Material Characterization of Shuttle Thermal Protection System for Impact Analyses

Lu, Wei‐Yang; Antoun, Bonnie R.; Korellis, John S.; Scheffel, Simon; Lee, Moo; Hardy, Robert

doi:10.2514/6.2004-945

Cited by 8 publications

(7 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The most directly relevant experimental results are those of Lu et al, 6 who performed tests at Sandia National Laboratories on samples taken from Space Shuttle wing leading edge panels, in support of the Columbia accident investigation. They provide data on elastic moduli as well as strength measurements obtained from tension, bending, and compression tests.…”

Section: Reinforced Carbon-carbonmentioning

confidence: 99%

See 1 more Smart Citation

Simulation of Hypervelocity Impact Effects on Reinforced Carbon-Carbon

Park

Fahrenthold

2006

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Spacecraft operating in low earth orbit face a significant orbital debris impact hazard.Of particular concern, in the case of the Space Shuttle, are impacts on critical components of the thermal protection system. Recent research has formulated a new material model of reinforced carbon-carbon, for use in the analysis of hypervelocity impact effects on the Space Shuttle wing leading edge. The material model has been validated in simulations of published impact experiments and applied to model orbital debris impacts at velocities beyond the range of current experimental methods. The results suggest that momentum scaling may be used to extrapolate the available experimental data base, in order to predict the size of wing leading edge perforations at impact velocities as high as 13 km/s. NOMENCLATURE

show abstract

Section: Reinforced Carbon-carbonmentioning

confidence: 99%

“…The loss of the Space Shuttle Columbia, 5 apparently due to impact damage on the wing leading edge, has motivated recent experimental 6 and computational 7 work aimed at developing a better understanding of the impact response of thermal protection materials.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Hypervelocity Impact Effects on Reinforced Carbon-Carbon

Park

Fahrenthold

2006

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…It is therefore necessary to investigate the effect of the impact damage on the operational life and overall structural performance of carbon-carbon structures used in these spacecraft designs. Experimental and computational methods have been developed to acquire a better understanding of the impact response in carbon-carbon materials [27][28][29][30][31][32][33], although many existing results available in open literature are referred to RCC materials only. Christiansen et al…”

Section: Introductionmentioning

confidence: 99%

High velocity impact tests on high temperature carbon-carbon composites

Xie

Meng

Ding

et al. 2016

Composites Part B: Engineering

View full text Add to dashboard Cite

General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. AbstractThis paper describes the effect of high velocity impact on the structural integrity of advanced carbon-carbon (C/C) composites for high temperature applications. Impact tests have been performed on heated C/C composite samples at high temperature to establish correlations between the mechanical performances of the composites and different impact factors. Two tensile tests were also performed to investigate the residual strength of the high temperature C/C structures with the impact damage. In this work we present two new equations to predict the dimensionless damage areas of the C/C impacted at elevated temperatures. The impact resistance of the C/C composites is affected by the diameter of the projectile, the temperature and thickness of the C/C laminates and -more importantly -by the impact velocity. The residual strength of the damaged C/C composites increased by 47% after heating the samples from 25°C to 1206°C.

show abstract

“…On the other hand, the very high impact velocities and the complex kinematics (perforation, fragmentation, and debris transport) of interest suggest the use of Eulerian (hydrocode) 14 or particle-based 15,16 modeling approaches. In addition to these complications, difficulties with constitutive modeling of porous ceramics 17,18 and other thermal protection system components [19][20][21] present significant obstacles to the effective use of simulation. As a result, numerical models have to date made only limited contributions in the design of tile thermal protection systems for orbital debris impact effects.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Orbital Debris Impact on Porous Ceramic Tiles

Lee

Fahrenthold

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

View full text Add to dashboard Cite

Ceramic tiles provide lightweight, reusable insulation for spacecraft thermal protection systems, but are vulnerable to orbital debris impact damage. Since a wide range of impact conditions that may be experienced on orbit cannot be duplicated in the laboratory, design for orbital debris impact effects must include analytical or numerical modeling. Recent research has developed and validated a new computational approach to the simulation of orbital debris impact on porous ceramic thermal protection systems. Simulations using the validated formulation suggest scaling rules for application in spacecraft design.

show abstract

Material Characterization of Shuttle Thermal Protection System for Impact Analyses

Cited by 8 publications

References 1 publication

Simulation of Hypervelocity Impact Effects on Reinforced Carbon-Carbon

Simulation of Hypervelocity Impact Effects on Reinforced Carbon-Carbon

High velocity impact tests on high temperature carbon-carbon composites

Simulation of Orbital Debris Impact on Porous Ceramic Tiles

Contact Info

Product

Resources

About