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    PRESENTOIR AVEC FACE TRANSLUCIDE POURVUE D'UNE OUVERTURE SECURISABLE
    1.
    发明公开
    PRESENTOIR AVEC FACE TRANSLUCIDE POURVUE D'UNE OUVERTURE SECURISABLE 有权
    爱沙尼亚麻省理工学院

    公开(公告)号：EP2943096A1

    公开(公告)日：2015-11-18

    申请号：EP13824340.7

    申请日：2013-12-18

    申请人： BLR

    发明人： THIVEL, Franck ,  PORPORA, Thierry

    IPC分类号： A47F3/00 ,  A47F3/12 ,  E05C19/02

    CPC分类号： A47F3/125 ,  A47F3/002 ,  E05B17/2003 ,  E05C19/024 ,  E06B3/385 ,  E06B9/04

    摘要： The invention relates to a display case having at least one translucent face provided with a securable opening, having: • a presentation volume provided to house one or more objects to be presented in the display case; • a viewing face provided with at least one secured pivoting window having: • a panel fixed to the display case in a pivoting manner by one of the sides of the panel by means of a pivoting side support; • a pivoting side rail fixed to the display case in a pivoting manner in the opposite region of the translucent panel with respect to the pivoting side support and having a housing in which the free edge of the panel is inserted when the panel is in the closed position; said panel being translucent.

    摘要翻译： 本发明涉及具有设置有可固定开口的至少一个半透明面的显示器壳体，该显示器壳体具有：呈现体积，用于容纳要呈现在显示器壳体中的一个或多个物体; •设置有至少一个固定枢转窗的观察面，其具有：•通过枢转侧支撑件通过面板的一个侧面以枢转方式固定到展示柜的面板; •枢转侧轨道，其以相对于所述枢转侧支撑件在所述半透明板的相对区域中以枢转方式固定到所述显示器壳体，并且具有壳体，当所述面板处于所述闭合状态时，所述壳体的所述自由边缘被插入所述壳体中 位置; 所述面板是半透明的。

    HELICOPTER WITH ANTI-TORQUE SYSTEM, RELATED KIT AND METHODS
    2.
    发明公开
    HELICOPTER WITH ANTI-TORQUE SYSTEM, RELATED KIT AND METHODS 审中-公开
    带有抗扭矩系统的直升机，相关试剂盒和方法

    公开(公告)号：EP3317180A2

    公开(公告)日：2018-05-09

    申请号：EP16825927.3

    申请日：2016-06-29

    申请人： BLR Aerospace, LLC

    发明人： CARPENTER, Michael ,  SMITH, Daniel, A.

    IPC分类号： B64C23/06

    CPC分类号： B64C27/82 ,  B64C7/00 ,  B64C23/06 ,  B64C2027/8263 ,  Y02T50/162

    摘要： A strake may extend along a portion of an approaching side of a tail boom of a helicopter. A number of vortex generators (VGs) may extend along a portion of a retreating side of the tail boom. For tail booms with circular cross sections, the strake and the VGs are positioned between approximately 5 and 15 degrees below a horizontal plane of the tail boom when viewed end on, on respective sides of the tail boom. For tail booms with non-circular cross sections, the strake and the VGs is positioned between approximately 5 and 15 degrees above a location where a change in curvature is greatest (e.g., where flow separation would otherwise occur) on a bottom half of the tail boom when viewed end on, on respective sides of the tail boom. A fairing may be located on the retreating side on the upper half of the tail boom, to create an asymmetric profile.

