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    • 4. 发明授权
    • Folding wing structure for missile
    • 导弹的折翼结构
    • US4858851A
    • 1989-08-22
    • US203200
    • 1988-06-07
    • Steven A. ManciniJoseph D. Kutschka
    • Steven A. ManciniJoseph D. Kutschka
    • B64C3/56F42B10/14
    • F42B10/146
    • A folding wing structure for a missile or other airframe comprises a supporting strut assembly including a leading strut and a trailing strut pivotally secured together at their common ends and pivotally mounted at spaced locations relative to the airframe at their opposite ends, the struts being moveable between a collapsed, storage position in which they are substantially colinear and an expanded, erect position in which they project radially out from the missile. A biassing device urges the struts into the erect position. A double walled, pocket-like wing member of flexible fabric material encloses the strut assembly and conforms substantially to the extended configuration of the struts, and a series of spaced, parallel reinforcing ribs extend chordwise across each wall of the wing member in its erect position between the leading and trailing struts.
    • 用于导弹或其他机身的折叠翼结构包括支撑支柱组件,其包括前导支柱和在其共同端部枢转地固定在一起的后支柱,并且在其相对端处相对于机身枢转地安装在间隔开的位置,支柱可在 一个倒塌的储存位置,在这些位置上,它们基本上是共线的,并且扩张的直立位置,它们从导弹径向伸出。 偏置装置将支柱推向直立位置。 柔性织物材料的双壁袋状翼构件包围支柱组件,并且基本上与支柱的延伸构型一致,并且一系列间隔开的平行的加强肋在其直立位置上横过翅片构件的每个壁延伸 在前后撑杆之间。