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Littérature scientifique sur le sujet « Space Nozzle »

Auteur : Grafiati

Publié le 4 juin 2021

Mis à jour le 17 février 2022

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Articles de revues sur le sujet "Space Nozzle"

Lu, Yonghua, Jing Li, Xiang Zhang et Yang Li. « The thrust measurement system research for combined nozzle in small space ». Transactions of the Institute of Measurement and Control 41, n^o 4 (19 septembre 2018) : 1149–59. http://dx.doi.org/10.1177/0142331218793485.

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For measuring the thrust of combined nozzles in satellite thruster with a small space, the test method that the nozzle directly sprays on the load baffle is employed in this paper. The key problem is how to design the positions of 10 load baffles and how to construct the measurement system. A set of complete and automatic nozzle thrust measurement system is designed and built, and the influence of the load baffle applied on the flow field of nozzles is analyzed using the software FLUENT. Furthermore, the load surface locations of the sensors for the different types of nozzles are analyzed. We draw the conclusion that the load baffle position should range from 4–8 mm for the I-type nozzle and range in 6–12 mm for II-type and III-type nozzle. The correction coefficients of the thrust forces for all channels of the measurement system are determined in the calibration experiment. The uncertainty of measurement system is estimated and the error source of the measurement system is traced. We found that the systematic uncertainty is mainly contributed by the A-type uncertainty which is related with the nozzle dimension and its inner structure. The B-type uncertainty of system is contributed by the force sensor.

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Akib, Yeasir Mohammad, Asif Kabir et Mahdi Hasan. « Characteristics Analysis of Dual Bell Nozzle using Computational Fluid Dynamics ». International Journal of Engineering Materials and Manufacture 4, n^o 1 (1 mars 2019) : 15–21. http://dx.doi.org/10.26776/ijemm.04.01.2019.02.

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Space exploration and space tourism have now become a raging competition among the developed nations. For this reason, different types of advanced rocket nozzles with prospective privileges are introduced. Altitude adaptive dual bell nozzle will soon replace the conventional nozzles for the first stage rocket launcher. Indeed, this nozzle has auto adaption capability based on altitude. The major feature of a dual bell nozzle is the two bell-shaped contours separated by an inflection point. This nozzle has left rooms for researchers to test different flight conditions and transition characteristics. In this paper, a dual bell nozzle contour has been developed in MATLAB and analysed for different thermodynamic parameters. ANSYS Fluent is used in analysing flow through the nozzle. Shadowgraph imaging technique is used for measuring density gradient and compared it with fluent results. The simulations were performed by using the k-epsilon turbulence model.

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Al-agele, Hadi A., D. M. Mahapatra, Clarence Prestwich et Chad W. Higgins. « Dynamic Adjustment of Center Pivot Nozzle Height : An Evaluation of Center Pivot Water Application Pattern and the Coefficient of Uniformity ». Applied Engineering in Agriculture 36, n^o 5 (2020) : 647–56. http://dx.doi.org/10.13031/aea.13190.

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Abstract.This study assesses the potential of dynamic nozzle height adjustment for overhead irrigation systems. This system would maintain the nozzle or emitter a constant distance above the crop canopy throughout the growing season and would dynamically respond to variability in canopy height across the field. Within such systems, nozzle height would no longer be fixed in space and time. Nozzle heights would instead vary across space and time. This dynamic system response may therefore have adverse impacts on water application uniformity. The impact of DESA on application uniformity was assessed in three steps. First, changes in individual sprinkler patterns for pressure, nozzle type, flow rate, and nozzle height were measured in controlled experiments. Next, parametrized equations of the individual sprinkler patterns and how they are altered by nozzle height are developed. Next, the Center Pivot Evaluation and Design software was used to simulate theoretical uniformity, and these simulations were tested against field measurements of the coefficient of uniformity. Finally, we use the parameterized equations within the Center Pivot Evaluation and Design software to simulate the coefficient of uniformity for pivots with constant nozzle heights with a random distribution of nozzle heights, which simulate a dynamic elevation system. It was found that the uniformity coefficient decreased by 4-6% as the distribution of heights throughout the pivot become more variable, due to localized dynamic height adjustment. Systems equipped with nozzles with triangular spray patterns were less impacted than systems equipped with nozzles with elliptical spray patterns. Keywords: Keyword. Center pivot, Center Pivot Elevation and Design (CPED), Nozzle height, Sensor, Sprinkler pattern, Uniformity coefficient.

