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公开(公告)号：US20160144944A1
公开(公告)日：2016-05-26
申请号：US14900973
申请日：2014-07-11
Applicant: William A. GOINGS , Eric LONG , LEARJET INC. , C&D ZODIAC INC.
Inventor： William A. GOINGS , Eric LONG
CPC classification number: B64C1/14 , B64D11/0023 , B64D11/02 , E05F11/54 , E05Y2900/502
Abstract: A door for an aircraft includes a first panel divisible into at least two first slats that are releasably connected to one another, a first tensioning cable attached between the at least two first slats, and a first tensioner connected to the first tensioning cable and being operative to apply a first tension thereto, thereby permitting the first tensioning cable to hold the at least two first slats together to form the first panel and to release the first tension in the first tensioning cable upon occurrence of a release action, thereby permitting the at least two first slats to dissociate from one another so that the first panel fragments.
Abstract translation: 一种用于飞行器的门包括可分成至少两个彼此可释放地连接的第一板条的第一板，连接在所述至少两个第一板条之间的第一张紧绳索，以及连接到所述第一张紧绳索并且被操作的第一张紧器 以向其施加第一张力，从而允许第一张紧缆索将至少两个第一板条保持在一起以形成第一板，并且在出现释放动作时释放第一张紧缆索中的第一张力，从而允许至少 两个第一个板条彼此离解，使第一个面板碎片。
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公开(公告)号：US20150307208A1
公开(公告)日：2015-10-29
申请号：US14441413
申请日：2013-11-14
Applicant: LEARJET INC.
Inventor： Harris K. BUTLER, III , Kris RUSTMAN
CPC classification number: B64D47/08 , B64C1/1407 , B64D45/00 , G02B6/06 , G02B23/08 , H04N7/183 , H04N7/186
Abstract: A viewing device for an aircraft includes an image receiver adapted to receive an image of a predetermined spatial area of an exterior of an aircraft, an image projector adapted to display the image of the predetermined spatial area, and an image conduit connecting the image receiver to the image projector. The image receiver is adapted to be positioned on an exterior side of the aircraft below a lateral width of a fuselage of the aircraft while the image projector is adapted to be positioned on an interior side of the aircraft above the lateral width of the fuselage of the aircraft. The image projector is adapted to be positioned at a first predetermined height above a floor on the interior side of the aircraft, consistent with a person's eye level. The image projector is separated from the image receiver by a first predetermined distance.
Abstract translation: 一种用于飞行器的观察装置，包括适于接收飞机外部预定空间区域的图像的图像接收器，适于显示预定空间区域的图像的图像投影仪，以及将图像接收器连接到 图像投影机。 图像接收器适于被定位在飞行器的外侧，在飞机的机身的横向宽度之下，同时图像投影仪适于被定位在飞行器的内侧，高于机身的机身的横向宽度 飞机。 图像投影仪适于被定位在飞行器内侧上的地板上方的第一预定高度，与人的眼睛水平一致。 图像投影仪与图像接收器分离第一预定距离。
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公开(公告)号：CA2918779C
公开(公告)日：2021-03-16
申请号：CA2918779
申请日：2014-07-21
Applicant: LEARJET INC
Inventor： CHANDRASEKHARAN REUBEN , AKEL IYAD , IAROCCI NICK , VAFA SHERMINEH
IPC: B64C5/02
Abstract: Tailplanes (24) and empennages (16) for aircraft (10) are disclosed. An exemplary tailplane (24) disclosed includes a stabilizer (30) having a fixed shape and an elevator (32) movably secured to the stabilizer (30). The elevator (32) is movable from a neutral position relative to the stabilizer (30). The stabilizer (32) and the elevator (32) define an airfoil cross-sectional shape (38) having a positive camber when the elevator (32) is in the neutral position. The positive camber of the airfoil cross-sectional shape (38) may facilitate movement of the elevator (32) during some flight conditions. Also disclosed are tailplanes (24) having camber distributions that vary along the spans of the tailplanes (24).
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公开(公告)号：CA2918779A1
公开(公告)日：2015-04-16
申请号：CA2918779
申请日：2014-07-21
Applicant: LEARJET INC
Inventor： CHANDRASEKHARAN REUBEN , AKEL IYAD , IAROCCI NICK , VAFA SHERMINEH
IPC: B64C5/02
Abstract: Tailplanes (24) and empennages (16) for aircraft (10) are disclosed. An exemplary tailplane (24) disclosed includes a stabilizer (30) having a fixed shape and an elevator (32) movably secured to the stabilizer (30). The elevator (32) is movable from a neutral position relative to the stabilizer (30). The stabilizer (32) and the elevator (32) define an airfoil cross-sectional shape (38) having a positive camber when the elevator (32) is in the neutral position. The positive camber of the airfoil cross-sectional shape (38) may facilitate movement of the elevator (32) during some flight conditions. Also disclosed are tailplanes (24) having camber distributions that vary along the spans of the tailplanes (24).
