Measurements report - Thermal property measurements of Manned Spacecraft Center spacesuit materials
Thermal emittance from quarter-mil aluminized Kapton space suit material and from sun and protective visors
Turnbow, F. J.↗
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The thermal conductivity of two thermal insulating materials Final report
Test methods and procedures to determine thermal conductivity of polyurethane foam and aluminized Mylar
Tye, R. P.↗
An experimental study of the effects of particle cloud impingement.
Particle clouds impingement effects, analyzing damages produced by exhaust from aluminized solid propellant rocket motors
Kuby, W. C.↗
A method for reducing the equivalent sink temperature of a vertically oriented radiator on the lunar surface
Aluminized plastic covers to reduce radiator sink temperatures on lunar surface
Bien, D. D.↗
Photographic study of solid propellants burning in an acceleration environment Final report
Acceleration effects on aluminized composite solid propellants combustion by high speed color cinematography
Baker, K. L.↗
Evaluation of two designs for cryogenic insulation
Shingle-type, crinkled, aluminized polyethylene ester is thermally and structurally tested for cryogenic insulation. Insulation systems require thermal efficiency with minimum weight, and the ability to withstand vibration, acceleration, and rapid pressure drops.
Getty, R. C.↗
Lightweight, self-evacuated insulation panels
Multilayer insulation of prefabricated panels is developed for cryogenic storage tanks. System utilizes panels of aluminized Mylar separated by sheets of low conductivity polyurethane foam. Panels are self-evacuated by cryopumping of gaseous carbon dioxide at time of use.
Dengler, R. P.↗
NASA-tricot - A lightweight radar reflective, knitted fabric
Fabric knitted on conventional knitting machines uses commercially available yarns, has high aerodynamic drag capability, and is relatively inexpensive. The two yarn components used are 15-denier nylon monofilament and aluminized Mylar tape.
Matthews, F. R.↗
Lightweight modular multilayer insulation Final report
Self evacuating multilayer insulation system of aluminized Mylar and polyurethane foam for liquid hydrogen tanks
Nies, G. E.↗
Superior cryogenic insulation developed
Multilayer composite consisting of alternate spunbond nylon layers and doubly aluminized mylar layers is used primarily in cryogenic thermal protection systems.
Hale, D. V.↗
Alloyed coatings for dispersion strengthened alloys
Processing techniques were developed for applying several diffusion barriers to TD-Ni and TD-NiCr. Barrier coated specimens of both substrates were clad with Ni-Cr-Al and Fe-Cr-Al alloys and diffusion annealed in argon. Measurement of the aluminum distribution after annealing showed that, of the readily applicable diffusion barriers, a slurry applied tungsten barrier most effectively inhibited the diffusion of aluminum from the Ni-Cr-Al clad into the TD-alloy substrates. No barrier effectively limited interdiffusion of the Fe-Cr-Al clad with the substrates. A duplex process was then developed for applying Ni-Cr-Al coating compositions to the tungsten barrier coated substrates. A Ni-(16 to 32)Cr-3Si modifier was applied by slurry spraying and firing in vacuum, and was then aluminized by a fusion slurry process. Cyclic oxidation tests at 2300 F resulted in early coating failure due to inadequate edge coverage and areas of coating porosity. EMP analysis showed that oxidation had consumed 70 to 80 percent of the aluminum in the coating in less than 50 hours.
Wermuth, F. R.↗
Development of oxidation resistance in thoriated nickel-chromium base alloys
A pack process was developed which permits the introduction of nearly six weight percent aluminum into solid solution in the near-surface region of TDNiCr (Ni-20Cr-2ThO2. At this aluminum concentration an adherent alumina scale is produced on the alloy surface upon exposure to an environment of 1330 n/sq m (10 torr) or 101,000 n/sq m (760 torr) air at temperatures of 1093 C (2000 F) and 1204 C (2200 F). Room temperature mechanical properties of the aluminized alloys compare favorably with those of TDNiCr as received. While diffusivities for aluminum are a factor of three higher than those for chromium in TDNiCr or Ni-20Cr, the diffusion rates are similar for either of these elements in the thoriated or unthoriated alloy for a given temperature and grain size.
Seltzer, M. S.↗
Hibonite, Ca2/Al, Ti/24O38, from the Leoville and Allende chondritic meteorites.
