対して垂直面内で揺動可能に設けられた第1支持部材81と、揺動軸部71と直交する方向に延びる回転軸部89を中心に第1支持部材81に対して作業回転位置と格納回転位置との間で相対回転可能に設けられた第2支持部材86とを備え、第1支持部材81に対する第2支持部材86の相対回転位置に応じて、サブブーム部材90を第1支持部材81および第2支持部材86の両方で支持し得る状態と、サブブーム部材90を第2支持部材86のみで支持し得る状態とに選択的に切り替えが可能である。【選択図】図5
57	Sub boom device for vehicle for high lift work	JP2012246591	2012-11-08	JP2014094798A	2014-05-22	HOJO TSUTOMU
PROBLEM TO BE SOLVED: To provide a sub boom device for a vehicle for high lift work which has a simple device configuration and can be stored by an operator's simple operation.SOLUTION: A sub beam device comprises a first sub beam support member 72 which is so attached to a slewing part 71 as to be capable of oscillating around a first oscillation pin 72a extending in a horizontal direction, a second sub beam support member 73 which is so attached to the first sub beam support member 72 as to be capable of oscillating around a second oscillation pin 73a orthogonal to the first oscillation pin 72a. The sub beam device is configured such that the second sub beam support member 73 is oscillated to a position at which the second sub beam support member 73 extends approximately in parallel to the first oscillation pic 72a, and simultaneously, a sub beam member 74 can be set to a storage attitude in which the first sub beam support member 72 is so oscillated as to be positioned to the lateral of a working table 40.
58	Operating mechanism for high lift devices for airplanes	US65016446	1946-02-26	US2502315A	1950-03-28	EARHART HAROLD W

59	ACTUATORS FOR HIGH LIFT DEVICES ON AIRCRAFT	EP17187112.2	2017-08-21	EP3290749A1	2018-03-07	HEIBERG, Christopher J.; McCORMICK, Patrick J.; ATMUR, Robert J.
Actuators for high lift devices on aircraft are disclosed herein. An example apparatus includes an actuator for a high lift device of an aircraft including a motor and a transmission, where the transmission includes a first gear stage and a second gear stage, the first gear stage including a first worm gear and the second gear stage including a second worm gear, the first worm gear, the second worm gear and the motor operative to prevent backdrive of the actuator.
60	Control system for aircraft high lift devices and method for controlling the configuration of aircraft high lift devices	EP14156914.5	2014-02-27	EP2913733A1	2015-09-02	Berens, Martin
The present disclosure pertains to a control system for an aircraft high lift device, the control system including a threshold setting unit configured to output one of a plurality of configuration change thresholds as an active output threshold, a threshold deactivation unit coupled to the threshold setting unit and configured to temporarily increase the active output threshold to a deactivation value, a configuration setting unit coupled to the threshold deactivation unit and configured to set the aircraft high lift device from a first configuration to a second configuration, if a measured value of an angle-of-attack of the aircraft exceeds the active output threshold, and a threshold control unit configured to control the threshold deactivation unit to temporarily increase the active output threshold to the deactivation value while the aircraft high lift device is mechanically moving from a first configuration to a second configuration.

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