公开(公告)号：US20150183509A1

公开(公告)日：2015-07-02

申请号：US14587590

申请日：2014-12-31

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Raúl LLAMAS SANDÍN ,  Miguel LUQUE BUZO ,  José Luis MARTÍNEZ MUÑOZ

IPC: B64C9/08

CPC classification number: B64C9/08 ,  B64C1/26 ,  B64C5/02 ,  B64C9/02 ,  B64C13/28

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract translation: 本发明提供了具有可调节水平稳定器（13）的飞行器，其不需要在后机身的阻力区域中的切口，并且在常规水平稳定器中占据较少的空间。 后部机身（5）至少包括具有耐机构的第一部分（9）和第二部分（11），第一部分的后部具有非抵抗机身（即整流罩）。 水平稳定器和修剪致动器（50）的承载结构（30）设置在所述第二部分（11）内。 枢轴元件（41）安装在其前侧并且联接到后机身的第一部分（9）。 连接配件（21）安装在其后侧，并且修整致动器（50）被设置成在修整操作期间在飞行器的Z轴方向上在连接配件（21）上施加力。