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Khobragade, Nikhil, John Wylie, Jonas Gustavsson et Rajan Kumar. « Control of Flow Separation in a Rocket Nozzle Using Microjets ». New Space 7, n^o 1 (mars 2019) : 31–42. http://dx.doi.org/10.1089/space.2018.0037.

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Zhang, Feng Hua, Hai Feng Liu, Jun Chao Xu et Chuan Lin Tang. « Experimental Investigation on Cavitation Noise of Water Jet and its Chaotic Behaviour ». Applied Mechanics and Materials 121-126 (octobre 2011) : 3919–24. http://dx.doi.org/10.4028/www.scientific.net/amm.121-126.3919.

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The cavitation noise signals were collected separately for the cavitation nozzle and general nozzle at the target position and the nozzle exit in the condition of different standoff distance. The features of signal’s frequency spectrum and power spectrum were analyzed for different nozzles. Based on chaotic theory, phase space reconstruction was processed and the maximum Lyapunov exponent was calculated separately for each cavitation signal’s time series. Under the condition of this experiment, the difference between the general nozzle and cavitation nozzle was mostly marked at the target position while the standoff distance is 35 mm, which mainly displayed at the high frequency segment. The maximum Lyapunov exponent calculated appeared at standoff distance 35 mm. At the nozzle exit, the noise signal of cavitation nozzle is different from the general nozzle. The difference also displayed at the high frequency segment, and no changing with the standoff distance

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Vemula, Rohit Chandra, Jonas Gustavsson et Rajan Kumar. « Rocket Nozzle Thrust and Flow Field Measurements Using Particle Image Velocimetry ». New Space 6, n^o 1 (mars 2018) : 37–47. http://dx.doi.org/10.1089/space.2017.0045.

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Gao, Xiang, Qing Zhen Yang, Hong Zhou et Jian Nan He. « Numerical Simulation on the Infrared Radiation Characteristics of S-Shaped Nozzles ». Applied Mechanics and Materials 482 (décembre 2013) : 282–86. http://dx.doi.org/10.4028/www.scientific.net/amm.482.282.

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Infrared stealth is of great importance to increase the survival ability of the aircraft. The exhaust system is the main radiation source of the aircraft at the rare hemisphere. A program using reverse Monte-Carlo method was developed to calculate the infrared radiation intensity of afterburning turbofan engine under non-afterburning condition, and simulate axisymmetric nozzle and three S-shaped nozzles with different relative eccentric distances. The results demonstrate that: the infrared intensity of S-shaped nozzle is much lower than that of axisymmetric nozzle; S-shaped nozzle can effectively reduce the maximum of IR intensity in the rear hemispheric space; the S-shaped nozzle with the relative eccentric distance of 0.5 can reduce the intensity of infrared radiation in critical detection directions effectively.

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Menon, Pranav. « Investigation of Variation in the Performance of an Electro Thermal Thruster with Aerospike Nozzle ». Advanced Engineering Forum 16 (avril 2016) : 91–103. http://dx.doi.org/10.4028/www.scientific.net/aef.16.91.