    AIRCRAFT STABILIZATION SYSTEMS AND METHODS OF MODIFYING AN AIRCRAFT WITH THE SAME
    3.
    发明公开
    AIRCRAFT STABILIZATION SYSTEMS AND METHODS OF MODIFYING AN AIRCRAFT WITH THE SAME 审中-公开
    飞机稳定系统和变型的飞机订单方法

    公开(公告)号：EP2935002A4

    公开(公告)日：2016-02-24

    申请号：EP13874489

    申请日：2013-12-17

    申请人： BLR AEROSPACE LLC

    发明人： DESROCHE ROBERT J

    IPC分类号： B64C27/82

    CPC分类号： B64C27/12 ,  B64C27/04 ,  B64C2027/8245 ,  Y10T29/49622

    摘要： A method of modifying a helicopter includes providing a tail boom of the helicopter and modifying a surface profile of the tail boom on at least a first side of the tail boom to improve flow attachment of air flowing over the first side of the modified tail boom during operation of the helicopter. The first side of the tail boom is located on an opposite side of the tail boom from a second side of the tail boom towards which a main rotor blade of the helicopter approaches during rotation.

    AIRCRAFT STABILIZATION SYSTEMS AND METHODS OF MODIFYING AN AIRCRAFT WITH THE SAME
    5.
    发明公开
    AIRCRAFT STABILIZATION SYSTEMS AND METHODS OF MODIFYING AN AIRCRAFT WITH THE SAME 审中-公开
    飞机稳定系统和变型的飞机订单方法

    公开(公告)号：EP2935002A2

    公开(公告)日：2015-10-28

    申请号：EP13874489.1

    申请日：2013-12-17

    申请人： BLR Aerospace, LLC

    发明人： DESROCHE, Robert, J.

    IPC分类号： B64C27/82

    CPC分类号： B64C27/12 ,  B64C27/04 ,  B64C2027/8245 ,  Y10T29/49622

    摘要： A method of modifying a helicopter includes providing a tail boom of the helicopter and modifying a surface profile of the tail boom on at least a first side of the tail boom to improve flow attachment of air flowing over the first side of the modified tail boom during operation of the helicopter. The first side of the tail boom is located on an opposite side of the tail boom from a second side of the tail boom towards which a main rotor blade of the helicopter approaches during rotation.

    HELICOPTER AND METHOD OF MANUFACTURING A HELICOPTER
    7.
    发明公开
    HELICOPTER AND METHOD OF MANUFACTURING A HELICOPTER 审中-公开

    公开(公告)号：EP3909848A1

    公开(公告)日：2021-11-17

    申请号：EP21182619.3

    申请日：2016-06-29

    申请人： BLR Aerospace, LLC

    发明人： Carpenter, Michael ,  Smith, Daniel

    IPC分类号： B64C23/06 ,  B64C7/00 ,  B64C27/82

    摘要： A helicopter (100) comprises a fuselage (102), a main rotor (106) coupled to the fuselage (102) and that in operation rotates in a first rotational direction with respect to the fuselage (102), an engine (110) carried by the fuselage (102) and drivingly coupled to rotate the main rotor (106) in the first rotational direction with respect to the fuselage (102), a tail boom (112) that extends rearwardly of the fuselage (102), the tail boom (112) having an approaching side and a retreating side (132), the approaching side being a side of the tail boom (112) that the main rotor (106) approaches when rotating in the first rotational direction, the retreating side (132) being a side of the tail boom (112) that the main rotor (106) retreats from when rotating in the first rotational direction, the retreating side (132) opposite the approaching side across a width of the tail boom (112), the approaching side of the tail boom (112) having a varying radius of curvature about a centerline, the retreating side (132) of the tail boom (112) has a varying radius of curvature about the centerline of the tail boom (112), and the radius of curvature over a portion of the tail boom (112) is infinite, and the tail boom (112) having an upper half, a lower a half and a horizontal plane (248) that extends between the upper half and the lower half of the tail boom (112), a first strake that extends outwardly from the approaching side of the tail boom (112), the first strake (130) positioned below the horizontal plane of the tail boom (112) at a position that is from approximately 5 degrees to 15 degrees above a location at which flow separation would otherwise occur on the approaching side below the horizontal plane in the absence of the first strake, and at least one vortex generator (136) that extends outwardly from the retreating side (132) of the tail boom (112), the at least one vortex generator (136) positioned below the horizontal plane of the tail boom (112) at a position that is from approximately 5 degrees to 15 degrees above a location at which flow separation would otherwise occur on the retreating side (132) below the horizontal plane in absence of the at least one vortex generator (136).