초록 ▼

A compression apparatus for compressing a curved region of a laminated element 2 having a first surface region following a first curved path and a second surface region opposed to the first surface region following a second curved path, wherein a first compression member 40 is placed against the fir

A compression apparatus for compressing a curved region of a laminated element 2 having a first surface region following a first curved path and a second surface region opposed to the first surface region following a second curved path, wherein a first compression member 40 is placed against the first surface region and urged towards a second compression member 50 placed against the second surface region.

대표청구항 ▼

1. An aerodynamic component of an aircraft comprising: an aerodynamic panel having a first surface forming a portion of an outer surface of the aircraft and a second surface opposite to the first surface;a laminated spar including a flange attached to the second surface;a curved region of a laminate

1. An aerodynamic component of an aircraft comprising: an aerodynamic panel having a first surface forming a portion of an outer surface of the aircraft and a second surface opposite to the first surface;a laminated spar including a flange attached to the second surface;a curved region of a laminated spar, wherein the curved region includes a first curved surface forming a first arc and a second curved surface opposite to the first curved surface;the laminated spar includes a first planar surface adjacent the first curved surface;a first compression member abutting the first curved surface, wherein the first compression member includes a curved surface covering and extending an entirety of the first arc of the first curved surface, and a side of the first compression member opposite to the curved surface includes a first planar surface in a plane of the first planar surface of the laminated spar;a second compression member abutting the second curved surface, anda fastener passing through the first and second compression members and the curved region of the laminated spar, wherein the fastener is under tension and urges the first compression member towards the second compression member thereby compressing the curved region of the laminated spar. 2. The aerodynamic component of claim 1 wherein the aerodynamic panel is a wing panel. 3. The aerodynamic component of claim 1 wherein the first compression member includes a surface adjacent the second surface of the aerodynamic panel. 4. The aerodynamic component of claim 1 wherein the first planar surface of laminated spar is a surface of the flange of the laminated spar. 5. The aerodynamic component of claim 1 wherein the first compression member includes a concave surface adapted to seat on the first curved surface, wherein the first curved surface is a convex surface. 6. The aerodynamic component of claim 1 wherein the second compression member includes a convex surface adapted to seat on the second curved surface, and the second curved surface is a concave surface. 7. The aerodynamic component of claim 1 wherein at least one of the first and second compression members has a threaded bore therein for engaging with a threaded region of the fastener. 8. The aerodynamic component of claim 1 wherein the fastener includes a shaft and a head at one end of the shaft, wherein the shaft extends through openings in the first and second compression members, and through an opening in the curve region of the laminated spar, and the head abuts against a rim of one of the openings in the first and second compression members. 9. The aerodynamic component of claim 1 wherein the second compression member is adjacent the flange of the laminated spar. 10. The aerodynamic component of claim 1 wherein the flange lies substantially parallel with the second surface of the aerodynamic panel. 11. The aerodynamic component of claim 1 further comprising another fastener joining the flange of the laminated spar to the aerodynamic panel. 12. The method of claim 1 wherein the side of the first compression member opposite to the curved surface includes a second planar surface in a plane of a second planar surface of the laminated spar. 13. A method comprising: joining a flange of a laminated spar to an inside surface of an aerodynamic panel having an outside surface;positioning a curved surface of a first compression member against a convex surface of a curved region of a laminated spar such that the curved surface of the first compression member extends an entirety of an arc formed by the convex surface;positioning a first planar surface of the first compression member in a plane of a first planar surface of the laminated spar, wherein the first planar surface is on a side of the first compression member opposite to the curved surface;positioning a second compression member against a concave surface of the curved region of the laminate spar, wherein the concave surface is opposite the convex surface;inserting a shaft of a fastener through the first and second compression members and the curved region of the laminated spar,securing a first end region of the fastener to the first compression member and a second end region of the fastener to the second compression member, andplacing the fastener under tension to urge the first compression member towards the second compression member and thereby compress the curved region of the laminated spar. 14. The method of claim 13 wherein the positioning steps include placing a concave surface of the first compression member against the convex surface of the curved region of the laminated spar and placing a convex surface of the second compression member against a concave surface of the curved region. 15. The method of claim 13 wherein joining the flange to the aerodynamic panel includes seating a surface of the flange on the inside surface of the aerodynamic panel. 16. The method of claim 13 further comprising positioning the first compression member adjacent the inside surface of the aerodynamic panel. 17. The method of claim 13 wherein the aerodynamic panel is a wing panel and joining the flange includes joining the flange to the wing panel. 18. The method of claim 13 further comprising positioning the second compression member adjacent the flange of the laminated spar. 19. The method of claim 13 wherein the first compression member has a second planar surface in a plane of a second planar surface of the laminated spar.