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公开(公告)号：US20140231584A1
公开(公告)日：2014-08-21
申请号：US14237598
申请日：2012-08-20
申请人： Dominique Ducos
发明人： Dominique Ducos
IPC分类号： B64C25/00
CPC分类号： B64C25/001 , B64C25/32
摘要： An anti-lofting deflector for landing gear having two wheels on an axle, the deflector comprising:a stationary support (5) for being fastened in service to a portion of the landing gear that carries the axle in order to extend between the wheels and present a distal end behind the wheels;a first flap (2) hinged to the support via its distal end about a first hinge axis (X1) substantially parallel to the axle;a second flap (3) hinged to the first flap about a second hinge axis (X2) substantially parallel to the first hinge axis; anda return member (11) arranged so as to urge the second flap against an abutment of the first flap that prevents the second flap from becoming aligned with the first flap, and to urge the first flap against an abutment of the stationary support that prevents the first flap from folding against the support.
摘要翻译： 一种用于在轴上具有两个轮子的起落架的防放卷偏转器，所述偏转器包括：固定支撑件（5），用于固定在起落架的一部分上，所述起落架承载所述轴，以便在所述车轮之间延伸并且呈现 轮后的远端; 围绕基本上平行于所述车轴的第一铰链轴线（X1）经由其远端铰接到所述支撑件的第一翼片（2） 围绕基本上平行于第一铰链轴线的第二铰链轴线（X2）铰接到第一挡板的第二挡板（3）; 以及返回构件（11），其布置成将所述第二挡板推压抵靠所述第一挡板的邻接部，所述第二挡板防止所述第二挡板与所述第一挡板对准，并且将所述第一挡板推压抵靠所述静止支撑件的抵接件， 第一个襟翼折叠在支撑上。
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公开(公告)号：US08602352B2
公开(公告)日：2013-12-10
申请号：US13376160
申请日：2010-06-03
摘要： A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.
摘要翻译： 一种在展开位置和缩回位置之间操作飞机起落架的方法。 起落架包括铰接到飞行器的腿部，腿部由包括两个铰接在一起的连杆的折叠支柱稳定在展开位置，该支柱由稳定器构件保持在对准位置，稳定器构件包括两个铰接在一起的链节， 通过锁定构件对齐。 该方法包括以下步骤：将支柱（2; 102）和稳定器构件（4; 104）布置成使得稳定器构件的至少一个连杆（4a; 104a）在移动过程中连续地移动 从展开位置到缩回位置，并且将操作致动器（10; 110）连接到连杆上，以便使连杆枢转抵靠锁定件并在其上施加倾向于移动腿部的力。
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3.发明申请公开(公告)号：US20130020436A1
公开(公告)日：2013-01-24
申请号：US13522782
申请日：2011-01-19
IPC分类号： B64C25/12
CPC分类号： B64C25/12 , B64C2025/125
摘要： The invention relates to an aircraft landing gear of deformable-parallelogram type, including: a leg including a casing (1) having a lower end on which a rocker arm (3) carrying at least one wheel is hinged by means of a pivot (2), a shock absorber (5) being connected between the rocker arm and the casing; two panels (10, 11) each hinged on the one hand on the structure of the aircraft and on the other hand on the leg, about parallel axes; According to the invention, one of the panels (11) is hinged on the leg whilst being connected to the casing by a pin on one end of the pivot (2) of the rocker arm.
摘要翻译： 本发明涉及一种可变形 - 平行四边形类型的飞机起落架，包括：腿部，其包括具有下端的壳体（1），通过枢轴（2）铰接至少一个轮的摇臂（3） ），在所述摇臂和所述壳体之间连接的减震器（5） 两个面板（10,11）一方面铰接在飞行器的结构上，另一方面在腿上围绕平行的轴线铰接; 根据本发明，一个面板（11）铰接在腿上，同时通过在摇臂的枢轴（2）的一端上的销连接到壳体。
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4.发明授权Device for unlocking an undercarriage in a deployed position, and an undercarriage fitted with such a device 有权用于在展开位置解锁底架的装置和装有这种装置的起落架公开(公告)号：US09145204B2
公开(公告)日：2015-09-29
申请号：US13697841
申请日：2011-05-17
申请人： Dominique Ducos
发明人： Dominique Ducos
摘要： A simple device for blocking and unblocking the locking member of an undercarriage having a breaker strut and including an unlocking device. The device comprises a rotary actuator of axis parallel to the hinge axis of the links of the stabilizing member; a crank connected to a shaft of the actuator; a pawl hinged to the end of the crank and including a step; a pin secured to and at a distance from one of the links of the stabilizing member; and return means for urging the pawl towards the pin. The actuator is actuatable between a first angular position in which the pin is in contact with the pawl facing the step while the links are substantially in alignment, and a second angular position that the crank reaches when the step of the pawl has pushed back the pin, taking the links of the stabilizer member out of alignment.
