초록 ▼

Various apparatus and methods for an actuator and display using one more shape memory springs. A shape memory spring is heated and urges a pin to a first or extended position. The pin may be supported in the first position by a supporting mechanism. The shape memory spring is heated electically, and

Various apparatus and methods for an actuator and display using one more shape memory springs. A shape memory spring is heated and urges a pin to a first or extended position. The pin may be supported in the first position by a supporting mechanism. The shape memory spring is heated electically, and in some embodiments under the control of a processor. The present invention may be used to display information provided in user interface from a computer program, including text, numerical data, and graphical images.

대표청구항 ▼

Various apparatus and methods for an actuator and display using one more shape memory springs. A shape memory spring is heated and urges a pin to a first or extended position. The pin may be supported in the first position by a supporting mechanism. The shape memory spring is heated electically, and

Various apparatus and methods for an actuator and display using one more shape memory springs. A shape memory spring is heated and urges a pin to a first or extended position. The pin may be supported in the first position by a supporting mechanism. The shape memory spring is heated electically, and in some embodiments under the control of a processor. The present invention may be used to display information provided in user interface from a computer program, including text, numerical data, and graphical images. d, will extend from the buccal side to the lingual side. 12. The instrument of claim 1 wherein a toe angle is formed by a first edge and a second edge both extending from the rounded point, such that lines co-linear with the first edge and the second edge intersect at an angle of 32°. 13. The instrument of claim 1 wherein at least one of the toe edge and the arch edge is a serrated edge. 14. The instrument of claim 13 wherein the serrated edge is comprised of a series of peaks separated by rounded valleys. 15. The instrument of claim 1 wherein the blade and the handle are stainless steel. 16. The instrument of claim 1 also comprising an inwardly curving ankle edge between the heel and the handle. 17. A instrument comprised of: an elongated handle having a first end and a second end; and a foot-shaped blade attached to the first end of the handle, the foot shaped blade having a top surface; a bottom surface, opposite the top surface; a heel shaped edge extending from the handle; an arch edge extending from the heel edge; a serrated toe edge extending from the arch edge, the toe edge forming a V-shape with a blunt point; and an instep edge extending from the toe edge to the handle; wherein the edges are all between the top surface and the bottom surface, the heel edge has an outwardly curved shape and the instep edge has an inwardly curved shape and the blade has a thickness and a length which enables the blade to be placed between adjacent teeth in a human mouth, which teeth have a buccal side and a lingual side, and the blade, when so placed, will extend from the buccal side to the lingual side. 18. The instrument of claim 17 wherein the arch edge is serrated. 19. The instrument of claim 17 wherein the arch edge is flat. A Aerospace Sciences Meeting and Exhibit. Nemo, NV, Jan. 11-14, 2001, pp. 92-102. Gonzalez et al., "An Experimental Study of Droop Leading Edge Modifications on High & Low Aspect Ratio Wings Up to 50° Angle of Attack", AIAA-93-3499-CP, 1993, pp 786-775. Stough et al., "Wing Modification for Increased Spin Resistance", SAE Technical Paper Series 830720, Apr. 12-15, 1983. Ross et al., "Tailoring Stall Characteristics Using Leading-Edge Droop Modifications", Journal of Aircraft, vol. 31, No. 4, Jul.-Aug. 1994, pp766-773. Staff, Langley Research Center, "Exploratory study of the effects of Wing-Leading-Edge Modifications on the Stall/Spin Behavior of a Light General Aviation Airplane", NASA TP-1589, 1979. Newsom et al., "Effects of Wing-Leading-Edge Modifications on a Full-Scale, Low-Wing General Aviation Airplane-Wind-Tunnel Investigation of High-Angle-of Attack Aerodynamic Characteristics", NASA TP-2011, 1982. Muri et al., "Wind-Tunnel Investigation of a Full-Scale General Aviation Airplane Equipped With an Advanced Natural Laminar Flow Wing", NASA TP-2722, 1987. Wortman et al., "Messungen an drei Flugelprofilen des Segelflugezeuges Ka 6", Vortrag am 8. OSTIV-Kongress, Jun. 1960, Kohn (and rough English translation). Ross et al., "Tailoring Stall Characteristics Using Leading-Edge Droop Modifications", Journal of Aircraft, Vo., 31, No. 4, Jul.-Aug., 1994. Stough et al., "Wing Modification for Increased Spin Resistance", Proc. Business Aircraft Meeting & Exposition, Wichita, Kanasa, Apr. 12-15, 1983. Gonzalez et al., "An Experimental Study of Droop Leading Edge Modifications on High & Low Aspect Ratio Wings Up to 50° Angle of Attack", AIAA paper 93-3496-CP, Proc. AIAA Applied Aerodynamics Conference, 11th,Monterey, CA, Aug. 9-11, 1993, p. 774-786. Stough et al., "Flight Investigation of the Effects of an Outboard Wing-Leading-Edge Modification on Stall/spin Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane", NASA TP-2691, Jul. 1987. Allison et al., Airfoil Modification Effects on Subsonic and Transoic Pressure Distributions and Performance for the EA-6B Airplane, NASA TP-3516, May 1995, pp. 84. Berak, "Aerodynamic modification of MS airfoil sections", Zpravodaj VZLU Issue; 5, p. 253-267 Jan. 01, 1990 11. (abstract enclosed). Hicks et al., "Effects of upper surface modification on the aerodynamic characteristics of the NACA 63 sub 2-215 airfoil section", NASA-TM-78503 A-7507, Jan. 01, 1979. Hicks, et al., "Effects of forward contour modification on the aerodynamic characteristics of the NACA 641-2