Claims
- 1. A coated article, comprising:
- a substrate having a surface; and
- a white coating on the surface of the substrate, the coating comprising
- a matrix comprising a silica/silicate transformation product of a ceramic precursor, and
- a plurality of doped zinc oxide pigment particles distributed in the matrix, the zinc oxide pigment particles being doped with an element that forms shallow donorlike states in the zinc oxide.
- 2. The coated article of claim 1, wherein the substrate is a spacecraft thermal radiator.
- 3. The coated article of claim 1, wherein the ceramic precursor comprises a silicone.
- 4. The coated article of claim 1, wherein the ceramic precursor comprises a microfiber.
- 5. The coated article of claim 1, wherein the silica/silicate transformation product comprises a mass of bonded and interlocked microfibers.
- 6. The coated article of claim 1, wherein the coating has a thickness of no less than about 0.002 inches.
- 7. The coated article of claim 1, wherein the coating has a thickness of from about 0.002 inches to about 0.005 inches.
- 8. The coated article of claim 1, wherein the zinc oxide is doped with an element from the group consisting of aluminum, gallium, indium, boron, zinc, tin, and hydrogen.
- 9. The coated article of claim 1, wherein the zinc oxide is doped with aluminum.
- 10. The coated article of claim 1, wherein the ratio of doped zinc oxide pigment particles:silica/silicate transformation product is from about 3:1 to about 4:1 parts by weight.
- 11. The coated article of claim 1, wherein the coating has a solar absorptance of from about 0.2 to about 0.3 and a surface electrical resistivity of from about 1.times.10.sup.6 ohms per square to about 1.times.10.sup.8 ohms per square.
- 12. A coated article, comprising:
- a substrate having a surface; and
- a white coating having a thickness of at least about 0.002 inches on the surface of the substrate, the coating comprising
- a matrix comprising a mass of bonded and interlocked silica/silicate microfibers formed as a transformation product of a silicone microfiber precursor, and
- a plurality of doped zinc oxide pigment particles distributed in the matrix, the zinc oxide pigment particles being doped with an element that forms shallow donorlike states in the zinc oxide.
- 13. The coated article of claim 12 wherein the coated article is a spacecraft thermal radiator.
- 14. The coated article of claim 12, wherein the coating has a thickness of from about 0.002 inches to about 0.005 inches.
- 15. The coated article of claim 12, wherein the ratio of doped zinc oxide pigment particles:silica/silicate microfibers is from about 3:1 to about 4:1 parts by weight.
- 16. A coated article, comprising:
- a substrate having a surface; and
- a white coating on the surface of the substrate, the coating comprising
- a matrix comprising a mass of bonded and interlocked microfibers, and
- a plurality of doped zinc oxide pigment particles distributed in the matrix, the zinc oxide pigment particles being doped with an element that forms shallow donorlike states in the zinc oxide.
- 17. A method for coating an article, comprising the steps of
- furnishing a substrate having a surface;
- furnishing a coating mixture comprising a ceramic precursor, a carrier, and a plurality of doped zinc oxide pigment particles, the zinc oxide pigment particles being doped with an element that forms shallow donorlike states in the zinc oxide
- applying the mixture to the surface of the substrate; and
- curing the mixture to evaporate the carrier and to transform the ceramic precursor to a silica/silicate transformation product, thereby forming a coating bonded to the surface of the substrate.
- 18. The method of claim 17, wherein the ceramic precursor comprises a silicone.
- 19. The method of claim 17, wherein the ceramic precursor comprises microfibers.
- 20. The method of claim 17, wherein the coating has a thickness of no less than about 0.002 inches.
Parent Case Info
This application is a continuation-in-part of application Ser. No. 08/717,443, filed Sept. 20, 1996, now U.S. Pat. No. 5,770,269 for which priority is claimed; which is a division of application Ser. No. 08/242,201, filed May 13, 1994, now U.S. Pat. No. 5,589,274, for which priority is claimed.
US Referenced Citations (21)
Foreign Referenced Citations (1)
Number |
Date |
Country |
0558044 |
Feb 1992 |
EPX |
Non-Patent Literature Citations (5)
Entry |
Anon., Technical Data Sheet RS 103 on "White Antistatic Paint SGC21", Feb. 1991. |
Cheng Hsieh et al., "Conductive White Thermal Control Paint for Spacecraft," Proc. 38th International SAMPE Symposium, pp. 609-622, May 10-13 1993. |
J. Cordaro et al., "Molecular Engineering of Pigments for Degradation-Resistant Thermal Control Coatings", AIAA Reprint AIAA-92-2167 of Presentation of AIAA Materials Specialist Conference on Coating Technology for Aerospace Systems, pp. 85-87, Apr. 16-17, 1992. |
Derwent Publication (Database WPI); AN 84-065980; JP-A-59022054 (Ricoh); 2 Feb. 1984; Abstract. |
Derwent Publication (Database WPI); AN 88-224490; JP-A-63159865 (Ricoh); 2 Jul. 1988; Abstract. |
Divisions (1)
|
Number |
Date |
Country |
Parent |
242201 |
May 1994 |
|
Continuation in Parts (1)
|
Number |
Date |
Country |
Parent |
717443 |
Sep 1996 |
|