摘要翻译： 一种简单的装置，用于阻挡和解锁具有断路器支柱并包括解锁装置的起落架的锁定构件。 该装置包括：平行于稳定构件的连杆的铰链轴线的旋转致动器; 连接到致动器的轴的曲柄; 棘爪铰接到曲柄的端部并包括一个台阶; 固定在所述稳定构件的所述连杆中的一个上并与其一定距离的销; 以及用于向销推动棘爪的返回装置。 致动器可以在第一角位置和第二角位置之间起第一角度位置，在第一角度位置，销与第二角度位置相对，当第二角度位置与棘爪相接触时， 使稳定器的连杆不对齐。
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5.发明授权Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner 有权飞机的主起落架，包括以铰接方式连接到飞行器结构的两个步进梁公开(公告)号：US09073629B2
公开(公告)日：2015-07-07
申请号：US13699911
申请日：2011-06-16
申请人： Dominique Ducos
发明人： Dominique Ducos
CPC分类号： B64C25/10 , B64C25/14 , B64C25/34 , B64C2025/125
摘要： An aircraft undercarriage comprising two rocker beams (1, 2) carrying wheels and mounted to pivot on a common pivot (Y1), the undercarriage including a shock-absorber device comprising two connecting rods (5, 6), each rod (5, 6) being coupled to a respective rocker beam, at least one connecting rod being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocker (7) pivotally mounted on a central pivot (8), wherein the common pivot of the rocker beams is secured to a structure of an aircraft to which the undercarriage is fastened and is mounted in a fixed position on the structure. The central pivot of the rocker is movable between a first position (rocker beams in a landing position) and a second position in which a rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position of the undercarriage.
摘要翻译： 一种飞机起落架，包括两个承载轮并且安装成在公共枢轴（Y1）上枢转的摇臂梁（1,2），起落架包括一个包括两个连接杆（5,6）的减振装置，每个杆（5,6） ）联接到相应的摇臂，至少一个连杆被伸缩并形成减震器。 两个连杆还联接到枢转地安装在中心枢轴（8）上的摇臂（7），其中摇臂梁的公共枢轴固定到飞机的结构，起落架被固定到该飞机上，并安装在 固定位置在结构上。 摇杆的中心枢轴可以在第一位置（在着陆位置的摇杆梁）和第二位置之间移动，在第二位置中摇杆已经在连接杆上拉动，以使摇臂梁朝向起落架的缩回位置枢转。
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公开(公告)号：US20120080559A1
公开(公告)日：2012-04-05
申请号：US13376160
申请日：2010-06-03
IPC分类号： B64C25/26
摘要： A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.
摘要翻译： 一种在展开位置和缩回位置之间操作飞机起落架的方法。 起落架包括铰接到飞行器的腿部，腿部由包括两个铰接在一起的连杆的折叠支柱稳定在展开位置，该支柱由稳定器构件保持在对准位置，稳定器构件包括两个铰接在一起的链节， 通过锁定构件对齐。 该方法包括以下步骤：将支柱（2; 102）和稳定器构件（4; 104）布置成使得稳定器构件的至少一个连杆（4a; 104a）在移动过程中连续地移动 从展开位置到缩回位置，并且将操作致动器（10; 110）连接到连杆上，以便使连杆枢转抵靠锁定件并在其上施加倾向于移动腿部的力。
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公开(公告)号：US06786451B2
公开(公告)日：2004-09-07
申请号：US10360638
申请日：2003-02-10
申请人： Maud Courtois , Dominique Ducos
发明人： Maud Courtois , Dominique Ducos
IPC分类号： B64C2516
CPC分类号： B64C25/16 , B64C7/00 , B64C2025/003
摘要： The invention relates to an aircraft landing gear having a retractable leg, in which the leg comprises a strut with a telescopic rod, the strut being hinged to a structure of the aircraft in order to pivot between a gear-up position and a gear-down position, said strut also being connected to the structure of the aircraft via hinged brace elements. According to an essential aspect of the invention, the landing gear includes an independent low-noise fairing system that serves, when the leg is in the gear-down position, to cover the front of at least a portion of the hinge between the brace elements, said low-noise fairing system comprising a hinged fairing of two complementary portions connected to each other via a hinge whose axis is parallel to the axis of the corresponding hinge portion of said brace elements.
