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  • 1980-1984  (13)
  • 1
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    Effect of simulated mission loads on orbiter thermal protection system undensified tiles (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 441-447
    Format: text
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  • 2
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    Mechanical properties of the Shuttle Orbiter thermal protection system strain isolator pad (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2029, Accession no. A82-30079
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 253-260
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  • 3
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    Life considerations of the shuttle orbiter densified-tile thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Shuttle orbiter themal protection system (TPS) incorporates ceramic reusable surface insulation tiles bonded to the orbiter substructure through a strain isolation pad. Densification of the bonding surface of the tiles increases the static strength of the tiles. The densification proces does not, however, necessarily lead to an equivalent increase in fatigue strength. Investigation of the expected lifetime of densified tile TPS under both sinusoidal loading and random loading simulating flight conditions indicates that the strain isolation pads are the weakest components of the TPS under fatigue loading. The felt pads loosen under repetitive loading and, in highly loaded regions, could possibly cause excessive step heights between tiles causing burning of the protective insulation between tiles. A method of improving the operational lifetime of the TPS by using a strain isolation pad with increased stiffness is presented as is the consequence of the effect of increased stiffness on the tile inplane strains and transverse stresses.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 1009-1024
    Format: application/pdf
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  • 4
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    Room temperature mechanical properties of shuttle thermal protection system materials (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted at room temperature to determine the mechanical properties and behavior of materials used for the thermal protection system of the space shuttle. The materials investigated include the LI-900 RSI tiles, the RTV-560 adhesive and the .41 cm (.16 thick) strain isolator pad (SIP). Tensile and compression cyclic loading tests were conducted on the SIP material and stress-strain curves obtained for various proof loads and load cyclic conditioning. Ultimate tensile and shear tests were conducted on the RSI, RTV, and SIP materials. The SIP material exhibits highly nonlinear stress-strain behavior, increased tangent modulus and ultimate tensile strength with increased loading rate, and large short time load relaxation and moderate creep behavior. Proof and cyclic load conditioning of the SIP results in permanent deformation of the material, hysteresis effects, and much higher tensile tangent modulus values at large strains.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-81786
    Format: application/pdf
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  • 5
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    Effect of load eccentricity and substructure deformation on ultimate strength of shuttle orbiter thermal protection system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of load eccentricity and substructure deformation on the ultimate strength and stress displacement properties of the shuttle orbiter thermal protection system (TPS) was determined. The LI-900 Reusable Surface Insulation (RSI) tiles mounted on the .41 cm thick Strain Isolator Pad (SIP) were investigated. Substructure deformations reduce the ultimate strength of the SIP/tile TPS and increase the scatter in the ultimate strength data. Substructure deformations that occur unsymmetric to the tile can cause the tile to rotate when subjected to a uniform applied load. Load eccentricity reduces SIP/tile TPS ultimate strength and causes tile rotation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-83182
    Format: application/pdf
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  • 6
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    Fatigue properties of shuttle thermal protection system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Static and cyclic load tests were conducted to determine the static and fatigue strength of the RIS tile/SIP thermal protection system used on the orbiter of the space shuttle. The material systems investigated include the densified and undensified LI-900 tile system on the .40 cm thick SIP and the densified and undensified LI-2200 tile system on the .23 cm (.090 inch) thick SIP. The tests were conducted at room temperature with a fully reversed uniform cyclic loading at 1 Hertz. Cyclic loading causes a relatively large reduction in the stress level that each of the SIP/tile systems can withstand for a small number of cycles. For example, the average static strength of the .40 cm thick SIP/LI-900 tile system is reduced from 86 kPa to 62 kPa for a thousand cycles. Although the .23 cm thick SIP/LI-2200 tile system has a higher static strength, similar reductions in the fatigue strength are noted. Densifying the faying surface of the RSI tile changes the failure mode from the SIP/tile interface to the parent RSI or the SIP and thus greatly increases the static strength of the system. Fatigue failure for the densified tile system, however, occurs due to complete separation or excessive elongation of the SIP and the fatigue strength is only slightly greater than that for the undensified tile system.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-81899
