The Experts below are selected from a list of 297 Experts worldwide ranked by ideXlab platform
Z. F. Karimov - One of the best experts on this subject based on the ideXlab platform.
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A Thermal Protection system for high-temperature surfaces
Thermal Engineering, 1997Co-Authors: L. V. Rodichev, Z. F. KarimovAbstract:A new method for Thermal Protection of high-temperature surfaces is considered. In this method, the Thermal Protection system has a layer of air in the space between the surface being insulated and the layer of Thermal insulation itself. The geometrical, Thermal and optical characteristics of the Thermal Protection system is optimized using a mathematical model that describes the process of heat transfer from the heat-emitting surface through the Thermal Protection system to the environment.
Wen Bao - One of the best experts on this subject based on the ideXlab platform.
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Research progress on active Thermal Protection for hypersonic vehicles
Progress in Aerospace Sciences, 2020Co-Authors: Zhang Silong, Jingying Zuo, Qin Jiang, Kunlin Cheng, Yu Feng, Wen BaoAbstract:Abstract Hypersonic vehicles with scramjet engine as propulsion devices is one of the most important developing trends in the aerospace field for both commercial and military application. The encountered huge aerodynamic heating and strong combustion heat release makes the Thermal Protection technology a critical issue. For the long run and for reusable purposes, an effective active other than a passive Thermal Protection method is required for the cooling process, mainly by including regenerative cooling, film cooling, transpiration cooling and their combinations. In this paper, the authors point out that the cooling resources are extremely limited for hypersonic vehicles. They define the “relative heat load” for the analysis of the active Thermal Protection for hypersonic vehicles. This paper presents a review of the research progress made on the active Thermal Protection method for air-breathing hypersonic vehicles in recent decades. It primarily covers the fundamental problems and recent advances, including regenerative cooling, film cooling, transpiration cooling, and combined cooling. A number of relevant aspects and remaining questions for each active cooling method are provided, including the basic flow and heat transfer mechanisms, the influencing factors and their effects, the progress in engineering application. Finally, summaries of each active cooling method, guidelines for their future development, and the authors’ view on the promising active Thermal Protection methods for future hypersonic vehicles are provided.
James O. Arnold - One of the best experts on this subject based on the ideXlab platform.
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Thermal Protection Materials for Reentry Applications
2013Co-Authors: Sylvia M. Johnson, James O. Arnold, Mairead Stackpoole, Mike Gusman, R. E. Loehman, Paul G. Kotula, Donald T. Ellerby, Paul Wercinski, James Reuthers, Dean KontinosAbstract:Thermal Protection materials and systems (IRS) 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 to 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 HfB2 and ZrB2 with SiC, will be discussed. The development, mechanical and Thermal properties, and uses of these materials will be reviewed.
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Thermal Protection Systems for Future NASA Space Vehicles
2000Co-Authors: Daniel B. Leiser, Daniel J. Rasky, James O. ArnoldAbstract:The proposed first through fourth generation of future NASA Reusable Launch Vehicles (RLV) within NASA will be described, in general, along with their relative goals for improvement in performance (i.e., cost, safety, life, and turnaround time). A brief description of Spaceliner 100 activities representing a means to achieve those goals will be included. Some of the families of Thermal Protection materials with widely varying characteristics that are being developed for first generation space vehicles at Ames Research Center will be described as well as potential materials and composites for second and third generation applications as systems. These families of materials include functionally gradient material composites that are made from a variety of low-density substrates and moderate to fully dense surface treatments providing the resultant material with both toughness and higher temperature capability opening the envelope of Thermal Protection Systems (TPS) capabilities. Some of the materials truly represent enabling technologies that are required to achieve substantially enhanced Thermal Protection system performance thereby reducing vehicle risk. Finally the needs for integrated vehicle health monitoring (IVHM) of future vehicles Thermal Protection systems relative to achieving the goals for third generation reusable launch vehicles and for improving vehicle performance and capabilities reducing risk will be described along with the state of the art in TPS.