摘要翻译： 本发明涉及一种具有可伸缩腿部的飞机起落架，其中腿部包括具有伸缩杆的支柱，该支柱铰接到飞行器的结构上，以便在起落位置和减档之间枢转 所述支柱还通过铰链支架元件连接到飞行器的结构。 根据本发明的一个重要方面，起落架包括一个独立的低噪声整流装置系统，当腿部处于减速位置时，其用于覆盖支架元件之间铰链的至少一部分的前部 所述低噪声整流罩系统包括通过铰链彼此连接的两个互补部分的铰接整流罩，所述铰链的轴线平行于所述支撑元件的相应铰链部分的轴线。
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8.发明授权Landing gear strut damper, and landing gear with independent struts comprising same 失效起落架支柱阻尼器和具有独立支柱的起落架组成公开(公告)号：US07426983B2
公开(公告)日：2008-09-23
申请号：US10541948
申请日：2003-12-29
CPC分类号： B64C25/58 , B64C25/60 , B64C2025/008 , B64C2025/125
摘要： A damper for an airplane landing gear leg comprises a main strut (11) and a rod piston (13) co-operating with the strut (11) to define a main chamber (15) and annular chamber (16) for hydraulic fluid, and presenting internally two adjacent chambers (19, 20) that are isolated from each other by a separator piston (21). The damper (10) further comprises a first secondary strut (26) telescopically Slidable on the above-mentioned rod piston (13), and a second secondary strut (37) telescopically slidable on the other end of the first secondary strut (26). The two second annular chambers (31, 40) as defined in this way are respectively connected to associated control circuits thus enabling the total length of the damper to be shortened or lengthened respectively for the purpose of causing the landing gear to contract or to be extended.
摘要翻译： 用于飞机起落架的减震器包括与支柱（11）配合的主支柱（11）和杆活塞（13），以限定用于液压流体的主室（15）和环形室（16），以及 在内部呈现通过分离器活塞（21）彼此隔离的两个相邻的室（19,20）。 阻尼器（10）还包括在上述杆式活塞（13）上可伸缩地滑动的第一辅助支柱（26）和在第一辅助支柱（26）的另一端可伸缩滑动的第二辅助支柱（37）。 以这种方式定义的两个第二环形腔室（31,40）分别连接到相关联的控制回路，从而能够使阻尼器的总长度分别缩短或延长，以使起落架收缩或延伸 。
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9.发明申请公开(公告)号：US20060163427A1
公开(公告)日：2006-07-27
申请号：US10541948
申请日：2003-12-29
申请人： Dominique Ducos , Ian Bennett , David Smart
发明人： Dominique Ducos , Ian Bennett , David Smart
IPC分类号： B64C25/58
CPC分类号： B64C25/58 , B64C25/60 , B64C2025/008 , B64C2025/125
摘要： A damper for an airplane landing gear leg comprises a main strut (11) and a rod piston (13) co-operating with the strut (11) to define a main chamber (15) and annular chamber (16) for hydraulic fluid, and presenting internally two adjacent chambers (19, 20) that are isolated from each other by a separator piston (21). The damper (10) further comprises a first secondary strut (26) telescopically slidable on the above-mentioned rod piston (13), and a second secondary strut (37) telescopically slidable on the other end of the first secondary strut (26). The two second annular chambers (31, 40) as defined in this way are respectively connected to associated control circuits thus enabling the total length of the damper to be shortened or lengthened respectively for the purpose of causing the landing gear to contract or to be extended.
摘要翻译： 用于飞机起落架的减震器包括与支柱（11）配合的主支柱（11）和杆活塞（13），以限定用于液压流体的主室（15）和环形室（16），以及 在内部呈现通过分离器活塞（21）彼此隔离的两个相邻的室（19,20）。 阻尼器（10）还包括可在上述杆式活塞（13）上可伸缩滑动的第一辅助支柱（26）和在第一辅助支柱（26）的另一端可伸缩滑动的第二辅助支柱（37）。 以这种方式定义的两个第二环形腔室（31,40）分别连接到相关联的控制回路，从而能够使阻尼器的总长度分别缩短或延长，以使起落架收缩或延伸 。
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公开(公告)号：US20050011991A1
公开(公告)日：2005-01-20
申请号：US10880466
申请日：2004-07-01
CPC分类号： B64C25/10 , B64C25/001 , B64C25/34 , B64C25/58 , B64C2025/008 , B64C2025/125
摘要： The invention relates to retractable landing gear for an aircraft, the landing gear being of the type that is raised vertically, and comprising a plurality of independent legs, each leg comprising a structural part rigidly secured to a structure of the aircraft, a pivoting rocker beam supporting a pair of wheels, and a shock absorber. In accordance with the invention, the shock absorber of each leg is extended by a positioning portion enabling the total length of the extended shock absorber to be shortened in order to collapse said leg, and each leg further comprises a positioning actuator connected in hinged manner to the extended shock absorber and arranged to lengthen relative to a normal use position in order to lengthen the corresponding leg. This makes it possible to shorten and/or lengthen one or another of the legs of the landing gear while the aircraft is stationary or taxiing slowly.
摘要翻译： 本发明涉及一种用于飞行器的可伸缩起落架，起落架是垂直升降的类型，并且包括多个独立的支腿，每个支腿包括刚性地固定到飞行器结构的结构部件，枢转摇臂梁 支撑一对轮子和减震器。 根据本发明，每个支腿的减震器通过定位部分延伸，使得能够缩短延伸的减震器的总长度，以便使所述腿部折叠，并且每个腿部还包括定位致动器，其以铰接方式连接到 延伸的减震器并且被布置成相对于正常使用位置延长，以便延长相应的腿部。 这使得可以在飞行器静止或滑行缓慢的情况下缩短和/或延长起落架的一个或多个腿部。
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