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公开(公告)号：EP2982597B1
公开(公告)日：2017-01-25
申请号：EP15177693.7
申请日：2015-07-21
发明人： Van Buskirk, Matthew Carl , Seifert, Michael Scott , Burnett, Michael Christopher , Isaac, Mark Loring
CPC分类号： B64C5/02 , B64C1/26 , B64C5/10 , B64C29/0033
摘要： According to one embodiment, an empennage attachment system features an aft attachment mechanism (164) and a forward attachment system (200). The aft attachment mechanism (164) is configured to be coupled to a tail section of a body of an aircraft (100) and to an empennage (160) proximate to an aft spar (162) of the empennage (160). The aft attachment mechanism (164) defines a pitch axis (165) such that the aft attachment mechanism (164) allows the empennage (160) to rotate about the pitch axis (165). The forward attachment system (200) is configured to be coupled to the tail section of the body and to the empennage (160) proximate to a forward spar (166) of the empennage (160). The forward attachment system (200) is configured to restrict rotation of the empennage (160) about the pitch axis (165) to an allowable range of motion.
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公开(公告)号：EP2982597A1
公开(公告)日：2016-02-10
申请号：EP15177693.7
申请日：2015-07-21
发明人： Van Buskirk, Matthew Carl , Seifert, Michael Scott , Burnett, Michael Christopher , Isaac, Mark Loring
CPC分类号： B64C5/02 , B64C1/26 , B64C5/10 , B64C29/0033
摘要： According to one embodiment, an empennage attachment system features an aft attachment mechanism (164) and a forward attachment system (200). The aft attachment mechanism (164) is configured to be coupled to a tail section of a body of an aircraft (100) and to an empennage (160) proximate to an aft spar (162) of the empennage (160). The aft attachment mechanism (164) defines a pitch axis (165) such that the aft attachment mechanism (164) allows the empennage (160) to rotate about the pitch axis (165). The forward attachment system (200) is configured to be coupled to the tail section of the body and to the empennage (160) proximate to a forward spar (166) of the empennage (160). The forward attachment system (200) is configured to restrict rotation of the empennage (160) about the pitch axis (165) to an allowable range of motion.
摘要翻译： 根据一个实施例，尾翼附接系统具有后附连机构（164）和前附件系统（200）。 后部附接机构（164）构造成联接到飞行器（100）的主体的尾部和靠近尾翼（160）的后部翼梁（162）的尾翼（160）。 尾部附接机构（164）限定俯仰轴线（165），使得后部附接机构（164）允许尾翼（160）围绕俯仰轴线（165）旋转。 前向附接系统（200）被配置为联接到身体的尾部和靠近尾翼（160）的向前梁（166）的尾翼（160）。 前向附接系统（200）被配置为将尾翼（160）围绕俯仰轴线（165）的旋转限制到允许的运动范围。
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