| 摘要 |
<p>A composite material elongate structural member, such as a spar (102), for use in an aerospace structure, comprises a web (108) disposed between upper and lower flanges (104, 106). The web (108) may include a clockwise twist about an axis (164) parallel to the length L at a first portion towards the wing-root-end of the spar (102) and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar (102). The geometry of the spar (102) may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange (104) via the web (108) to a distal edge of the lower flange (106) varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar (102), undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member (102) varies non-linearly may be reduced by means of such an arrangement.</p> |
