1. A bendable and twistable support member, comprising:
a plurality of first cap-shaped elements, wherein each of said plurality of first cap-shaped elements comprises an opening end and a semispherical top end which has a central hole, the semispherical top end of one first cap-shaped element being inserted into the opening end of another first cap-shaped element such that said plurality of first cap-shaped elements are stacked together;
a string passing through the central hole on each of said stacked plurality of first cap-shaped elements to tie up them from being undetachable.
2. The bendable and twistable support member of claim 1, further comprising a second cap-shaped element, which comprises an opening end and a semispherical top end having a central hole, wherein the opening end of the second cap-shaped element is inserted into the opening end of an outest first cap-shaped element of said plurality of first cap-shaped elements to form a stack, and the string further passes through the central hole of the second cap-shaped element to tie up it with said plurality of first cap-shaped elements.
3. The bendable and twistable support member of claim 2, further comprising two stoppers provided on two opposite terminals of the support member, wherein the two stoppers are connected to two ends of the string respectively, and the two stoppers have a size larger than a diameter of the central hole.
4. The bendable and twistable support member of claim 1, wherein each of the plurality of cap-shaped elements is a metal cap.
5. The bendable and twistable support member of claim 1, wherein the string comprises a metal wire.
6. A toy animal, comprising at least one support member coated with an outer fabric cover for simulating an appendage of the toy animal, wherein the support member comprises:
a plurality of first cap-shaped elements, wherein each of said plurality of first cap-shaped elements comprises an opening end and a semispherical top end which has a central hole, the semispherical top end of one first cap-shaped element being inserted into the opening end of another first cap-shaped element such that said plurality of first cap-shaped elements are stacked together;
a string passing through the central hole on each of said stacked plurality of first cap-shaped elements to tie up them from being undetachable.
7. The toy animal of claim 1, wherein the support member further comprises a second cap-shaped element, which comprises an opening end and a semispherical top end having a central hole, wherein the opening end of the second cap-shaped element is inserted into the opening end of an outest first cap-shaped element of said plurality of first cap-shaped elements to form a stack, and the string further passes through the central hole of the second cap-shaped element to tie up it with said plurality of first cap-shaped elements.
8. The toy animal of claim 7, wherein the support member further comprises two stoppers provided on two opposite terminals of the support member, wherein the two stoppers are connected to two ends of the string respectively, and the two stoppers have a size larger than a diameter of the central hole.
9. The toy animal of claim 1, wherein each of the plurality of cap-shaped elements is a metal cap.
10. The toy animal of claim 1, wherein the string comprises a metal wire.
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 transparency comprising a glass piece, the glass piece comprising:
a chemically tempered first major surface and an opposite second major surface;
a case depth, wherein the case depth is defined as a distance from the first major surface of the glass piece toward the second major surface, the distance ending at a position within the glass piece at which the glass piece has is zero stress, and
a tensile stress zone within the glass piece at a depth from the first major surface greater than the distance of the case depth from the first major surface, wherein glass in the tensile stress zone has a glass composition comprising:
Ingredient
Percent by weight
SiO2
60 to 75;
Al2O3
in the range selected from the group
of 18 to 29; 18 to 28, 19 to 28.5, and
20 to 25;
Li2O
3 to 9; and
ZrO2
0 to 3;
where percent by weight (\u201cwt %\u201d) of Al2O3+ZrO2 is in the range selected from the group of 18 to 28 wt %, 19 to 27 wt %, 20 to 26 wt %, 18 to 29 wt %, 19 to 28.5 wt % and 20 to 26 wt %, and wherein the glass in the tensile stress zone has at least one of the following properties: (a) a log 10 viscosity temperature of at least 1280\xb0 F. (694\xb0 C.) and (b) a liquidus temperature of at least 2350\xb0 F. (1288\xb0 C.).
2. The aircraft transparency according to claim 1, wherein the glass in the tensile stress zone has a log 10 viscosity in the temperature range of 1328\xb0 F. (720\xb0 C.) to 1499\xb0 F. (815\xb0 C.); a liquidus temperature in the \xb0 temperature range of 2437\xb0 F. (1336\xb0 C.) to 2575\xb0 F. (1413\xb0 C.), and a log 7.6 softening point temperature in the temperature range of 1544\xb0 F. (840\xb0 C.) to 1724\xb0 F. (940\xb0 C.).
3. The aircraft transparency according to claim 2, wherein the glass piece has at least one of the following properties: a case depth in the range of 7 to 13.3 mils, an abraded modulus of rupture in the range of 72 to 78.6 thousand pounds per square inch (\u201cKPSI\u201d), a modulus of rupture in the range of 76 to 106 KPSI, a center tension in the range of 6.1 to 103 KPSI, a center tension area in the range of 554 to 1033 poundsinch, a Vickers hardness 1000 in the range of 600 to 614 kilograms per square millimeter (\u201ckgmm2\u201d), and a Knoop hardness 1000 in the range of 503 to 526 kgmm2.
4. The aircraft transparency according to claim 2, wherein the glass piece has at least one of the following properties: a case depth in the range of 11.5 to 17.4 mils, an abraded modulus of rupture in the range of 77 to 78 thousand pounds per square inch (\u201cKPSI\u201d), a modulus of rupture in the range of 71 to 112 KPSI, center tension in the range of 6.1 to 10.3 KPSI, a center tension area in the range of 749 to 1080 poundsinch, a Vickers hardness 1000 in the range of 598 to 606 kilograms per square millimeter (\u201ckgmm2\u201d), and a Knoop hardness 1000 in the range of 505 to 522 kgmm2.