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One of the most recently developed modes of propulsion is electric propulsion. The commonly used chemical propulsion systems have the advantage of a high Specific Impulse as compared to that of ion propulsion systems. However, owing to the efficacy of ion propulsion systems, it is considered the future of space exploration.Electro thermal thrusters produce thrust by using electrical fields to force hot plasma out of the nozzle with certain exit velocity. The plasma’s exit velocity and the system’s thrust capacity, as of now, are insufficient for space travel to be conducted within a reasonable time. I intend to study the possibility of improving the thruster’s performance by using an aerospike nozzle as an exit nozzle which meets the conditions required for the thruster to function appropriately. I shall be studying the plasma plume exit velocity variation with respect to the nozzles used. Also, a thermal analysis will be conducted in order to find the correct material for the nozzle.

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Li, Jue, Zi Rui Lou et Wei Hong. « Research on Effects of Diameter and Arrangement of Nozzles on Combustion and Emissions in Cylinder ». Advanced Materials Research 455-456 (janvier 2012) : 320–26. http://dx.doi.org/10.4028/www.scientific.net/amr.455-456.320.

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Based on the YD4A75-C3 electronically controlled common rail diesel engine, using CFD simulation software, the combustion and emission’s behavior in cylinder was simulated on the numbers, diameter and arrangement of nozzles. The research results showed: in the condition of the certain total nozzle flow area, the proper nozzle numbers could improve fuel’s atomization quality and increase the uniformity degree of gas mixture. The staggered arrangement of nozzles could reduce interference and overlap among the adjacent fuel sprays and increase the air utilization and the space distribution of fuel, finally, the degree of mixing was increased obviously.

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Mehta, Yogesh, Vikas N. Bhargav et Rajan Kumar. « Experimental Characterization and Control of an Impinging Jet Issued from a Rocket Nozzle ». New Space 9, n^o 3 (1 septembre 2021) : 187–201. http://dx.doi.org/10.1089/space.2020.0053.

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Thèses sur le sujet "Space Nozzle"

Bae, Yoon-Yeong. « Performance of an aero-space plane propulsion nozzle / ». Full-text version available from OU Domain via ProQuest Digital Dissertations, 1989.

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Glesner, Colin Christopher. « Development of Magnetic Nozzle Simulations for Space Propulsion Applications ». Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/74947.

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A means of space propulsion using the channeling of plasma by a divergent magnetic field, referred to as a magnetic nozzle has been explored by a number of research groups. This research develops the capability to apply the high order accurate Runge-Kutta discontinuous Galerkin numerical method to the simulation of magnetic nozzles. The resistive magnetohydrodynamic model of plasma behavior is developed for these simulations. To facilitate this work, several modeling capabilities are developed, including the implementation of appropriate inflow and far-field boundary conditions, the application of a technique for correcting errors that develop in the divergence of the magnetic field, and a split formulation for the magnetic field between the applied and the perturbed component. This model is then applied to perform a scaling study of the performance of magnetic nozzles over a range of Bk and Rm. In addition, the effect of the choice of simulation domain size is investigated. Finally, recommendations for future work are made.
Master of Science

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Meiss, Jan-Hendrik. « Numerical investigation of nozzle base flow interaction of a generic space vehicle ». Aachen Shaker, 2009. http://d-nb.info/99777827X/04.

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Bradford, John Edward. « A technique for rapid prediction of aftbody nozzle performance for hypersonic launch vehicle design ». Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12896.

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Squire, Daniel E. « Flow study of the nozzle region of the space shuttle solid rocket motor ». Thesis, This resource online, 1988. http://scholar.lib.vt.edu/theses/available/etd-04122010-083741/.

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Vidakovic, Steven Slavko. « Fluid dynamic means of varying the thrust vector from an axisymmetric nozzle / ». Title page, summary and contents only, 1995. http://web4.library.adelaide.edu.au/theses/09PH/09phv648.pdf.

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Meiß, Jan H. [Verfasser]. « Numerical Investigation of Nozzle-Base-Flow Interaction of a Generic Space Vehicle / Jan H Meiß ». Aachen : Shaker, 2009. http://d-nb.info/1159836361/34.

