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公开(公告)号：US4907761A
公开(公告)日：1990-03-13
申请号：US285600
申请日：1988-12-16
摘要： A control mechanism according to the invention comprises a crank (13) constrained to rotate with the catapult bar (10), a catapult bar linkage comprising a link (14) and a lever (16) which are hinged to each other, and having a first end hinged to the crank (13) at a point distant from the pivot pin of the catapult bar, and a second end hinged about a pin (17) carried by the landing gear and distant from the pivot pin (11) of the catapult bar (10), and control means (18) for controlling the relative disposition of the link and the lever.
摘要翻译： 根据本发明的控制机构包括被限制为与弹射杆（10）一起旋转的曲柄（13），弹射杆连杆，包括彼此铰接的连杆（14）和杆（16），并且具有 第一端在远离弹射杆的枢轴的点处铰接到曲柄（13），并且第二端铰接在由起落架承载并远离弹射器的枢轴销（11）的销（17） 杆（10）和用于控制连杆和杆的相对布置的控制装置（18）。
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12.发明授权公开(公告)号：US08800920B2
公开(公告)日：2014-08-12
申请号：US13522782
申请日：2011-01-19
IPC分类号： B64C25/10
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 while 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）通过在摇臂的枢轴（2）的一端上的销连接到壳体上而铰接在腿上。
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13.发明申请DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT 有权用于联接执行机构以控制飞机的起落架的装置公开(公告)号：US20140209738A1
公开(公告)日：2014-07-31
申请号：US14238534
申请日：2012-09-07
IPC分类号： B64C25/20
摘要： A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.
摘要翻译： 一种用于将用于操作飞行器起落架的致动器联接到飞机结构的装置。 该装置包括杠杆，其具有用于铰接到飞行器的结构的第一端和致动器铰接的第二端，作用在杠杆上的预加载结构，以将其推向稳定的休止位置，该静止位置由 没有任何力通过致动器的杠杆; 以及当所述致动器被致动时限定所述杠杆的至少一个工作位置的邻接结构。
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公开(公告)号：US08495810B2
公开(公告)日：2013-07-30
申请号：US12810751
申请日：2008-12-24
申请人： Richard Masson , Dominique Ducos
发明人： Richard Masson , Dominique Ducos
CPC分类号： C22C47/00 , C22C47/04 , C22C47/064 , Y10T29/49 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , Y10T29/49801 , Y10T29/49885 , Y10T29/49968 , Y10T29/4998 , Y10T29/49984 , Y10T29/49986 , Y10T29/49993
摘要： A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing is formed for an insert in a main metal body having an upper face; an insert formed from a bundle of fibers with a metal matrix is placed in the housing; a metal cover is placed on the main body so as to cover the insert; the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The housing has the shape of a notch of L-shaped cross section with a face perpendicular to the upper face and a face parallel to the upper face, the cover having an internal notch of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch.
摘要翻译： 一种用陶瓷纤维增强的金属部件的制造方法，其特征在于，在具有上表面的主金属体中形成用于插入物的壳体; 将由具有金属基体的纤维束形成的插入物放置在壳体中; 金属盖放置在主体上以覆盖插入件; 将盖焊接到金属体上; 进行热等静压操作; 将所获得的部件加工成所需的形状。 壳体具有L形截面的凹口的形状，具有垂直于上表面的面和平行于上表面的面，该盖具有L形横截面的内凹口，其具有与 具有所述插入件的金属体的外壳上形成有盖，使得压力垂直于凹口的所述面施加。
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公开(公告)号：US20110005060A1
公开(公告)日：2011-01-13
申请号：US12810751
申请日：2008-12-24
申请人： Richard Masson , Dominique Ducos
发明人： Richard Masson , Dominique Ducos
IPC分类号： B23P17/00
CPC分类号： C22C47/00 , C22C47/04 , C22C47/064 , Y10T29/49 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , Y10T29/49801 , Y10T29/49885 , Y10T29/49968 , Y10T29/4998 , Y10T29/49984 , Y10T29/49986 , Y10T29/49993
摘要： The present invention relates to a process for manufacturing a metal part reinforced with ceramic fibres, in which: a housing is formed for an insert in a main metal body (2) having an upper face (21); an insert (3) formed from a bundle of fibres with a metal matrix is placed in the housing; a metal cover (4) is placed on the main body (2) so as to cover the insert (3); the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The process is characterized in that the housing has the shape of a notch of L-shaped cross section with a face (23P) perpendicular to the upper face (21) and a face (23S) parallel to the upper face (21), the cover (4) having an internal notch (43) of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover (4) being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch (23).
