1. A nail care system comprising:
A manicure bowl having a front wall, a side wall, and a floor cooperating with each other to define an interior space for retaining fluid therein; a hand tool adapted to being powered; a plurality of adapter heads for interfacing with said hand tool; a base housing having an aperture and defining a cavity there through, said manicure bowl being removably received within said cavity and the base housing further having a storage compartment for storing said powered hand tool and said plurality of motion adapter heads; a fan disposed in an interior space of said base housing for circulating air in said cavity, wherein said fan being located directly above said manicure bowl.
2. The nail care system of claim 1, further comprising a lid for covering at least an upper portion of said storage compartment.
3. The nail care system of claim 2, wherein said lid is at least partially translucent.
4. The nail care system of claim 2, wherein said lid is hingedly connected to said base housing.
5. The nail care system of claim 1, wherein said floor of said manicure bowl is contoured to support a hand and fingers.
6. The nail care system of claim 1, wherein said manicure bowl is selectively received in said cavity such that said front wall of said manicure bowl is flush with an exterior surface of said base housing at an interface between said front wall and said exterior surface of said base housing.
7. The nail care system of claim 1, wherein one of said plurality of adapter heads is a linear motion adapter head and another of said plurality of adapter heads is a rotary motion adapter head.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. An aircraft wing having a controllable structural stiffness for adjusting its shape, the wing comprising:
an upper wing surface;
at least one upper spar coupled to said upper wing surface;
a lower wing surface;
at least one lower spar coupled to said lower wing surface;
a plurality of fasteners for connecting said one upper spar and said one lower spar;
at least one of said fasteners comprising an adjustable clamp movable between a clamped position wherein said one upper spar and said one lower spar are secured at said clamp for fixing the shape of said wing and an unclamped position wherein said one upper spar and said one lower spar are relatively movable at said clamp for adjusting the shape of said wing.
2. An aircraft wing in accordance with claim 1, wherein: said adjustable clamp comprises a bolt of adjustable grip.
3. An aircraft wing in accordance with claim 2, wherein:
said one upper spar and said one lower spar each comprise aligned longitudinal slots receiving said bolt.
4. An aircraft wing in accordance with claim 2, wherein:
said bolt is a piezo-electric bolt.
5. An aircraft wing in accordance with claim 1, wherein:
each of said plurality of fasteners comprises a corresponding adjustable clamp selectively movable between a clamped position wherein said one upper spar and said one lower spar are secured together at said clamp for fixing the shape of said wing and an unclamped position wherein said one upper spar and said one lower spar are relatively movable at said clamp for adjusting the shape of said wing, each said adjustable clamp being spaced along said one upper spar and said one lower spar.
6. An aircraft wing in accordance with claim 5, comprising:
a second upper spar associated with said upper wing surface;
a second lower spar associated with said lower wing surface;
a plurality of second fasteners for connecting said second upper spar and said second lower spar;
at least one of said second fasteners comprising an adjustable second clamp movable between a clamped position wherein said second upper spar and said second lower spar are secured at said clamp for fixing the shape of said wing and an unclamped position wherein said second upper spar and said second lower spar are relatively movable at said second clamp for adjusting the shape of said wing.
7. An aircraft wing in accordance with claim 6, wherein:
a bending axis of said wing is defined by selectively controlling said first fasteners and selectively controlling said second fasteners.
8. An aircraft wing in accordance with claim 7, wherein:
aerodynamic forces bend said wing about said bending axis and produce a predetermined twist in said wing.
9. An aircraft wing in accordance with claim 6, wherein:
a first bending axis of said wing is defined by selectively controlling a first plurality of said first fasteners along and selectively controlling a first plurality of said second fasteners.
10. An aircraft wing in accordance with claim 9, wherein:
a second bending axis of said wing is defined by selectively controlling a second plurality of said first fasteners along and selectively controlling a second plurality of said second fasteners.
11. An aircraft wing in accordance with claim 10, wherein:
when said wing is subjected to aerodynamic forces, said first bending axis produces a twist in said wing in a first direction and said second bending axis produces a twist in said wing in a second direction.
12. An aircraft wing comprising:
an upper wing surface;
a first substructure extending from said upper wing surface;
a lower wing surface;
a second substructure extending from said lower wing surface;
a plurality of selectively operable clamping assemblies coupling said first and said second substructures and operable to selectively control the structural stiffness of said wing.
13. An aircraft wing in accordance with claim 12, wherein:
said plurality of selectively operable clamping assemblies are selectively operable to provide a controllable bending axis for said wing.
14. An aircraft wing in accordance with claim 13, wherein:
the clamping force of each of said plurality of selectively operable clamping assemblies is modulated to control twist of said aircraft wing in the presence of aerodynamic forces.
15. An aircraft wing in accordance with claim 12, wherein:
the clamping force of each of said plurality of selectively operable clamping assemblies is modulated to modulate the bending axis of said wing.
16. A method for controlling a wing comprising an upper wing surface and a lower wing surface, said method comprising:
providing a first substructure coupled to said upper wing surface;
providing a second substructure coupled to said lower wing surface;
providing a plurality of selectively operable clamping assemblies coupling said first and said second substructures; and
selectively adjusting said clamping assemblies to selectively control the structural stiffness of said wing.
17. A method in accordance with claim 16, comprising:
controlling the bending axis of said wing with said clamping assemblies.
18. A method in accordance with claim 17, comprising:
controlling the twist of said aircraft wing in the presence of aerodynamic forces by modulating the clamping force of each of said plurality of selectively operable clamping assemblies.
19. A method in accordance with claim 17, comprising:
modulating the bending axis of said by selectively modulating the clamping force of each of said plurality of selectively operable clamping assemblies.
20. A method in accordance with claim 16, comprising:
controlling the twist of said aircraft wing in the presence of aerodynamic forces by selectively adjusting the structural stiffness of said wing.