5. The aircraft transparency according to claim 1, wherein the case depth is a first case depth and further comprising a second case depth, wherein the tensile stress zone is between the first and the second case depths, and the second case depth is defined as a distance from the second major surface of the glass piece toward the first major surface and ending at a position within the glass piece at which there is zero stress.
6. The aircraft transparency according to claim 5, wherein the glass piece submerged into a container of boiling 0.50 wt % sulfuric acid for 30 minutes has weight loss in the range of 0.002 to 0.014 milligrams per square centimeter-hour.
7. The aircraft transparency according to claim 1 further comprising a mounting frame wherein the glass piece is secured in the mounting frame.
8. The aircraft transparency according to claim 7, wherein the case depth is a first case depth and further comprising a second case depth, wherein the tensile stress zone is between the first and the second case depths, and the second case depth is defined as a distance from the second major surface of the glass piece toward the first major surface and ending at a position within the glass piece at which there is zero stress.
9. An aircraft transparency comprising a glass piece, the glass piece comprising:
a chemically tempered first major surface and a chemically tempered opposite second major surface;
a first case depth and a second case depth, wherein the first case depth is defined as a first distance from the first major surface of the glass piece toward the second major surface, the first distance ending a first position within the glass piece at which there is zero stress and the second case depth is defined as a second distance from the second major surface of the glass piece toward the first major surface, the second distance ending a second position within the glass piece at which there is zero stress, wherein the first position is spaced from the second position, and
a tensile stress zone defined as interior glass, wherein the interior glass is within the glass piece between the first and the second positions, wherein the interior glass has a glass composition comprising:
Ingredient
Percent by weight
SiO2
60 to 75;
Al2O3
18 to 28; and
Li2O
3 to 9;
wherein the glass composition has at least one of the following properties (a) a log 10 viscosity temperature of at least 1413\xb0 F. and (b) a liquidus temperature of at least 2436\xb0 F.
10. The aircraft transparency according to claim 9, wherein the glass within the first case depth has a lower concentration of lithium than the interior glass.
11. The aircraft transparency according to claim 9, wherein the first distance is in the range of 7 to 16.5 mils.
12. The aircraft transparency according to claim 9, wherein the glass composition of the interior glass comprises:
Ingredient
Percent by weight
SiO2
64.83 to 69.29;
Al2O3
21.97 to 23.51;
Li2O
4.94 to 6.50;
Na2O
0.39 to 2.00; and
K2O
0.07 to 0.10;
where the combined percent by weight (\u201cwt %\u201d) of Na2O and K2O is in the range of 0.49 to 2.07 wt %.
13. The aircraft transparency according to claim 12, wherein the glass piece has a center tension in the range of 5,700 to 14,900 pound per square inch.
14. The aircraft transparency according to claim 12, wherein the glass piece has a center tension area in the range of 632 to 979 pounds per inch.
15. The aircraft transparency according to claim 12, wherein the glass piece has a modulus of rupture in the range of 71,000 to 112,000 pounds per square inch.
16. The aircraft transparency according to claim 12, wherein the glass piece has a Vicker’s hardness 1000 in the range of 586 to 614 kilograms per square millimeters measured on one of the major surfaces.
17. The aircraft transparency according to claim 9 further comprising a mounting frame wherein the glass piece is a layer of a laminate and the laminate is secured in the mounting frame.
18. A method of chemically strengthening a glass piece, comprising:
providing a glass piece having a predetermined shape and thickness and a composition comprising:
Ingredient
Percent by weight
SiO2
60 to 75;
Al2O3
18 to 28;
Li2O
3 to 9;
Na2O
0 to 3;
K2O
0 to 0.5;
CaO
0 to 3;
MgO
0 to 3;
SO3
0 to 0.20;
Total iron expressed as Fe2O3
0 to 1.25;
ZrO2
0 to 3;
Total tin expressed as SnO2
0 to 0.70;
TiO2
0 to 5;
P2O5
0 to 1.75;
ZnO
0 to 1.25; and
B2O3
0 to 1.75;
where weight percent (\u201cwt %\u201d) of CaO+MgO is in the range of 0 to 6 wt %, wt % of Al2O3+ZrO2 is in the range of 18 to 28 wt %, and wt % of Na2O+K2O is in the range of 0.05 to 3.00 wt %, wherein the glass piece has a log 10 viscosity temperature of at least 1413\xb0 F. and a liquidus temperature of at least 2435\xb0 F.;
submerging the glass piece in a molten sodium nitrate bath heated to a temperature of greater than 300\xb0 F. (149\xb0 C.) for at least 8 hours to provide the glass piece with a case depth in the range of 7 to 16.5 mils, and
removing the glass piece from the bath.
19. The method according to claim 18, wherein the chemically tempered glass piece has at least one of the following properties:
glass within the case depth has a lower concentration of lithium than glass within the glass piece and outside of the case depth;
the glass piece has a case depth in the range of 7 to 16.5 mils (0.17 to 0.419 millimeters);
center tension in the glass piece is in the range of 5,700 to 14,900 pounds per square inch (39 to 103 mega Pascal (\u201cmPa\u201d)).
the glass has a center tension area (\u201cCTA\u201d) in the range of 632 to 1,390 pounds per inch (113 to 248 kilograms per centimeter);
the glass piece has a modulus of rupture in the range of 76,000 to 120,000 pounds per square inch (524 to 827 mPa);
the glass piece has an abraded modulus of rupture in the range of 67,000 to 89,000 pounds per square inch (462 to 614 mPa);
the glass piece has a HV (Vicker’s hardness) 1000 in the range of 586 to 614 kilograms force per square millimeters; and
the glass piece has an HK (Knoop’s hardness) 1000 in the range of 503 to 529 kilograms force per square millimeters.
20. The method according to claim 18 further including mounting the chemically tempered glass piece in an aircraft transparency mounting frame.