公开(公告)号：EP2950071A1

公开(公告)日：2015-12-02

申请号：EP14382202.1

申请日：2014-05-30

申请人： Airbus Operations S.L.

发明人： Maldonado Morello, Julian ,  Díaz Parrilla, Jose, Maria ,  Gómez Garciá, Javier

IPC分类号： G01L15/00 ,  G01M9/06

CPC分类号： G01M9/06 ,  G01L15/00

摘要： An aerodynamic pressure sensing system for an such as an airplane lifting surface, rotor blade etc. is disclosed wherein a plurality of pressure probes (7) are arranged on the upper and lower surfaces of the airfoil-shaped body (1) to sense aerodynamic pressure at discrete locations thereof, wherein the pressure sensitive elements (7) are arranged to form a plurality of rows (8) on said upper and lower surfaces. According to the invention between 55-75% of the total number of the pressure sensitive elements (7) are arranged at the leading edge section, and the remaining pressure sensitive elements are arranged at the intermediate section of the airfoil-shaped body. The invention allows measuring aerodynamic forces generated at the leading edge of the airfoil and particularly the suction peak more precisely and with a reduced number of pressure probes.

摘要翻译： 公开了一种用于例如飞机提升表面，转子叶片等的空气动力学压力感测系统，其中在翼型体（1）的上表面和下表面上布置有多个压力探针（7）以感测空气动力压力 在其离散位置处，其中压敏元件（7）被布置成在所述上表面和下表面上形成多个行（8）。 根据本发明，压敏元件（7）的总数的55-75％之间布置在前缘部分，其余的压敏元件设置在翼型体的中间部分。 本发明允许测量在翼型的前缘产生的空气动力，特别是在更精确地减少吸力峰值并且减少数量的压力探针。