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41by Protz, Christopher S. (Christopher Stephen), 1977-“... storable bipropellant micro-rocket engine. Micro-rockets are built using MEMS technology and are projected...”
Published 2005
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42by Joppin, Carole, 1979-“... for a liquid regeneratively cooled micro rocket engine focusing on the characterization of their cooling...”
Published 2005
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44by Leto Angelo“...In the radial turbine preliminary design for an expander rocket engine, a comparison was made...”
Published 2020-01-01
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46by Lundmark, Martin“...In this thesis a Large Eddy Simulation (LES) of a hybrid rocket engine burning ethylene (C2H4...”
Published 2020
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48by Izabel Cecilia Ferreira de Souza Vicentin, Carlos Henrique Marchi, Antonio Carlos Foltran, Diego Moro, Nicholas Dicati Pereira da Silva, Marcos Carvalho Campos, Luciano Kiyoshi Araki, J. Aerosp. Technol. Manag., São José dos Campos, v11, e3819, 2019 https://doi.org/10.5028/jatm.v11.1066 ORIGINAL PAPER 1.Universidade Federal do Paraná – Setor de Ciências Exatas – Engenharia Mecânica – Curitiba/PR – Brazil. 2.Universidade Positivo – Engenharia Mecânica – Curitiba/PR – Brazil. *Correspondence author: izabeldesouza@gmail.com Received: Feb. 6, 2018 | Accepted: Oct. 30, 2018 Section Editor: T John Tharakan ABSTRACT: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one-dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero-order. Moreover, the sensitivity coefficients were obtained by Duhamel’s theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors. KEYWORDS: Combustion chambers, Heat flux, Heat conduction, Ill-posed problems. INTRODUCTION In a thrust chamber (nozzle and combustion chamber), the amount of energy transferred as heat to the chamber walls is between 0.5% and 5% of the total generated energy (Sutton 1992). Nevertheless, this amount could be enough to cause structural failure. Thus, to prevent the chamber and nozzle walls from failing, it is necessary to predict the heat flux accurately. Furthermore, accurate determination of heat flux is also important in the calculation of rocket engine performance and for the cooling system design. Convective and radiative heat transfer must be determined for characterization of total heat flux. The convective heat transfer coefficient typically depends on many fluid physical properties. The computation of the radiation heat transfer must be accounted by the surfaces emissivity and the absorption and scattering coefficients of the fluid mixture. However, information about these parameters is not always easily found. Considering the propellant applied in this work (potassium nitrate with sucrose, KNSu), the combustion products that affects radiation heat transfer are predominantly Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine Izabel Cecilia Ferreira de Souza Vicentin1,*, Carlos Henrique Marchi1, Antonio Carlos Foltran1, Diego Moro1,2, Nicholas Dicati Pereira da Silva1, Marcos Carvalho Campos1, Luciano Kiyoshi Araki1, Alysson Nunes Diógenes“... in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a...”
Published 2019-08-01
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49“... hybrid rocket engine design, which could be useful in some practical applications. ...”
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50“... for the Quad Hybrid Rocket Engine Levitating Platform (4-HELP). The 4-HELP is designed to demonstrate...”
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55by Alexandru-Iulian ONEL, Oana-Iuliana POPESCU, Ana-Maria NECULAESCU, Tudorel-Petronel AFILIPOAE, Teodor-Viorel CHELARU“... characteristics of liquid propelled rocket engines. The main propulsive parameters are computed using combustion...”
Published 2019-09-01
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56by Fischbach, Sean Robert“...This research is an analytical investigation of wave interactions in a simulated liquid rocket...”
Published 2007
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59by Ruiz, Anthony“...In the past fifty years, most design parameters of the combustion chamber of Liquid Rocket Engines...”
Published 2012
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60by Biju Kumar, K SSubjects: “...Cryogenic Rocket Engines...”
Published 2014
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