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  • 1
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    Active Wireless Temperature Sensors for Aerospace Thermal Protection Systems (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Health diagnostics is an area where major improvements have been identified for potential implementation into the design of new reusable launch vehicles in order to reduce life-cycle costs, to increase safety margins, and to improve mission reliability. NASA Ames is leading the effort to advance inspection and health management technologies for thermal protection systems. This paper summarizes a joint project between NASA Ames and Korteks to develop active wireless sensors that can be embedded in the thermal protection system to monitor sub-surface temperature histories. These devices are thermocouples integrated with radio-frequency identification circuitry to enable acquisition and non-contact communication of temperature data through aerospace thermal protection materials. Two generations of prototype sensors are discussed. The advanced prototype collects data from three type-k thermocouples attached to a 2.54-cm square integrated circuit.
    Keywords: Instrumentation and Photography
    Type: SPIE 8th Annual International Symposium on NDE for Health Monitoring and Diagnostics; Mar 02, 2003 - Mar 06, 2003; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 2
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    Fractographic Analysis of HfB2-SiC and ZrB2-SiC Composites (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Hafnium diboride-silicon carbide and zirconium diboride-silicon carbide composites are potential materials for high temperature leading edge applications on reusable launch vehicles. In order to establish material constants necessary for evaluation of in-situ fracture, bars fractured in four point flexure were examined using fractographic principles. The fracture toughness was determined from measurements of the critical crack sizes and the strength values, and the crack branching constants were established to use in forensic fractography of materials for future flight applications. The fracture toughnesses range from about 13 MPam (sup 1/2) at room temperature to about 6 MPam (sup 1/2) at 1400 C for ZrB2-SiC composites and from about 11 MPam (sup 1/2) at room temperature to about 4 MPam (sup 1/2) at 1400 C for HfB2-SiC composites.
    Keywords: Composite Materials
    Type: 26th Annual International Conference on Advanced Ceramics and Composites; Jan 13, 2002 - Jan 18, 2002; Unknown
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    NASA TECHNICAL REPORTS
  • 3
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    Property and Microstructural Characterization of Diboride Composites for High Temperature Aerospace Applications (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Previous work on refractory diboride composites has shown these systems to have potential for use in high temperature leading edge applications for reusable reentry vehicles. These composites, based on compositions of HfB2 or ZrB2 with SiC particulate reinforcements, have shown good oxidation resistance in reentry environments. In this work we are investigating the effects of composition and microstructure on properties. Preliminary studies of composite mechanical properties and oxidation behavior will be discussed.
    Keywords: Composite Materials
    Type: 26th Annual International Conference on Advanced Ceramics and Composites; Jan 13, 2002 - Jan 18, 2002; Unknown
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    NASA TECHNICAL REPORTS
  • 4
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    Assessing Factors of Safety, Margins of Safety, and Reliability of Thermal Protection Systems (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: This paper provides formally derived definitions for Thermal Protection Systems (TPS) factors of safety and margins of safety borrowing from machine design approaches. The new factors of safety and margins of safety definitions are quite simple and easy to use, and should provide improved comparison of design safety and margins of past, present and future vehicles, These definitions are then applied to several entry vehicles, including Apollo, the Space Shuttle, the Mars Viking and Pathfinder vehicles, and the Pioneer Venus entry vehicle for example and clarity, and to aid in developing a database of previous TPS design experience. In addition to the factors and margins of safety, definitions of computed reliabilities incorporation the reliability index used in machine design are also developed and presented. Adoption and use of the reliability index will hopefully considerably aid the optimization of TPS design for future vehicles.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: 26th Annual Conference on Composites, Materials and Structures; Jan 28, 2001 - Jan 31, 2001; Cocoa Beach, FL; United States
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  • 5
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    Processing and Properties Of Refractory Zirconium Diboride Composites For Use In High Temperature Applications (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The Thermal Protection Materials and Systems Branch at NASA Ames Research Center is involved in the development of a class of refractory oxidation-resistant diboride composites termed Ultra High Temperature Ceramics or UHTCs. These composites have good high temperature properties making them candidate materials for thermal protection system (TPS) applications. The current research focuses on improving processing methods to develop more reliable composites with enhanced thermal and mechanical properties. This presentation will concentrate on the processing of ZrB2/SiC composites. Some preliminary mechanical properties and oxidation data will also be presented.
    Keywords: Composite Materials
    Type: Pacific Rim IV International Conference; Nov 04, 2001 - Nov 08, 2001; Wailea, HI; United States
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  • 6
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    Waterproofing Nanostructured Aerogel-Ceramic Fiber Composites (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Aerogels are nanoporous materials which can be used to enhance the transport properties of ceramic fiber materials, to exploit their unique properties such as high porosity, large surface area, low density and low thermal conductivity. Numerous applications have been investigated. major obstacle to commercialization is that the structure of aerogels collapses due to the adsorption of water. simple and relatively cheap process has been developed to waterproof silica, alumina and alumina-silica and carbon aerogels and composites incorporating them. Previous waterproofing methods are short lived or expensive and time consuming.
