| タイトル | Shearographic non-destructive evaluation of the Space Shuttle |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960028755 |
| 著者（英） | Hooker, Jeffery A.; Davis, Christopher K.; Tenbusch, Kenneth E.; Simmons, Stephen M. |
| 著者所属（英） | NASA |
| 発行日 | 1995-12-08 |
| 言語 | eng |
| 内容記述 | Preliminary results of shearographic inspections of the shuttle external tank (ET) spray-on foam insulation (SOFI) and solid rocket booster (SRB) Marshall sprayable ablative (MSA-2) epoxy-cork thermal protection systems (TPS) and remote manipulator system (RMS) honeycomb are presented. Debonding SOFI or MSA-2 damage the orbiter belly tile and exposes the ET/SRB to thermal loading. Previous work with the ET/SRB showed promising results with shearography. The first area investigated was the jack pad close-out, one of many areas on the ET where foam is applied at KSC. Voids 0.375 inch were detected in 1.75 inch thick foam using a pressure reduction of less dm 0.4 psi. Of primary interest are areas of the ET that directly face the orbiter tile TPS. It is estimated that 90% of tile TPS damage on the orbiter 'belly' results from debonding SOFI during ascent. Test panels modeling these areas were manufactured with programmed debonds to determine the sensitivity of shearography as a function of debond size, SOFI thickness, and vacuum. Results show a Probability of Detection (POD) of .95 or better for of debonds with a diameter equal to the SOFI thickness at less than 0.4 psi pressure reduction. Preliminary results are also presented on inspections of MSA-2 and the remote manipulator system (RMS) honeycomb material. |
| NASA分類 | Space Transportation |
| レポートNO | 96N29423
NASA-TM-111441
NAS 1.15:111441 |
| 権利 | No Copyright |
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