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Thermal Protection Technology for Access to Space Vehicles
1996Co-Authors: Howard E. Goldstein, James O. ArnoldAbstract:In the next century a new generation of space launch vehicles will be required to replace the Space Shuttle and the current expendable launch vehicle fleet. These new transportation systems must provide much lower lifecycle cost and mission versatility. In order to provide these attributes the vehicles must be designed with large operational margins of safety and weights comparable or lower than current systems. Advancements in Thermal Protection Systems (TPS) will be necessary to obtain these goals. This presentation will describe the Thermal Protection technology now under development by NASA that will be available for future Access to Space vehicles.
L. V. Rodichev - One of the best experts on this subject based on the ideXlab platform.
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A Thermal Protection system for high-temperature surfaces
Thermal Engineering, 1997Co-Authors: L. V. Rodichev, Z. F. KarimovAbstract:A new method for Thermal Protection of high-temperature surfaces is considered. In this method, the Thermal Protection system has a layer of air in the space between the surface being insulated and the layer of Thermal insulation itself. The geometrical, Thermal and optical characteristics of the Thermal Protection system is optimized using a mathematical model that describes the process of heat transfer from the heat-emitting surface through the Thermal Protection system to the environment.
Daniel J. Rasky - One of the best experts on this subject based on the ideXlab platform.
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Thermal Protection Systems for Future NASA Space Vehicles
2000Co-Authors: Daniel B. Leiser, Daniel J. Rasky, James O. ArnoldAbstract:The proposed first through fourth generation of future NASA Reusable Launch Vehicles (RLV) within NASA will be described, in general, along with their relative goals for improvement in performance (i.e., cost, safety, life, and turnaround time). A brief description of Spaceliner 100 activities representing a means to achieve those goals will be included. Some of the families of Thermal Protection materials with widely varying characteristics that are being developed for first generation space vehicles at Ames Research Center will be described as well as potential materials and composites for second and third generation applications as systems. These families of materials include functionally gradient material composites that are made from a variety of low-density substrates and moderate to fully dense surface treatments providing the resultant material with both toughness and higher temperature capability opening the envelope of Thermal Protection Systems (TPS) capabilities. Some of the materials truly represent enabling technologies that are required to achieve substantially enhanced Thermal Protection system performance thereby reducing vehicle risk. Finally the needs for integrated vehicle health monitoring (IVHM) of future vehicles Thermal Protection systems relative to achieving the goals for third generation reusable launch vehicles and for improving vehicle performance and capabilities reducing risk will be described along with the state of the art in TPS.
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"TPSX: Thermal Protection System Expert and Material Property Database"
1997Co-Authors: Thomas H. Squire, Frank S. Milos, Daniel J. RaskyAbstract:The Thermal Protection Branch at NASA Ames Research Center has developed a computer program for storing, organizing, and accessing information about Thermal Protection materials. The program, called Thermal Protection Systems Expert and Material Property Database, or TPSX, is available for the Microsoft Windows operating system. An "on-line" version is also accessible on the World Wide Web. TPSX is designed to be a high-quality source for TPS material properties presented in a convenient, easily accessible form for use by engineers and researchers in the field of high-speed vehicle design. Data can be displayed and printed in several formats. An information window displays a brief description of the material with properties at standard pressure and temperature. A spread sheet window displays complete, detailed property information. Properties which are a function of temperature and/or pressure can be displayed as graphs. In any display the data can be converted from English to SI units with the click of a button. Two material databases included with TPSX are: 1) materials used and/or developed by the Thermal Protection Branch at NASA Ames Research Center, and 2) a database compiled by NASA Johnson Space Center 9JSC). The Ames database contains over 60 advanced TPS materials including flexible blankets, rigid ceramic tiles, and ultra-high temperature ceramics. The JSC database contains over 130 insulative and structural materials. The Ames database is periodically updated and expanded as required to include newly developed materials and material property refinements.
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Rigid Tile Thermal Protection Materials Research and Space Shuttle Performance
1995Co-Authors: Daniel B. Leiser, Daniel J. RaskyAbstract:The materials research activities and materials characterization capabilities of the Thermal Protection Materials and Systems Branch at Ames Research Center will be described. The Branch's activities involved with the development of several parts of the Thermal Protection system on the Space Shuttle and their performance will be reviewed. The status of materials research in rigid light weight insulations and the potential of a newer generation of Thermal Protection materials designated as Toughened Uni-Piece Fibrous Insulation (TUFI) used in protecting entry vehicles will be presented.
