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Bibliographies thématiques / Rocket engine nozzle / Livres

Livres sur le sujet « Rocket engine nozzle »

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Auteur : Grafiati

Publié le 14 mars 2023

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1

United States. National Aeronautics and Space Administration., dir. Comparison of two procedures for predicting rocket engine nozzle performance. [Washington, DC] : National Aeronautics and Space Administration, 1987.

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2

Marable, R. W. Design, fabrication, and test of the RL10 derivative II chamber/primary nozzle. [West Palm Beach, Fla : Pratt and Whitney Aircraft, 1989.

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3

Leonard, Schoenman, et United States. National Aeronautics and Space Administration., dir. Advanced small rocket chambers option 3 : 110 1bf Ir-Re rocket. [Washington, DC] : National Aeronautics and Space Administration, 1995.

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4

J, Sovie Amy, Haag Thomas W et United States. National Aeronautics and Space Administration., dir. Arcjet nozzle design impacts. [Washington, DC] : National Aeronautics and Space Administration, 1989.

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5

Milton, Lamb, et United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20. [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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6

M, Kim Y., Shang H. M et United States. National Aeronautics and Space Administration., dir. Turbulence modelling of flow fields in thrust chambers : Final technical report for the period June 10, 1991 through September 13, 1992. [Huntsville, Ala.] : Research Institute, the University of Alabama in Huntsville, 1993.

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7

M, Kim Y., Shang H. M et United States. National Aeronautics and Space Administration., dir. Turbulence modelling of flow fields in thrust chambers : Final technical report for the period June 10, 1991 through September 13, 1992. [Huntsville, Ala.] : Research Institute, the University of Alabama in Huntsville, 1993.

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8

J, Pavli Albert, Kacynski Kenneth J et United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., dir. Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m℗ø(350 psia). [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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9

George C. Marshall Space Flight Center., dir. Flight motor set 360H005 (STS-28R). Brigham City, UT : Thiokol Corp., Space Operations, 1990.

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10

United States. National Aeronautics and Space Administration., dir. Calculation of propulsive nozzle flowfields in multidiffusing chemically recating environments. [Washington, DC] : National Aeronautics and Space Administration, 1994.

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11

Jankowsky, Robert S. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Cleveland, Ohio] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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12

D, Leavitt Laurence, et United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., dir. Static internal performance of single-expansion-ramp nozzles with thrust-vectoring capability up to 60ʻ́. [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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13

Turchi, Peter J. The effects of magnetic nozzle configurations on plasma thrusters : Final report, grant/contract no. : NAG3-843. [Washington, DC : National Aeronautics and Space Administration, 1997.

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14

United States. National Aeronautics and Space Administration., dir. Heat transfer in rocket engine combustion chambers and regeneratively cooled nozzles : Final report. Huntsville, AL : SECA, Inc., 1993.

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15

United States. National Aeronautics and Space Administration., dir. Heat transfer in rocket engine combustion chambers and regeneratively cooled nozzles : Final report. Huntsville, AL : SECA, Inc., 1993.

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16

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., dir. Pocketing mechanics of SRM nozzle liner. [Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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17

Quentmeyer, Richard J. Hot-gas-side heat transfer characteristics of subscale, plug-nozzle rocket calorimeter chamber. Cleveland, Ohio : Lewis Research Center, 1993.

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18

A, Roncace Elizabeth, et United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., dir. Hot-gas-side heat transfer characteristics of subscale, plug-nozzle rocket calorimeter chamber. [Washington, DC] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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19

William, Hall, et United States. National Aeronautics and Space Administration., dir. Proceedings : Nozzle Initiative Industry Advisory Committee on Standardization of Carbon-Phenolic Test Methods and Specifications held at Aerojet, Sacramento, California, November 14-15, 1991. [Washington, DC : National Aeronautics and Space Administration, 1991.

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20

Cook, M. Shelf life extension for the lot AAE nozzle severance LSCs : Final test report. Brigham City, UT : Thiokol Corp., Space Operations, 1990.