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Glassman, Brian. « Spray Cooling for Land, Sea, Air and Space Based Applications, A Fluid Managment System for Multiple Nozzle Spray Cooling and a Guide to High Heat Flux Heater Design ». Master's thesis, University of Central Florida, 2005. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3521.

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This thesis is divided into four distinct chapters all linked by the topic of spray cooling. Chapter one gives a detailed categorization of future and current spray cooling applications, and reviews the major advantages and disadvantages that spray cooling has over other high heat flux cooling techniques. Chapter two outlines the developmental goals of spray cooling, which are to increase the output of a current system and to enable new technologies to be technically feasible. Furthermore, this chapter outlines in detail the impact that land, air, sea, and space environments have on the cooling system and what technologies could be enabled in each environment with the aid of spray cooling. In particular, the heat exchanger, condenser and radiator are analyzed in their corresponding environments. Chapter three presents an experimental investigation of a fluid management system for a large area multiple nozzle spray cooler. A fluid management or suction system was used to control the liquid film layer thickness needed for effective heat transfer. An array of sixteen pressure atomized spray nozzles along with an imbedded fluid suction system was constructed. Two surfaces were spray tested one being a clear grooved Plexiglas plate used for visualization and the other being a bottom heated grooved 4.5 x 4.5 cm2 copper plate used to determine the heat flux. The suction system utilized an array of thin copper tubes to extract excess liquid from the cooled surface. Pure water was ejected from two spray nozzle configurations at flow rates of 0.7 L/min to 1 L/min per nozzle. It was found that the fluid management system provided fluid removal efficiencies of 98% with a 4-nozzle array, and 90% with the full 16-nozzle array for the downward spraying orientation. The corresponding heat fluxes for the 16 nozzle configuration were found with and without the aid of the fluid management system. It was found that the fluid management system increased heat fluxes on the average of 30 W/cm2 at similar values of superheat. Unfortunately, the effectiveness of this array at removing heat at full levels of suction is approximately 50% & 40% of a single nozzle at respective 10[degrees]C & 15[degrees]C values of superheat. The heat transfer data more closely resembled convective pooling boiling. Thus, it was concluded that the poor heat transfer was due to flooding occurring which made the heat transfer mechanism mainly forced convective boiling and not spray cooling. Finally, Chapter four gives a detailed guide for the design and construction of a high heat flux heater for experimental uses where accurate measurements of surface temperatures and heat fluxes are extremely important. The heater designs presented allow for different testing applications; however, an emphasis is placed on heaters designed for use with spray cooling.
M.S.
Department of Mechanical, Materials and Aerospace Engineering;
Engineering and Computer Science
Mechanical Engineering

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Ramirez, Carlos. « Meso-machining of miniature space system components ». To access this resource online via ProQuest Dissertations and Theses @ UTEP, 2007. http://0-proquest.umi.com.lib.utep.edu/login?COPT=REJTPTU0YmImSU5UPTAmVkVSPTI=&clientId=2515.

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Bulut, Jane. « Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application ». Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basis of decided design characteristics, Angelino's method is used to design the nozzle contour through MATLAB. The flow field over the aerospike analyzed using commercial CFD program FLUENT for sea level, optimum expansion and vacuum conditions. Flow simulations are carried out for air (specific heat ratio, gamma= 1.4), and afterwards based on the obtained thrust values at each altitude for air, expected thrust values for the real propellant, LOX/LCH4 (specific heat ratio, gamma = 1.1664), are calculated. Finally, the study is concluded with the comparison of trend in thrust and specific impulse for conventional bell nozzle and aerospike. For the conventional bell engine the values obtained in commercial computational simulation of chemical rocket propulsion and combustion software RPA for bell nozzle with same characteristics with aerospike, Po = 30 bar and expansion ratio = 15, are taken as reference for sea level, optimum expansion level and vacuum condition performance. Due to its ability to adopt the altitude, aerospike delivers higher performance at the low altitudes with respect to the conventional bell nozzle which has the same expansion ratio and combustion chamber pressure. Last in order but not in importance, after obtaining the flow field on plug of the aerospike, the shock wave impingement on the nozzle surface at sea level has been investigated.

