Bonded Wing Leading Edge for Laminar Flow

The patent removes fasteners from the leading edge skin panel attachment to eliminate surface discontinuities. Instead of using traditional fastening methods that create protrusions and gaps, the skin panels are bonded directly to the wing box structure, extracting the harmful fastening elements from the aerodynamic surface while maintaining structural integrity through adhesive bonding.

The patent introduces adhesive bonding as an intermediary method between the leading edge skin panels and the wing box structure. This bonding method serves as a mediator that provides structural strength without creating surface discontinuities, as the adhesive creates a smooth transition that maintains laminar flow while still achieving the necessary structural attachment.

The patent applies local quality by positioning anti-icing system components in specific locations that minimize their impact on laminar flow. The anti-icing boots and heating elements are integrated into the leading edge structure in a way that maintains surface smoothness in the critical laminar flow region, allowing ice protection functionality while preserving airflow quality in the most sensitive areas.

The patent moves anti-icing system components to alternative dimensions or locations that reduce their aerodynamic impact. By integrating anti-icing elements into the internal structure or positioning them on the lower surface where they have minimal impact on upper surface laminar flow, the system provides ice protection while maintaining favorable airflow characteristics over the critical upper leading edge surface.

The patent applies dynamics by making the Krueger flap system movable and adjustable. The flaps can be deployed only when needed for high-angle of attack operations, and their design allows them to move smoothly with the airflow. The dynamic deployment capability enables the system to provide enhanced lift when required while maintaining a streamlined, flush configuration during cruise to minimize surface discontinuities and prevent flow separation.

The patent incorporates preliminary action by designing the Krueger flap mechanism to maintain a flush, streamlined configuration before deployment. The flaps are pre-positioned to be flush with the leading edge surface, and the deployment mechanism is designed to maintain surface continuity even during transition, preventing flow separation by ensuring smooth airflow over the surface before high-lift operations are required.