Electric harness for engine of airplane, has tubular protecting structure enclosing electrical conductors connected to sensor, where male or female contacts connect/disconnect two parts of one of electrical conductors,申请号FR20090004341-传众专利搜索

Electric harness for engine of airplane, has tubular protecting structure enclosing electrical conductors connected to sensor, where male or female contacts connect/disconnect two parts of one of electrical conductors

申请公布号：FR2950205(A1)

申请号：FR20090004341

申请日期：2009.09.11

申请公布日期：2011.03.18

申请人：

SNECMA

发明人：DETERRE GEOFFRAY

分类号：H02G3/02;F02C7/00

主分类号：H02G3/02

摘要：<p>The harness (10) has a tubular protecting structure (12) including an electromagnetic shielding braid (22) whose end is protected by a cylindrical sleeve (32), and enclosing electrical conductors (14, 15) connected to a sensor (18) e.g. vibration sensor. The sensor has a body (16) on which an end of the structure is detachably fixed. One of the conductors has two parts that are housed in the structure and the body, respectively. Elongated male or female contacts (40, 42) connect/disconnect the two parts. One of the parts is mounted in a passage of an elastomer block (36). The electromagnetic shielding braid is made of metal. The cylindrical sleeve is made of thermoshrinkable plastic material.</p>