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公开(公告)号：CA2788948C
公开(公告)日：2019-03-26
申请号：CA2788948
申请日：2010-07-13
Applicant: LEARJET INC , SHORT BROTHERS PLC
Inventor： LANDRY ALAIN , BELANGER GERMAIN
Abstract: A system and method for fabricating a composite material assembly. The components of the assembly originate from more than one mold while providing curing or solidifying under heat and vacuum in one step only, preferably with a composite material in a pre-preg form which does not require autoclave treatment. A removable insert is removed from a second mold prior to assembly of a first mold to the second mold. A section of a laminate extending over the removable insert overlaps over an adjacent laminate after closing and assembly of the first mold onto the second mold.
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Patent Agency Ranking
公开(公告)号：CA2836641A1
公开(公告)日：2012-11-22
申请号：CA2836641
申请日：2011-05-19
Applicant: LEARJET INC
Inventor： BUTLER HARRIS
IPC: B64C13/30
Abstract: A cable support apparatus for an aircraft cable control system comprises at least one cable support unit (20). The cable support unit comprises a pulley (21) adapted to carry a cable (11) of the aircraft cable control system; a support link (22) with a first joint (23) between the pulley and the support link and a second joint (24) between the support link and the structure (10) of the aircraft; a compensation link (30) connected with the structure of the aircraft. The a thermal expansion of the compensation link causes a displacement of the support link. An aircraft and a method for maintaining a tension of a cable of a cable control system of an aircraft are also provided.
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公开(公告)号：CA2836641C
公开(公告)日：2017-10-24
申请号：CA2836641
申请日：2011-05-19
Applicant: LEARJET INC
Inventor： BUTLER HARRIS
IPC: B64C13/30
Abstract: A cable support apparatus for an aircraft cable control system comprises at least one cable support unit (20). The cable support unit comprises a pulley (21) adapted to carry a cable (11) of the aircraft cable control system; a support link (22) with a first joint (23) between the pulley and the support link and a second joint (24) between the support link and the structure (10) of the aircraft; a compensation link (30) connected with the structure of the aircraft. The a thermal expansion of the compensation link causes a displacement of the support link. An aircraft and a method for maintaining a tension of a cable of a cable control system of an aircraft are also provided.
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公开(公告)号：CA2917564A1
公开(公告)日：2015-01-15
申请号：CA2917564
申请日：2014-07-11
Applicant: LEARJET INC , C & D ZODIAC INC
Inventor： GOINGS WILLIAM A , LONG ERIC
Abstract: A door for an aircraft includes a first panel (58) divisible into at least two first slats (64-70) that are releasable connected to one another, a first tensioning cable (100) attached between the at least two first slats, and a first tensioner (124) connected to the first tensioning cable and being operative to apply a first tension thereto, thereby permitting the first tensioning cable to hold the at least two first slats together to form the first panel and to release the first tension in the first tensioning cable upon occurrence of a release action, thereby permitting the at least two first slats to dissociate from one another so that the first panel fragments.
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公开(公告)号：CA2917564C
公开(公告)日：2021-07-20
申请号：CA2917564
申请日：2014-07-11
Applicant: LEARJET INC , C&D ZODIAC INC
Inventor： GOINGS WILLIAM A , LONG ERIC
Abstract: A door for an aircraft includes a first panel (58) divisible into at least two first slats (64-70) that are releasable connected to one another, a first tensioning cable (100) attached between the at least two first slats, and a first tensioner (124) connected to the first tensioning cable and being operative to apply a first tension thereto, thereby permitting the first tensioning cable to hold the at least two first slats together to form the first panel and to release the first tension in the first tensioning cable upon occurrence of a release action, thereby permitting the at least two first slats to dissociate from one another so that the first panel fragments.
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公开(公告)号：CA2841447C
公开(公告)日：2019-01-15
申请号：CA2841447
申请日：2011-07-26
Applicant: LEARJET INC
Inventor： BUTLER HARRIS , VELETAS MIHALIS , HAWKINS JAMES D
IPC: B64C13/24
Abstract: A bias gain system (10) for aircraft rudder comprises a pair of connector ends (21) receiving an actuation force from a bias actuator (12). A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar (11) as a function of the actuation forces from the bias actuators. A mechanism comprising links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.
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