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Livres sur le sujet "Space Nozzle"

George, Russell J. Flight motor set 360L001 (STS-26R) : Final report. Brigham City, UT : Thiokol Corp., Space Operations, 1989.

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George, Russell J. Flight motor set 360L001 (STS-26R) : Final report. Brigham City, UT : Thiokol Corp., Space Operations, 1989.

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D, Ball Richard, Chamis C. C et United States. National Aeronautics and Space Administration., dir. Probabilistic assessment of space nuclear propulsion system nozzle. [Washington, D.C.] : National Aeronautics and Space Administration, 1994.

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J, Hester, et George C. Marshall Space Flight Center., dir. Analytical investigation of solid rocket nozzle failure. [Marshall Space Flight Center, Ala.] : National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 1985.

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United States. National Aeronautics and Space Administration., dir. RSRM nozzle fixed housing cooldown test final report. Brigham City, Utah : Morton Thiokol, Inc., Aerospace Group, 1989.

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United States. National Aeronautics and Space Administration., dir. RSRM nozzle fixed housing cooldown test final report. Brigham City, Utah : Morton Thiokol, Inc., Aerospace Group, 1989.

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Design and analysis report for the flight weight 20-inch Columbium secondary nozzle for the RL10 engine. Cleveland, Ohio : NASA Lewis Research Center, 1989.

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H, Dunlap Patrick, et NASA Glenn Research Center, dir. Development of thermal barriers for solid rocket motor nozzle joints. [Cleveland, Ohio] : National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Operations, Thiokol Corporation Space, et George C. Marshall Space Flight Center., dir. Space shuttle production verification motor-1 (PV-1) static fire. : Final test report. Brigham City, UT : Thiokol Corp., Space Operations, 1989.

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Chapitres de livres sur le sujet "Space Nozzle"

Barklage, Alexander, et Rolf Radespiel. « Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 129–43. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_8.

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Abstract This work investigates the interaction of the afterbody flow with the propulsive jet flow on a generic space launcher equipped with two alternative nozzle concepts and different afterbody geometries. The flow phenomena are characterized by experimental measurements and numerical URANS and LES simulations. Investigations concern a configuration with a conventional truncated ideal contour nozzle and a configuration with an unconventional dual-bell nozzle. In order to attenuate the dynamic loads on the nozzle fairing, passive flow control devices at the base of the launcher main body are investigated on the configuration with TIC nozzle. The nozzle Reynolds number and the afterbody geometry are varied for the configuration with dual-bell nozzle. The results for integrated nozzles show a shift of the nozzle pressure ratio for transition from sea-level to altitude mode to significant lower levels. The afterbody geometry is varied including a reattaching and non-reattaching outer flow on the nozzle fairing. Investigations are performed at supersonic outer flow conditions with a Mach number of $$Ma_\infty =3$$. It turns out, that a reattachment of the outer flow on the nozzle fairing leads to an unstable nozzle operation.

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Haidn, Oskar J., Nikolaus A. Adams, Rolf Radespiel, Thomas Sattelmayer, Wolfgang Schröder, Christian Stemmer et Bernhard Weigand. « Collaborative Research for Future Space Transportation Systems ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 1–30. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_1.

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Abstract This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

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Loosen, Simon, Matthias Meinke et Wolfgang Schröder. « Numerical Analysis of the Turbulent Wake for a Generic Space Launcher with a Dual-Bell Nozzle ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 163–77. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_10.

