FRSI Blanket (Nomex Felt)

Name: FRSI Blanket (Nomex Felt)
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Reusable Composites: Composite Flexible Blankets
Composition: Aramid fibers, white RTV elastomer (e.g. Dow Corning DC92-007)
Manufacturer: Albany International
Technical Readiness Level: 9
Last Modified: 2001-10-01

Description:

  • FRSI is a heat-treated Nomex felt blanket with an OML (outer mold line) layer of white RTV silicone elastomer. For shuttle orbiter applications, FRSI varies in thickness from 0.16 to 0.40 inch depending on the heat load encountered during re-entry. FRSI is bonded directly to the orbiter skin using a RTV silicone adhesive. The white RTV coating is used to waterproof the felt and provide the required thermal and optical properties. The coating is vented using 0.035Ó holes on six inch centers. FRSI covers nearly 50 percent of the orbiter's upper surfaces due to its light weight and the relatively low temperatures and heating rates encountered on the leeward (upper) surfaces.

Point of Contact:

  • Marc Rezin
  • NASA Ames Research Center
  • mrezin@mail.arc.nasa.gov

Pictures:

Properties at Standard Conditions
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Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density 8.65e+01 kg/m^3 4.32 unknown assumed/assumed 2 2006-01-05
Thermal Conductivity (Isotropic)1 4.06e-02 W/m-K 1.85e-03 unknown interpolated(T) 2 2006-01-05
Specific Heat 1.31e+03 J/kg-K 65.3 unknown TRUE 2 2006-01-05
Emissivity 0.8 - 0.04 unknown true/assumed 2 2006-01-05
Multiple Use Temperature Limit 5.06e+02 K 25.3 predicted assumed/assumed 2 2006-01-05
Single Use Temperature Limit 6.44e+02 K 32.2 predicted assumed/assumed 2 2006-01-05
Purchase Cost 1.72e+03 $/m^2 86.1 predicted assumed/assumed 1 2006-01-05
Installation Time 2.13e+04 s/m^2 1.07e+03 predicted assumed/assumed 1 2006-01-05
Inspection/Repair Time per Flight 3.49e+03 s/m^2 1.74e+02 predicted assumed/assumed 1 2006-01-05
Replacement Fraction per Flight 2.80e-02 - 1.40e-03 predicted assumed/assumed 1 2006-01-05
Reuse Flight Limit (# of flights) 0.0 - N/A unknown assumed/assumed 1 2006-01-05

Notes:

  • 1. Nomex felt thermal conductivity.

Property References:

  • 1. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 2. anon: Space Shuttle Program Thermodynamic Design Data Book. Penetrations.:SD73-SH-0226:Rockwell International, Downey, CA:Jan. 1981:TPSX Ref. #23.

General References:

  • 1. S. Amanda Chiu, William C. Pitts: Reusable Surface Insulations for Reentry Spacecraft:AIAA Paper 91-0695:Jan. 1991:TPSX Ref. #3.
  • 2. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 3. C. Ehrlich, et al.: Advanced Manned Launch System Study (AMLS); Reusable Cyrogenic Tank Design:Contract NAS1-18975 DRD-9:Rockwell International, Space Systems Division, Downey, CA:Jul.-Sep. 1993:TPSX Ref. #8.
  • 4. anon: Current Technology for Thermal Protection Systems:NASA Conf. Pub. 3157:Feb. 1992:TPSX Ref. #9.
  • 5. D.A. Kourtides, S.A. Chiu, D.J. Iverson, D.M. Lowe: Thermal Response of Rigid and Flexible Insulations and Reflective Coating in an Aeroconvective Heating Environment:NASA TM-103925:Mar. 1992:TPSX Ref. #26.
  • 6. D.A. Kourtides, J.L. Bandfield, N. Pakrasi, W.C. Pitts: Effect of Ceramic Coatings on Thermal Performance of Flexible Insulations:26th International SAMPE Technical Conference, Atlanta, GA:Oct. 24-27, 1994:TPSX Ref. #27.