    Format: application/pdf
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  • 7
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    Effect of preforming adherends on static and fatigue strength of bonded composite single-lap joints (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical and experimental investigation was conducted on bonded composite single-lap joints with the adherends performed to reduce the angle between the line of action of the applied in-plane force and the bondline. A classical closed-form solution was used to analyze the composite joints with various preform angles and overlap lengths. The adherends of the test specimens were preformed before bonding, during the layup and curing process. Static tests were conducted for preform angles of 0, 5, 10, and 15 deg and overlap lengths of 0.75, 1.75, 2.75, and 3.75 in. A limited fatigue study was conducted for specimens with a 2.75-in. overlap and a preform angle of 5 deg. Results of the analysis showed that preforming the adherends of bonded composite single-lap joints significantly reduced the shear and peel stress concentrations in the adhesive. Experimental results showed that preforming the adherends significantly increased their static and fatigue strength and thus increased the load level for which bonded composite single-lap joints can be designed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-2324 , L-15780 , NAS 1.60:2324
    Format: application/pdf
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  • 8
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    Room temperature shear properties of the strain isolator pad for the shuttle thermal protection system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted at room temperature to determine the shear properties of the strain isolator pad (SIP) material used in the thermal protection system of the space shuttle. Tests were conducted on both the .23 cm and .41 cm thick SIP material in the virgin state and after fifty fully reversed shear cycles. The shear stress displacement relationships are highly nonlinear, exhibit large hysteresis effects, are dependent on material orientation, and have a large low modulus region near the zero stress level where small changes in stress can result in large displacements. The values at the higher stress levels generally increase with normal and shear force load conditioning. Normal forces applied during the shear tests reduces the low modulus region for the material. Shear test techniques which restrict the normal movement of the material give erroneous stress displacement results. However, small normal forces do not significantly effect the shear modulus for a given shear stress. Poisson's ratio values for the material are within the range of values for many common materials. The values are not constant but vary as a function of the stress level and the previous stress history of the material. Ultimate shear strengths of the .23 cm thick SIP are significantly higher than those obtained for the .41 cm thick SIP.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-81900
    Format: application/pdf
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  • 9
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    Assessment of the Shuttle Orbiter Thermal Protection System undensified tiles under mission dynamic loads (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is provided of the results of a series of base driven random dynamic load tests of the Thermal Protection System (TPS). The results were used to insure the integrity of the undensified TPS prior to the first flight in the wing and mid-fuselage region. The number of specimens and the load ranges investigated were limited. Attention is given to the test specimens, the test procedure, a data analysis, and a discussion of the results. All specimens for both the wing and mid-fuselage regions survived an equivalent of 72 ascent missions and exhibited residual static strength greater than their original proof loads. These results indicate that the undensified tiles had sufficient strength to withstand ascent loads during the first flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 82-0790 , In: Structures, Structural Dynamics and Materials Conference; May 10, 1982 - May 12, 1982; New Orleans, LA
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  • 10
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    Mechanical properties of the Shuttle Orbiter thermal protection system strain isolator pad (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation conducted to determine the static and fatigue properties of the Strain Isolator Pad (SIP) used on the Shuttle Orbiter Thermal protection system is described. Static tension-compression and shear test results show that the SIP is highly nonlinear and that it possesses a large hysteresis, a large low modulus region for low stress levels, and stress-strain properties that are highly sensitive to strain rate and previous load history. In addition, the shear properties are also found to be sensitive to forces applied normal to the plane of the pad and to the orientation of the material. For the undensified tile/SIP system, static and fatigue failure takes place at the SIP/tile interface at low stress levels and for a small number of cycles.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 82-0789 , In: Structures, Structural Dynamics and Materials Conference; May 10, 1982 - May 12, 1982; New Orleans, LA
    Format: text
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