    Keywords: Nonmetallic Materials
    Type: Pacific Rim IV International Conference; Nov 04, 2001 - Nov 08, 2001; Wailea, HI; United States
    Format: text
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  • 7
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    Composites: Processing and Fabrication Methodologies of Nonoxide Ceramic Composites. Processing HfB2 Composites for Use in Extreme Environments (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: HfB2 and ZrB2 composites containing SiC are known to have good thermal shock and configurational stability at elevated temperatures. These are promising ultra-high temperature ceramics (UHTCs) for use on the sharp leading edges of next generation space vehicles. Sharp leading edges on these vehicles will need to: withstand repeated exposures to temperatures 〉 2200 C in oxidizing environments; have good thermal shock and ablation resistance; and withstand the mechanical stress of launch and reentry. The HfB2/SiC composite is currently undergoing processing improvements in an effort to better the performance of a material that has been studied for approx. 35 years. The potential for HfB2/SiC composites to meet the requirements of hypersonic flight depends on controlling processing techniques. This presentation will focus on understanding processing steps now being undertaken to optimize the material properties of HfB2/SiC composites at NASA Ames Research Center. Correlation between processing techniques and microstructure will be shown. Preliminary oxidation studies will also be discussed.
    Keywords: Composite Materials
    Type: Pacific Rim IV International Conference; Nov 04, 2001 - Nov 08, 2001; Wailea, HI; United States
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  • 8
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    Flight Performance of a Functionally Gradient Material, TUFI, on Shuttle Orbiter (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: TUFI, Toughened Uni-Piece Fibrous Insulation, a functionally gradient material has been successfully flying on the Shuttle Orbiters in several locations on two insulation substrates over the past few years. TUFI is composed of insulation and a gradated surface treatment. The locations it has flown include the base heat shield where damage had been observed after every flight before its application. It was also applied to the to of the body flap, the bottom of the body flap and around selected windows and doors where damage had been observed in the past. A description of the types of processing used including substrates will be presented and its overall performance will be reviewed.
    Keywords: Composite Materials
    Type: Pacific Rim IV International Conference; Nov 04, 2001 - Nov 08, 2001; Wailea, HI; United States
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  • 9
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    Thermal Protection Materials for Reentry and Planetary Applications (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Thermal protection materials and systems (TPS) are used to protect spacecraft during reentry into Earth's atmosphere or entry into planetary atmospheres. As such, these materials are subject to severe environments with high heat fluxes and rapid heating. Catalytic effects can increase the temperatures substantially. These materials are also subject to impact damage from micrometeorites or other debris during ascent, orbit, and descent, and thus must be able to withstand damage and function following damage. Thermal protection materials and coatings used in reusable launch vehicles will be reviewed, including the needs and directions for new materials to enable new missions that require faster turnaround and much greater reusability. The role of ablative materials for use in high heat flux environments, especially for non-reusable applications and upcoming planetary missions, will be discussed. New thermal protection system materials may enable the use of sharp nose caps and leading edges on future reusable space transportation vehicles. Vehicles employing this new technology would have significant increases in maneuverability and out-of-orbit cross range compared to current vehicles, leading to increased mission safety in the event of the need to abort during ascent or from orbit. Ultrahigh temperature ceramics, a family of materials based on HfB2and ZrB2 with SiC, will be discussed. The development, mechanical and thermal properties, and uses of these materials will be reviewed.
    Keywords: Composite Materials
    Type: Conference on Structural Ceramics and Ceramic Composites for High Temperature Applications; Oct 01, 2001; Spain
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    NASA TECHNICAL REPORTS
  • 10
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    Wireless Subsurface Sensors for Health Monitoring of Thermal Protection Systems on Hypersonic Vehicles (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Health diagnostics is an area where major improvements have been identified for potential implementation into the design of new reusable launch vehicles (RLVs) in order to reduce life cycle costs, to increase safety margins, and to improve mission reliability. NASA Ames is leading the effort to develop inspection and health management technologies for thermal protection systems. This paper summarizes a joint project between NASA Ames and industry partners to develop "wireless" devices that can be embedded in the thermal protection system to monitor temperature or other quantities of interest. These devices are sensors integrated with radio-frequency identification (RFID) microchips to enable non-contact communication of sensor data to an external reader that may be a hand-held scanner or a large portal. Both passive and active prototype devices have been developed. The passive device uses a thermal fuse to indicate the occurrence of excessive temperature. This device has a diameter under 0.13 cm. (suitable for placement in gaps between ceramic TPS tiles on an RLV) and can withstand 370 C for 15 minutes. The active device contains a small battery to provide power to a thermocouple for recording a temperature history during flight. The bulk of the device must be placed beneath the TPS for protection from high temperature, but the thermocouple can be placed in a hot location such as near the external surface.
    Keywords: Launch Vehicles and Launch Operations
    Type: 3rd International Workshop on Structural Health Monitoring; Sep 12, 2001 - Sep 14, 2001; Stanford, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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