摘要翻译： 本发明涉及一种用陶瓷纤维增强的金属部件的制造方法，其中：在具有上表面（21）的主金属体（2）中形成用于插入件的壳体; 将由具有金属基体的纤维束形成的插入件（3）放置在壳体中; 金属盖（4）被放置在主体（2）上以覆盖插入件（3）; 将盖焊接到金属体上; 进行热等静压操作; 将所获得的部件加工成所需的形状。 该方法的特征在于，壳体具有垂直于上表面（21）的面（23P）和平行于上表面（21）的面（23S）的L形横截面的凹口的形状， 具有L形横截面的内部凹口（43）的盖（4），其具有与具有所述插入件的金属体的形状互补的形状，所述盖（4）在外侧成形，使得施加压力 垂直于凹口（23）的所述面。
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公开(公告)号：US07007891B2
公开(公告)日：2006-03-07
申请号：US10880466
申请日：2004-07-01
IPC分类号： B64C25/14
CPC分类号： B64C25/10 , B64C25/001 , B64C25/34 , B64C25/58 , B64C2025/008 , B64C2025/125
摘要： 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 the 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： 用于飞机的伸缩起落架，起落架是垂直升起的类型，并且包括多个独立的腿，每个腿包括刚性地固定到飞行器的结构的结构部分，支撑一对 车轮和减震器。 根据本发明，每个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使腿部折叠，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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17.发明授权Device for coupling an actuator for controlling the landing gear of an aircraft 有权用于联接用于控制飞行器的起落架的致动器的装置公开(公告)号：US09511852B2
公开(公告)日：2016-12-06
申请号：US14238534
申请日：2012-09-07
摘要： A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.
摘要翻译： 一种用于将用于操作飞行器起落架的致动器联接到飞机结构的装置。 该装置包括杠杆，其具有用于铰接到飞行器的结构的第一端和致动器铰接的第二端，作用在杠杆上的预加载结构，以将其推向稳定的休止位置，该静止位置由 没有任何力通过致动器的杠杆; 以及当所述致动器被致动时限定所述杠杆的至少一个工作位置的邻接结构。
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公开(公告)号：US09254912B2
公开(公告)日：2016-02-09
申请号：US14237598
申请日：2012-08-20
申请人： Dominique Ducos
发明人： Dominique Ducos
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 comprises 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. It also has a first flap (2) hinged to the support via its distal end about a first hinge axis (X1) substantially parallel to the axle and a second flap (3) hinged to the first flap about a second hinge axis (X2) substantially parallel to the first hinge axis. Finally, there is a a 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： 一种用于起落架的防抱板偏转器，在轴上具有两个轮子。 偏转器包括固定支撑件（5），用于固定在起落架的一部分上，所述起落架承载车轴，以便在车轮之间延伸并且在车轮之后提供远端。 它还具有围绕基本上平行于车轴的第一铰链轴线（X1）经由其远端铰接到支撑件的第一挡板（2），以及围绕第二铰链轴线（X2）铰接到第一挡板的第二挡板（3） 基本上平行于第一铰链轴线。 最后，设置有一个返回构件（11），以便将第二挡板推压抵靠第一挡板的邻接部分，从而防止第二挡片与第一挡片对准，并且将第一挡板推靠在固定件 支撑件防止第一挡板折叠支撑。
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公开(公告)号：US08458886B2
公开(公告)日：2013-06-11
申请号：US12810949
申请日：2008-12-24
申请人： Richard Masson , Dominique Ducos
发明人： Richard Masson , Dominique Ducos
CPC分类号： C22C47/025 , C22C47/00 , Y10T29/49 , Y10T29/49012 , Y10T29/49343 , Y10T29/49801 , Y10T29/49968 , Y10T29/4998 , Y10T29/49995
摘要： A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing for an insert is machined in a metal body having an upper face; an insert formed from a fiber bundle having a metal matrix is placed in the housing; a metal cover is placed on the metal body so as to cover the insert; the cover is welded onto the metal body; the assembly including the metal body with the cover undergoes a hot isostatic compression treatment; and the treated assembly is machined to obtain the part. The insert is a rectilinear insert and the housing forms a rectilinear groove that extends beyond the insert and is open at each end, the groove being filled by a tab when the cover is placed on the metal body.
摘要翻译： 一种制造用陶瓷纤维增强的金属部件的方法，其中：用于插入件的壳体在具有上表面的金属体中加工; 将由具有金属基体的纤维束形成的插入物放置在壳体中; 金属盖被放置在金属体上以覆盖插入物; 将盖焊接到金属体上; 包括具有盖的金属体的组件进行热等静压处理; 并且对经处理的组件进行加工以获得部件。 插入件是直线插入件，并且壳体形成延伸超过插入件的直线槽，并且在每个端部是开口的，当盖被放置在金属体上时，凹槽由凸片填充。
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20.发明申请MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS AND A DEFORMABLE PARALLELOGRAM STRUCTURE 审中-公开包括两台起重机和一个可变平行机构结构的飞机主要起落架公开(公告)号：US20130140399A1
公开(公告)日：2013-06-06
申请号：US13704164
申请日：2011-06-16
申请人： Dominique Ducos
发明人： Dominique Ducos
IPC分类号： B64C25/62
CPC分类号： B64C25/62 , B64C25/10 , B64C25/34 , B64C2025/125
摘要： An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system.
摘要翻译： 一种飞机起落架，其特征在于，它包括两个支撑轮的摇臂，并安装成在起落架的至少一个枢轴上枢转，起落架包括一个减震器装置，该减震器装置包括耦合到各个摇臂梁的两个连杆， 并且所述连杆中的至少一个伸缩并形成减震器。 两个连杆也联接到可枢转地安装在中心枢轴上的摆动横杆，摇臂梁的枢轴和横杆的中心枢轴安装在腿上，该腿通过两个面板连接到飞行器的机身 它们围绕与摇臂梁的铰链轴垂直的轴线铰接到腿部和飞机的结构，并且与腿部协作以形成可变形的平行四边形系统。
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