公开(公告)号：US20150360792A1

公开(公告)日：2015-12-17

申请号：US14765399

申请日：2014-02-04

Applicant: ASTRIUM SAS ,  AIRBUS DEFENCE AND SPACE SAS

Inventor： Benjamin FAURE ,  Jérôme BERTRAND ,  Yohann CORABOEUF ,  Samuel CHEVROLLIER ,  Robert ABADIE-LA-HAILLE ,  Pascal MEZIERES ,  Angélique SANTERRE

IPC: B64D37/04 ,  B64G1/40 ,  B64D37/30 ,  B64D37/06

CPC classification number: B64G1/402 ,  B64D37/04 ,  B64D37/06 ,  B64D37/30 ,  F17C13/00 ,  F17C13/008 ,  F17C2201/0119 ,  F17C2201/054 ,  F17C2205/0192 ,  F17C2221/08 ,  F17C2223/0161 ,  F17C2270/0194 ,  F17C2270/0197

Abstract: The present invention relates to a device for mounting and supporting a generally cylindrical or tapered tank, having a main axis X, that includes a pair of first means for retaining the tank along a vertical axis Z on each of a first and second end of the tank, a second means for retaining the tank along a horizontal axis Y, perpendicular to the main axis, on the first end of the tank, and a third means for retaining in a ball-and-socket joint, the means being located around the vertical axis and connected to the second end of the tank.

Abstract translation: 本发明涉及一种用于安装和支撑具有主轴线X的大致圆柱形或锥形槽的装置，该主轴线包括一对第一装置，用于沿着垂直轴线Z在第一和第二端 罐，第二装置，用于沿着垂直于主轴线的水平轴线Y在罐的第一端上保持箱体，以及用于保持在球窝接头中的第三装置，该装置位于 垂直轴并连接到油箱的第二端。

公开(公告)号：US20160052650A1

公开(公告)日：2016-02-25

申请号：US14781938

申请日：2014-03-28

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Eugénio FERREIRA ,  Angélique SANTERRE ,  Benjamin FAURE ,  Samuel CHEVROLLIER ,  Pierre PARPAITE ,  Christophe FAVRE

IPC: B64G1/62 ,  B64C25/10 ,  B64C9/32 ,  B64G1/14

CPC classification number: B64G1/62 ,  B64C9/323 ,  B64C25/10 ,  B64C25/16 ,  B64G1/14 ,  Y02T50/32

Abstract: A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft.

Abstract translation: 适用于航空飞行的太空飞机除了包括设置在其下翼面下方的一个或多个快门的姿态控制装置之外，还包括限定下翼面的机体和机翼，并且在收起位置和倾斜延伸位置之间可操纵 在从空间飞行阶段到飞机航空飞行阶段的过渡期间进行空气动力学制动。

公开(公告)号：US20150360791A1

公开(公告)日：2015-12-17

申请号：US14763859

申请日：2014-02-04

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Samuel CHEVROLLIER ,  Robert ABADIE-LAHAILLE ,  Pascal MEZIERES ,  Benjamin FAURE ,  Jérôme BERTRAND ,  Yohann CORABOEUF ,  Angélique SANTERRE

IPC: B64D37/04 ,  B64G1/40 ,  B64D37/30 ,  B64D37/06

CPC classification number: B64D37/04 ,  B64D37/06 ,  B64D37/30 ,  B64G1/402 ,  F16C11/0695 ,  F17C2205/0192 ,  F17C2221/08 ,  F17C2270/0197

Abstract: The invention concerns a tank retainer for retaining a tank in the fuselage of an aircraft which includes, between the tank and a frame rigidly connected to the fuselage of the aircraft, a hinged retaining means and a fastening rod on which said hinged retaining means is mounted. Advantageously, the hinged retaining means is intended to be connected to a rear end of the tank and the fastening rod is suitable for being mounted on the frame rigidly connected to the fuselage of the aircraft and, preferably, the hinged retaining means comprises a ball joint.

Abstract translation: 本发明涉及一种用于将坦克保持在飞行器的机身中的坦克保持器，其包括在坦克和刚性地连接到飞行器的机身的框架之间，铰接的保持装置和紧固杆，所述铰接的保持装置安装在该紧固杆上 。 有利地，铰接的保持装置旨在连接到罐的后端，并且紧固杆适于安装在刚性地连接到飞行器的机身的框架上，并且优选地，铰接的保持装置包括球形接头 。