Composite wing-body joint

Details Composite wing-body joint Composite wing-body joint

B - Operations, Transporting

64

C

B64C 1/26 (2006.01) B64C 3/18 (2006.01) B64C 3/26 (2006.01)

Patent

CA 2649125

Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel (104) spanning substantially the entire wingspan of an aircraft, includes at least a center portion (110) and a pair of outwardly projecting wing portions (106, 108). The portions may include a skin formed from successive layers or plies of composite material which overlap and offset at the joint between respective sections creating a pad-up area to carry loads between the portions. In a particular implementation, the skin is laid over one or more structural stringers (112) which are transitioned into the joints (116, 118) between sections such as by tapering of the thickness and/or stiffness of the stringer.

Certains modes de réalisation de l'invention concernent des panneaux et des joints composites intégrés pour des structures composites. Dans un mode de réalisation, un panneau intégré qui s'étend sensiblement sur la totalité de l'envergure d'un aéronef, comprend au moins une partie centrale et une paire de parties ailes faisant saillie vers l'extérieur. Ces parties peuvent comprendre une peau formée à partir de couches ou pellicules successives de matériau composite qui sont superposées et décalées au niveau du joint entre des sections respectives, ce qui permet de créer une surface d'accumulation pour porter des charges entre lesdites parties. Dans un mode de réalisation particulier, la peau est disposée sur une ou plusieurs lisses structurales qui sont passées dans les joints entre les sections par réduction progressive de l'épaisseur et/ou de la rigidité de la lisse.

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