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Abstract The turbulent wake of an axisymmetric generic space launcher equipped with a dual-bell nozzle is simulated at transonic ($$Ma_\infty = 0.8$$ and $$Re_D = 4.3\cdot 10^5$$) and supersonic ($$Ma_\infty = 3$$ and $$Re_D = 1.2\cdot 10^6$$) freestream conditions, to investigate the influence of the dual-bell nozzle jet onto the wake flow and vice versa. In addition, flow control by means of four in circumferential direction equally distributed jets injecting air encountering the backflow in the recirculation region is utilized to determine if the coherence of the wake and consequently, the buffet loads can be reduced by flow control. The simulations are performed using a zonal RANS/LES approach. The time-resolved flow field data are analyzed by classical spectral analysis, two-point correlation analysis, and dynamic mode decomposition (DMD). At supersonic freestream conditions, the nozzle counter pressure is reduced by the expansion of the outer flow around the nozzle lip leading to a decreased transition nozzle pressure ratio. In the transonic configuration a spatio-temporal mode with an eigenvalue matching the characteristic buffet frequency of $$Sr_D=0.2$$ is extracted by the spectral and DMD analysis. The spatial shape of the detected mode describes an antisymmetric wave-like undulating motion of the shear layer inducing the low frequency dynamic buffet loads. By flow control this antisymmetric coherent motion is weakened leading to a reduction of the buffet loads on the nozzle fairing.

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Kolditz, Torge, Caner-Veli Ince et Annika Raatz. « Investigation on the Convergence of the Genetic Algorithm of an Aerodynamic Feeding System Due to the Enlargement of the Solution Space ». Dans IFIP Advances in Information and Communication Technology, 63–77. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-72632-4_5.

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AbstractTo meet the demands for flexible assembly technology, an aerodynamic feeding system has been developed. The system autonomously finds the optimal configuration of four parameters – two angles of inclination, nozzle pressure and component speed – using a genetic algorithm, which has been presented in earlier work. To increase the flexibility of the feeding system, an actuator was implemented, that enables the variation of the nozzle position orthogonally to the moving direction of the components. This paper investigates the effects of the more flexible flow against the components on their behavior when passing the nozzle. Additionally, the nozzle position was implemented into the genetic algorithm as a fifth parameter. Therefore, the impact of the enlargement of the solution space of the genetic algorithm due to the implementation of a fifth parameter is investigated in this paper as well.

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Schumann, Jan-Erik, Markus Fertig, Volker Hannemann, Thino Eggers et Klaus Hannemann. « Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes ». Dans Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 179–91. Cham : Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_11.

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Abstract The flow field around generic space launch vehicles with hot exhaust plumes is investigated numerically. Reynolds-Averaged Navier-Stokes (RANS) simulations are thermally coupled to a structure solver to allow determination of heat fluxes into and temperatures in the model structure. The obtained wall temperatures are used to accurately investigate the mechanical and thermal loads using Improved Delayed Detached Eddy Simulations (IDDES) as well as RANS. The investigated configurations feature cases both with cold air and hot hydrogen/ water vapour plumes as well as cold and hot wall temperatures. It is found that the presence of a hot plume increases the size of the recirculation region and changes the pressure distribution on the nozzle structure and thus the loads experienced by the vehicle. The same effect is observed when increasing the wall temperatures. Both RANS and IDDES approaches predict the qualitative changes between the configurations, but the reattachment location predicted by IDDES is up to 7% further upstream than that predicted by RANS. Additionally, the heat flux distribution along the nozzle and base surface is analysed and shows significant discrepancies between RANS and IDDES, especially on the nozzle surface and in the base corner.

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Sauer, K., K. Baumgärtel, Th Roatsch et J. F. McKenzie. « Laval nozzle effects in solar wind-exosphere interaction ». Dans Space Plasmas : Coupling Between Small and Medium Scale Processes, 43–47. Washington, D. C. : American Geophysical Union, 1995. http://dx.doi.org/10.1029/gm086p0043.

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Zhou, Ying, Pei Feng, Huanlong Hu, Pengjian Li et Cijun Shuai. « Pre-design and Analysis of Flow Field of Spacer-Free Nozzle of Aluminum Roll-Casting ». Dans Advanced Electrical and Electronics Engineering, 651–55. Berlin, Heidelberg : Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19712-3_83.

