Titanium anodize to control thermal radiation with solar absorbance and emittance applications.
Resistivity is 4.5 Ohms per square inch. Can be used as an antigalling coating on titanium surfaces lubricated with oils, greases, hydraulic fluids, or in pneumatic systems.
Black emissivity coating.
Coating to control thermal radiation with solar absorbance and emittance applications.
High temperature version of Ultra VE-17.
Used on BK-11and Tiodize Type I to harden coating for high durability and handling.
Used to control IR reflectance on aluminum.
The ratio of the radiation intensity from a surface to the radiation intensity at the same wavelength from a blackbody at the same temperature.
The Western Development Laboratories Division (WDL) of Ford Aerospace Communications Corporation (FACC) was chosen by the Government of India to design and build the first generation spacecraft for the Indian National Satellite System … INSAT-1. This spacecraft will introduce sociological and economical advantages of modern communications to India’s population which exceeds 613,000,000 and covers a land area measuring 3,280,483 square kilometers. INSAT-1 will provide reliable communication capability to India’s rugged terrain and inaccessible regions far more economically than any alternative high quality terrestrial system.
To accomplish the satellite’s major communications, direct broadcast satellite service, meteorology and data collection missions, it will be placed in geostationary orbit 35,784 Km above India and will employ a single 445-newton (100 pound) thruster for apogee boost. During design and development of the thruster at WDL, protection of adjacent structure against the plume was considered necessary. Titanium was the best lightweight choice for a shield, provided the thermal absorptivity/emissivity of less than 1.0 could be achieved. The TIODIZE Type I Process has these characteristics, and samples of 6Al-4V titanium were coated by TIODIZE Co., Inc. and evaluated by WDL utilizing the Gier Dunkle Source Transfer Optical System. Subsequently, preformed parts of the flight hardware were coated, and test samples were processed with the parts to verify thermal characteristics. Results of WDL tests on these test samples are presented below:
Since the desired as/´n of less than 1.0 was achieved by the single coating, the heavier coating used to achieve the very low ratio was not used for production hardware. For additional testing, see page 12 of the Tiodize Process Booklet.
Another significant use for the TIODIZE PROCESS is the control of thermal radiation. The solar absorptance (as) and normal emittance (´n) for ULTRA V-E17 and bare Type I and II TIODIZE PROCESS coatings were found to be as shown below:
|AS/EN||TYPE I Bare||Ultra V-EI7||TYPE II BARE|
|A||TIODIZE Type II all over Ultra VE-17 one side No Top Coat||Black||0.928 / 0.923||No Loss|
|B||Same as A, except with Top Coat||Black||0.936 / 0.934||No Loss|
|C||TIODIZE Type I all over Ultra VE-17 one side No Top Coat||Black||0.946 / 0.947||No Loss|
|D||Same as C, except with Top Coat||Black||0.95 / 0.951||No Loss|
|E||TIODIZE Type I all over +K-seal||Tan||0.932 / 0.946||Some loss on side 1 of each panel; No loss on reverse side of each panel.|
The specimens were made of Titanium 6Al-4V foil, .005 inches in thickness, and TIODIZED with Type I and Type II. The ULTRA V-E17, when used, was TIODIZE® black organic coating. The absorptance was determined by the 19 point integration between 0.32 and 2.1 microns wavelength. The emittance was arrived at by a 25 point integration between 4.8 and 26.2 microns. Spectral measurements were made in either a heated Hohlraum chamber or a Gierdunkle integrating sphere with an incident angle of 20 degrees on specimens water cooled to approximately room temperature.