Abstract: Components for valve treatment systems are disclosed. Valve treatment systems can include a delivery system for an implantable device. The delivery system can include one or more of clasp control components slidably disposed on a catheter handle, a control element for opening and closing the implantable device, a catheter assembly with features to reduce friction with another catheter assembly, grips for attaching catheter assemblies to clamps, catheter assemblies with features that stiffen or provide variable stiffness, and catheter assemblies with one or more steering control lumens incorporated into a reinforcement layer.

Abstract: A method and apparatus of creating vortices via vortex controllers, wherein the vortices are capable of entraining high-energy surrounding flow to induce a series of powerful longitudinal vortices that reattach separated flow by merging into single vortices along the undersurface of the afterbody to reenergize the fuselage boundary layer, thus preventing undersurface flow separation and reducing overall afterbody drag.

Abstract: A method and apparatus of creating vortices via vortex controllers, wherein the vortices are capable of entraining high-energy surrounding flow to induce a series of powerful longitudinal vortices that reattach separated flow by merging into single vortices along the undersurface of the afterbody to reenergize the fuselage boundary layer, thus preventing undersurface flow separation and reducing overall afterbody drag.

Abstract: Method and apparatus for generating a stable leading edge lifting vortex controller that significantly improves flight control and safety of an aircraft. More specifically, in a preferred embodiment, the present invention is generally a triangular or diamond-shaped member, as seen in a plan view, having a leading edge and a trailing edge wherein the trailing edge of the member is attached to the leading edge of an aircraft wing in substantially the same plane as the wing. The distal end of the leading edge of the member has a slightly drooped rounded nose. The member has a variable thickness wherein the upper surface of the member has a camber and wherein the member is substantially shaped like an airfoil. The thickness at the centerline of the member proximal to the wing is approximately the thickness of the leading edge of the wing to provide a smooth transition along the centerline.

Abstract: A fluid flow control for reducing the drag associated with an upswept afterbody includes a pair of ridges forming substantially symmetric flow channels arranged in an approximately helical fashion on either side of the afterbody so as to intersect at approximately the centerline of the undersurface. Each ridge has a generally rearward pitch so that the flow channels form a substantially V-shaped configuration rearwardly. The flow channels cross the local fluid flow streamlines at an optimum angle for producing a strong vortex core along the channel length with the vortex rotating in a direction counter to that normally found in the wake of conventional upswept afterbodies.

Abstract: A method of applying and controlling vortex lift to a unique high-lift airfoil (29) is described wherein the planform of the airfoil (29) comprises a swept-forward outer panel (31) and a swept-aft or unswept inboard panel (33). A leading edge vortex (37) is formed on (31) and attached flow is maintained on (33). The attached flow on (33) causes the vortex (37) of the airfoil (29) to turn downstream and also induces axial flow along axis of vortex (37). Both of these results serve to delay vortex burst. A high-lift trailing edge device (45) such as a mechanical flap as the circulation control concept will induce a high leading edge flow angularity and cause the vortex (37) to grow in strength, thereby increasing vortex lift. The vortex (37) replaces the high-weight, high-lift leading device that would otherwise be required.