Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

A thermochemical cure model for predicting temperature and degree of cure profiles in curing phenolic parts was developed,
validated and refined over several years. The model supports optimization of cure cycles and allows input of properties based upon
the types of material and the process by which these materials are used to make nozzle components. The model has been refined
to use sophisticated computer graphics to demonstrate the changes in temperature and degree of cure during the curing process.
The effort discussed in the paper will be the conversion from an outdated solid modeling input program and SINDA analysis code
to an integrated solid modeling and analysis package (I-DEAS solid model and TMG). Also discussed will be the incorporation
of updated material properties obtained during full scale curing tests into the cure models and the results for all the Reusable Solid
Rocket Motor (RSRM) nozzle rings.
Author
Curing; Thermal Analysis; Upgrading
20000064704 Saclay Research Centre, Direction des Sciences de la Matiere, Gif-sur-Yvette, France
In situ study of glasses decomposition layer
Zarembowitch-Deruelle, O.; Oct. 21, 1997; 186p; In French; In English
Report No.(s): DE99-609730; FRCEA-TH-631; No Copyright; Avail: Department of Energy Information Bridge
The aim of this work is to understand the involved mechanisms during the decomposition of glasses by water and the consequences
on the morphology of the decomposition layer, in particular in the case of a nuclear glass: the R(sub 7) T(sub 7). The
chemical composition of this glass being very complicated, it is difficult to know the influence of the different elements on the
decomposition kinetics and on the resulting morphology because several atoms have a same behaviour. Glasses with simplified
composition (only 5 elements) have then been synthesized. The morphological and structural characteristics of these glasses have
been given. They have then been decomposed by water. The leaching curves do not reflect the decomposition kinetics but the
solubility of the different elements at every moment. The three steps of the leaching are: (1) de-alkalinization (2) lattice rearrangement
(3) heavy elements solubilization. Two decomposition layer types have also been revealed according to the glass heavy elements
rate.
NTIS
Decomposition; Borosilicate Glass
20000064928 Thiokol Corp., Brigham City, UT USA
Thermal Characterization of Adhesive
Spomer, Ken A., Thiokol Corp., USA; [1999]; 12p; In English; 32nd; 32nd International SAMPE Technical Conference, 21-25
May 2000, Long Beach, CA, USA; Sponsored by Society for the Advancement of Materials and Process Engineering, USA
Contract(s)/Grant(s): NAS8-97238; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche
The current Space Shuttle Reusable Solid Rocket Motor (RSRM) nozzle adhesive bond system is being replaced due to
obsolescence. Down-selection and performance testing of the structural adhesives resulted in the selection of two candidate
replacement adhesives, Resin Technology Group’s Tiga 321 and 3M’s EC2615XLW. This paper describes rocket motor testing
of these two adhesives. Four forty-pound charge motors were fabricated in configurations that would allow side by side comparison
testing of the candidate replacement adhesives and the current RSRM adhesives. The motors provided an environment where
the thermal performance of adhesives in flame surface bondlines was compared. Results of the FPC testing show that: 1) The phenolic
char depths on radial bond lines is approximately the same and vary depending on the position in the blast tube regardless
of which adhesive was used; 2) The adhesive char depth of the candidate replacement adhesives is less than the char depth of the
current adhesives; 3) The heat-affected depth of the candidate replacement adhesives is less than the heat-affected depth of the
current adhesives; and 4) The ablation rates for both replacement adhesives are slower than that of the current adhesives.
Author
Adhesives; Space Shuttle Boosters; Rocket Engines; Performance Tests; Bonded Joints; Resins
20000065642 NASA Glenn Research Center, Cleveland, OH USA
International Test Program for Synergistic Atomic Oxygen and VUV Exposure of Spacecraft Materials
Rutledge, Sharon, NASA Glenn Research Center, USA; Banks, Bruce, NASA Glenn Research Center, USA; Dever, Joyce, NASA
Glenn Research Center, USA; Savage, William, Cleveland State Univ., USA; May 2000; 14p; In English; 8th; 5th; Materials in
a Space Environment, 5-9 Jun. 2000, Arcachon, Arcachon, France, France; Sponsored by Centre National d’Etudes Spatiales,
France
Contract(s)/Grant(s): RTOP 632-6A-1E
Report No.(s): NASA/TM-2000-210054; E-12255; NAS 1.15:210054; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche
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