公开(公告)号：US08746619B2

公开(公告)日：2014-06-10

申请号：US13630654

申请日：2012-09-28

Applicant: Northwestern Polytechnical University

Inventor： Yulong Li ,  Jun Liu ,  Tao Suo ,  Zhongbin Tang ,  Jun Lv ,  Liangdao Zhou ,  Guangrong Zhu ,  Hao Cong ,  Zhengli Zhang

IPC: B64C1/00 ,  B64D7/00

CPC classification number: B64C5/06 ,  B64C3/28

Abstract: The present invention relates to a tail for improving anti-bird strike performance of an aircraft. A leading edge reinforcement having a shape of an isosceles triangle is located inside a tail leading edge. The leading edge reinforcement is spanwisely fixed in sections between respective spans formed by the wing rib inside the tail leading edge along the tail of the aircraft. An apex angle of the leading edge reinforcement is the same as an apex angle or arc transition of the tail leading edge skin. The leading edge reinforcement is fixedly connected with the small front beam by a leading edge reinforcement fixed surface. The present invention additionally installs a leading edge reinforcement in the original tail of the aircraft.

Abstract translation: 本发明涉及一种提高飞机防鸟击性能的尾巴。 具有等腰三角形形状的前缘加强件位于尾部前缘内。 前缘加强件沿翼形方向固定在沿着飞机尾部的尾翼前缘内的翼肋形成的相应跨度之间的部分。 前缘加强件的顶角与尾部前缘皮肤的顶角或圆弧过渡相同。 前缘加强件通过前缘加强固定表面与小前梁固定连接。 本发明另外在飞行器的原始尾部安装前缘加强件。

公开(公告)号：US20130082142A1

公开(公告)日：2013-04-04

申请号：US13630654

申请日：2012-09-28

Applicant: Northwestern Polytechnical University

Inventor： Yulong Li ,  Jun Liu ,  Tao Suo ,  Zhongbin Tang ,  Jun Lv ,  Liangdao Zhou ,  Guangrong Zhu ,  Hao Cong ,  Zhengli Zhang

IPC: B64D45/00

CPC classification number: B64C5/06 ,  B64C3/28

Abstract: The present invention relates to a tail for improving anti-bird strike performance of an aircraft. A leading edge reinforcement having a shape of an isosceles triangle is located inside a tail leading edge. The leading edge reinforcement is spanwisely fixed in sections between respective spans formed by the wing rib inside the tail leading edge along the tail of the aircraft. An apex angle of the leading edge reinforcement is the same as an apex angle or arc transition of the tail leading edge skin. The leading edge reinforcement is fixedly connected with the small front beam by a leading edge reinforcement fixed surface. The present invention additionally installs a leading edge reinforcement in the original tail of the aircraft.

Abstract translation: 本发明涉及一种提高飞机防鸟击性能的尾巴。 具有等腰三角形形状的前缘加强件位于尾部前缘内。 前缘加强件沿翼形方向固定在沿着飞机尾部的尾翼前缘内的翼肋形成的相应跨度之间的部分。 前缘加强件的顶角与尾部前缘皮肤的顶角或圆弧过渡相同。 前缘加强件通过前缘加强固定表面与小前梁固定连接。 本发明另外在飞行器的原始尾部安装前缘加强件。