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21

Jankovsky, Robert S. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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22

D, Smith Timothy, Pavli Albert J et NASA Glenn Research Center, dir. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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23

D, Smith Timothy, Pavli Albert J et NASA Glenn Research Center, dir. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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24

D, Smith Timothy, Pavli Albert J et NASA Glenn Research Center, dir. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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25

Jian-Shun, Shuen, et United States. National Aeronautics and Space Administration., dir. A numerical study of chemically reacting flow in nozzles. [Washington, DC] : National Aeronautics and Space Administration, 1989.

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26

1934-, Hoffman Joe D., et United States. National Aeronautics and Space Administration., dir. The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios. [Washington, DC] : National Aeronautics and Space Administration, 1994.

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27

1934-, Hoffman Joe D., et United States. National Aeronautics and Space Administration., dir. The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios. [Washington, DC] : National Aeronautics and Space Administration, 1994.

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28

Kopp, Robert William. Determination of the velocity, density, mass flux and enthalpy profiles for very high temperature arc jet nozzle flow. Monterey, Calif : Naval Postgraduate School, 1989.

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29

Operations, Thiokol Corporation Space, et George C. Marshall Space Flight Center., dir. Flight motor set 360L002 (STS-27R). : Final report. Brigham City, UT : Thiokol Corp., Space Operations, 1989.

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30

United States. National Aeronautics and Space Administration., dir. Evaluation of coated columbium test panels having application to a secondary nozzle extension for the RL10 rocket engine system : Parts I and II : final report. 1989.

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31

Calculation of propulsive nozzle flowfields in multidiffusing chemically recating environments. [Washington, DC] : National Aeronautics and Space Administration, 1994.

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32

Heat transfer in rocket engine combustion chambers and regeneratively cooled nozzles. Huntsville, AL : SECA, Inc., 1993.

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33

Heat transfer in rocket engine combustion chambers and regeneratively cooled nozzles. Huntsville, AL : SECA, Inc., 1993.

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34

Escudier, Marcel. Engineering applications of the linear momentum equation. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198719878.003.0010.

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In this chapter a method is shown for applying the linear momentum equation, together with the continuity equation and either Bernoulli’s equation or some other information about static pressure, to the analysis of a diverse range of practical problems. A key aim is to demonstrate that it is possible to establish a relatively simple theoretical basis which can give quite accurate and useful information about the performance of such complex machines as jet and rocket engines, the jet pump, and the Pelton turbine. Other examples include flow through a sudden enlargement, a convergent nozzle, a pipe bend, a pipe junction, and a cascade of guidevanes. For each example it is shown how to define a suitable control volume.

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35

High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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36

Comparison of response surface and kriging models in the multidisciplinary design of an aerospike nozzle. Hampton, VA : Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1998.

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37

Escudier, Marcel. Introduction to Engineering Fluid Mechanics. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198719878.001.0001.

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Turbojet and turbofan engines, rocket motors, road vehicles, aircraft, pumps, compressors, and turbines are examples of machines which require a knowledge of fluid mechanics for their design. The aim of this undergraduate-level textbook is to introduce the physical concepts and conservation laws which underlie the subject of fluid mechanics and show how they can be applied to practical engineering problems. The first ten chapters are concerned with fluid properties, dimensional analysis, the pressure variation in a fluid at rest (hydrostatics) and the associated forces on submerged surfaces, the relationship between pressure and velocity in the absence of viscosity, and fluid flow through straight pipes and bends. The examples used to illustrate the application of this introductory material include the calculation of rocket-motor thrust, jet-engine thrust, the reaction force required to restrain a pipe bend or junction, and the power generated by a hydraulic turbine. Compressible-gas flow is then dealt with, including flow through nozzles, normal and oblique shock waves, centred expansion fans, pipe flow with friction or wall heating, and flow through axial-flow turbomachinery blading. The fundamental Navier-Stokes equations are then derived from first principles, and examples given of their application to pipe and channel flows and to boundary layers. The final chapter is concerned with turbulent flow. Throughout the book the importance of dimensions and dimensional analysis is stressed. A historical perspective is provided by an appendix which gives brief biographical information about those engineers and scientists whose names are associated with key developments in fluid mechanics.

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