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Zhou, Ying, Pei Feng, Pengjian Li, Huanlong Hu et Cijun Shuai. « Optimize Structure Dimension of Spacer-Free Nozzle of Aluminum Roll Casting Using Orthogonal Experiment Design ». Dans Advanced Electrical and Electronics Engineering, 657–61. Berlin, Heidelberg : Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19712-3_84.

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Zhou, Ying, Pei Feng, Huanlong Hu, Pengjian Li et Cijun Shuai. « Quantitative Analysis of Orthogonal Experiment on Simulation of Fluid Field in Spacer-Free Nozzle in Aluminum Roll-Casting ». Dans Advanced Electrical and Electronics Engineering, 663–67. Berlin, Heidelberg : Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19712-3_85.

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Zhou, Ying, Pei Feng, Pengjian Li, Huanlong Hu et Cijun Shuai. « An Optimization Scheme of Single-Spacer Nozzle of Aluminum Roll Casting Using Coupled Fluid-Thermal Finite Element Analysis ». Dans Advanced Electrical and Electronics Engineering, 669–74. Berlin, Heidelberg : Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19712-3_86.

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Actes de conférences sur le sujet "Space Nozzle"

Rao, G., J. Beck et T. Booth. « Nozzle optimization for space-based vehicles ». Dans 35th Joint Propulsion Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2584.

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Williams, Craig H. « Fusion Propulsion Through a Magnetic Nozzle and Open Divertor ». Dans SPACE TECHNOLOGY AND APPLICATIONS INT.FORUM-STAIF 2003 : Conf.on Thermophysics in Microgravity ; Commercial/Civil Next Generation Space Transportation ; Human Space Exploration ; Symps.on Space Nuclear Power and Propulsion (20th) ; Space Colonization (1st). AIP, 2003. http://dx.doi.org/10.1063/1.1541333.

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Davis, Darrell. « Thermal analysis of the MC-1 chamber/nozzle ». Dans Space technology and applications international forum - 2001. AIP, 2001. http://dx.doi.org/10.1063/1.1357937.

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Onder, Nagehan, et Ceyhun Tola. « Effects of Nozzle Throat and Combustion Chamber Design Variables on Divergent Portion of the Nozzle ». Dans 2019 9th International Conference on Recent Advances in Space Technologies (RAST). IEEE, 2019. http://dx.doi.org/10.1109/rast.2019.8767796.

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Chavers, D. Gregory. « Status of Magnetic Nozzle and Plasma Detachment Experiment ». Dans SPACE TECH.& APPLIC.INT.FORUM-STAIF 2006 : 10th Conf Thermophys Applic Microgravity ; 23rd Symp Space Nucl Pwr & Propulsion ; 4th Conf Human/Robotic Tech & Nat'l Vision for Space Explor. ; 4th Symp Space Coloniz. ; 3rd Symp on New Frontiers & Future Concepts. AIP, 2006. http://dx.doi.org/10.1063/1.2169224.

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Chutkey, Kiran, N. Balakrishnan et B. Vasudevan. « Experimental analysis of linear plug nozzle ». Dans 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2628.

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Swaraj Kumar, B., Z. A. Samitha, S. Sheena et P. Balachandran. « Design and Testing of Clover Nozzle ». Dans 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-8094.

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Gronland, T., et J. Cambier. « Sensitivity to physical modelling for nozzle/afterbody flowfields ». Dans Space Plane and Hypersonic Systems and Technology Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-4547.

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Perrier, P., M. Rapuc, P. Rostand, R. Hallard, D. Regard, A. Dufour et O. Penanhoat. « Nozzle and afterbody design for hypersonic airbreathing vehicles ». Dans Space Plane and Hypersonic Systems and Technology Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-4548.

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NORDLUND, R. « Space Shuttle Main Engine nozzle thermal protection system ». Dans 20th Thermophysics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1053.

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