公开(公告)号：US20170334545A1

公开(公告)日：2017-11-23

申请号：US15523074

申请日：2015-10-30

Applicant: Airbus Operations, S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Javier Francisco HONORATO RUIZ ,  Jose Francisco CRUZ DOMINGUEZ ,  Luis RAMOS GARCIA

IPC: B64C5/02 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: An aircraft horizontal tail plane (HTP) of the continuous type, wherein the inner-most ribs of the right-hand side and left-hand side torsion boxes are arranged to have one end joined right at the joint zone where both rear spars meet at axis of symmetry of the HTP. In this way, the loads at this central region of the HTP are concentrated at the joint zone where the inner-most ribs and the rear spars converge. The HTP can be manufactured with a reduced number of components.

公开(公告)号：US20150375846A1

公开(公告)日：2015-12-31

申请号：US14753986

申请日：2015-06-29

Applicant: Airbus Operations, S.L.

Inventor： Carlos GARCIA NIETO ,  Enrique GUINALDO FERNÁNDEZ ,  Iker VELEZ DE MENDIZÁBAL ALONSO ,  Luis RAMOS GARCIA

IPC: B64C3/28 ,  B64C3/18 ,  B21J15/02 ,  B29D99/00

CPC classification number: B64C3/28 ,  B21J15/02 ,  B29C70/30 ,  B29D99/0003 ,  B29D99/0028 ,  B29K2105/256 ,  B64C3/185 ,  B64C3/20 ,  Y02T50/43

Abstract: A method for manufacturing a leading edge of an aircraft lifting surface, the leading edge having a leading edge skin and a supporting structure including at least two spars span-wise arranged and fixed internally to the leading edge skin. In the method of the invention, the supporting structure is obtained from a single laminate of plies of composite material, which is conformed in such that in a cross-sectional view, the laminate includes a trapezoidal configuration which forms a front spar and a rear spar of the supporting structure. A leading edge obtained by the above-described method is disclosed. Since the supporting structure of the leading edge is obtained from a single component, namely the laminate, the manufacturing method is simplified and production costs are significantly reduced.

Abstract translation: 一种用于制造飞机提升表面的前缘的方法，所述前缘具有前缘皮肤和支撑结构，所述支撑结构包括跨越方向布置并固定在所述前缘皮肤内部的至少两个翼梁。 在本发明的方法中，支撑结构由复合材料层的单层层叠体获得，该复合材料层叠在一起，在横截面图中，层压板包括形成前翼梁和后翼梁的梯形构型 的支撑结构。 公开了通过上述方法获得的前沿。 由于前缘的支撑结构是从单一部件即层压板获得的，所以制造方法简单化，生产成本显着降低。