Hibonite was discovered in light-colored, Ca-Al-Ti-rich and Si-Fe-poor, achondritic inclusions of the Leoville and Allende HL-group chondrites. Two varieties of hibonite occur: one emits a bright red-orange luminescence under electron bombardment and has high amounts of Al2O3 (87.7; 87.9) and low amounts of MgO (0.65; 0.8) and TiO2 (0.68; 0.8). The other emits a bright blue luminescence and is low in Al2O3 (78.7; 79.2) and high in MgO (3.3; 3.7) and TiO2 (6.5; 7.9) (in wt. %). The oxide CaO is about the same in both varieties. It is suggested that the change in the color of the visible luminescence results from changes in composition. The origin of hibonite which occurs in complex mineral assemblages together with anorthite, gelhenite, wollastonite, aluminous diopside, andradite, Ca-pyroxene, perovskite, spinel, taenite, chromite, and pentlandite, and in close proximity to nodules containing calcite, whewellite, forsterite and many of the aforementioned phases, is discussed. The proposition that hibonite and associated phases originated by contact metamorphism and metasomatism of calcite-dolomite bearing assemblages cannot, at this time, be completely ruled out.
Keil, K.↗
Development of the Algol III solid rocket motor for SCOUT.
The design and performance of a motor developed for the first stage of the NASA SCOUT-D and E launch vehicles are discussed. The motor delivers a 30% higher total impulse and a 35 to 45% higher payload mass capability than its predecessor, the Algol IIB. The motor is 45 in. in diameter, has a length-to-diameter ratio of 8:1 and delivers an average 100,000-lb thrust for an action time of 72 sec. The motor design features a very high volumetrically loaded internal-burning charge of 17% aluminized polybutadiene propellant, a plasma-welded and heat-treated steel alloy case, and an all-ablative plastic nose liner enclosed in a steel shell. The only significant development problem was the grain design tailoring to account for erosive burning effects which occurred in the high-subsonic-Mach-number port. The tests performed on the motor are described.
Felix, B. R.↗
Oxidation resistant claddings for superalloys.
The oxidation protection afforded IN-100 and WI-52 superalloys by thin claddings of NiCrAlSi and FeCrAlY alloys was examined primarily at 1090 C. Comparisons were made with commercial aluminide coatings using cyclic furnace and high velocity burner rig tests. In furnace tests, NiCrAlSi on IN-100 and FeCrAlY on WI-52 performed as well or better than two aluminide coatings. Burner rig performance of the FeCrAlY cladding was better than that of the NiCrAlSi cladding on IN-100 and the aluminide coating on WI-52, but less than the aluminide coating on IN-100. An aluminized NiCrAlSi cladding performed better than any coating or cladding.
Gedwill, M. A.↗
Infrared radiation of thin plastic films.
A combined analytical and experimental study is presented for infrared radiation characteristics of thin plastic films with and without a metal substrate. On the basis of the thin-film analysis, a simple analytical technique is developed for determining band-averaged optical constants of thin plastic films from spectral normal transmittance data for two different film thicknesses. Specifically, the band-averaged optical constants of polyethylene terephthalate and polyimide were obtained from transmittance measurements of films with thicknesses in the range of 0.25 to 3 mil. The spectral normal reflectance and total normal emittance of the film side of singly aluminized films are calculated by use of optical constants; the results compare favorably with measured values.
Tien, C. L.↗
Oxidation resistant claddings for superalloys.
The oxidation protection afforded IN-100 and WI-52 superalloys by thin claddings of NiCrAlSi and FeCrAlY alloys was examined primarily at 1090 C. Comparisons were made with commercial aluminide coatings, using cyclic furnace and high-velocity burner rig tests. In furnace tests, NiCrAlSi on IN-100 and FeCrAlY on WI-52 performed as well as or better than two aluminide coatings. Burner rig performance of the FeCrAlY cladding was better than that of the NiCrAlSi cladding on IN-100 and the aluminide coating on WI-52, but less than the aluminide coating on IN-100. An aluminized NiCrAlSi cladding performed better than any coating or cladding.
Gedwill, M. A.↗
Effects of overlaps, stitches, and patches on multilayer insulation.
The effects of spacecraft installation-type discontinuities on aluminized Mylar multilayer insulation have been measured using an electrically heated cylindrical calorimeter. The experimental results have been reproducible within plus or minus 10% or better for identical blankets and less than plus or minus 5% for the same blanket. Good blanket performance can be obtained using short interleaving for joints, eliminating stitched seams, and using small patches, particularly over the hot side of stitches. The heat loss through stitching is excessive but highly localized. Analytical models matched to thermocouple test results are presented. The manner in which radiation and conduction participate in heat transfer adjacent to discontinuities is indicated. High lateral heat transfer is also established as an important phenomenon in the vicinity of a discontinuity.
Stimpson, L. D.↗