发明名称 SKIN-STRINGER DESIGN FOR COMPOSITE WINGS
摘要 The present invention relates to composite skin-stringer composites capable of removing or reducing the risk of desquamation in a skin-stringer interface. To achieve the purpose, in regard to a superior load, a skin and a stringer arrange ply directions (in other words, angles of fiber routes of plies) by being transformed to reduce relative opening (demolition mode I) and/or sliding (demolition mode II) and/or scissoring (demolition mode III) in the skin-stringer interface. The situation is possible when coupling between specific transformation modes is purposefully activated instead of being suppressed. The suggested solution is capable of solving existing problems by controlling the ply directions of the stringer so that the stringer transforms cracks to be formed by a load (before undesirably malfunctioning modes) through a controlled method to suppress or ″close″ the cracks.
申请公布号 KR20160083812(A) 申请公布日期 2016.07.12
申请号 KR20150190283 申请日期 2015.12.30
申请人 THE BOEING COMPANY 发明人 BALABANOV VLADIMIR;WECKNER OLAF;WU YUAN JYE;SAADI ABDELHAI MAYSARA;RASSAIAN MOSTAFA
分类号 B64C1/06;B64F5/00 主分类号 B64C1/06
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