Enthalpy measurement in a low-density high-temperature infrasonic flow

Zalogin, G. N.; Knot'ko, V. B.; Lunev, V. V.; Ostapovich, O. N.; Redichkin, S. B.

doi:10.1007/bf00870217

Cited by 1 publication

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“…Flow diagnostics in plasmatrons is based on contact measurements of the static pressure, stagnation pressure, heat fluxes to high-and low-catalytic materials, enthalpy [18][19][20][21][27][28][29][30], and also on spectral measurements of temperatures [31]. The measurement of atomic concentrations c Ae on the outer boundary of the boundary layer (which are necessary for reconstructing γ) is still a problem.…”

Section: Experimental Methods and Facilitiesmentioning

confidence: 99%

Chapter 6: Modeling of Catalytic Properties of Thermal Protection Coatings of Space Vehicles

2013

Hypersonic Aerodynamics and Heat Transfer

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The large practical interest in research of the interaction of multispecies gas mixtures with catalytic surfaces in supersonic flows was aroused by the development of reusable space vehicles, the Space Shuttle and Buran. For such vehicles, the use of low-catalytic coatings can ensure significant reduction of heat fluxes and, therefore, the weight of necessary thermal protection systems. Consequently, the payload can be increased. Laboratory and in-flight tests of experimental reusable systems-Bor, Buran, and Space Shuttle-showed that the use of low-catalytic coatings makes it possible to reduce heat fluxes to the vehicle surface by a factor of 3-5 [1][2][3][4][5].The interest in this problem was revived when the International Space Station was created and also due to the development of hypersonic transportation systems, such as NASP in the USA, Sanger in Germany, HOTOL in Great Britain, aerospace glider in Japan, and reentry vehicles such as the European mini-shuttle Hermes and the Japanese vehicle HOPE. The program of manned flights was also successfully developed in China. These projects gave rise to significant theoretical and experimental research all over the world. The efforts associated with the development of a rescue space vehicle for returning from the International Space Station in the case of emergency also increased the interest in effective thermal protection systems.A further impetus to future space transportation technologies is expected to be given by programs aimed at the development of hypersonic reusable flying vehicles. New problems in science and technology are also posed by projects of scientific expeditions to Mars, which can be realized in the near future.The development of promising aerospace vehicles requires solving, principally, new scientific and engineering problems. One of the most important problems is the development of a reusable thermal protection system. Calculations of thermal loads and predictions of the lifetime of a reusable thermal protection system require fundamental information

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Section: Experimental Methods and Facilitiesmentioning

confidence: 99%

Chapter 6: Modeling of Catalytic Properties of Thermal Protection Coatings of Space Vehicles

2013

Hypersonic Aerodynamics and Heat Transfer

View full text Add to dashboard Cite

show abstract

Enthalpy measurement in a low-density high-temperature infrasonic flow

Cited by 1 publication

References 2 publications

Chapter 6: Modeling of Catalytic Properties of Thermal Protection Coatings of Space Vehicles

Chapter 6: Modeling of Catalytic Properties of Thermal Protection Coatings of Space Vehicles

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