Development Of Solid Propellant Rocket Motor by Azhar, Thaqif Naqiuddin Ahmad

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Gas dynamics and thermodynamics of solid-propellant rockets/ by 460055 Sorkin, R. E.

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Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine by 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

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Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine by Izabel Cecilia Ferreira de Souza Vicentin, Carlos Henrique Marchi, Antonio Carlos Foltran, Diego Moro, Nicholas Dicati Pereira da da Silva, Marcos Carvalho Campos, Luciano Kiyoshi Araki, Alysson Nunes Diógenes

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Experimental and numerical investigation on solid propellant rocket motor performance by Almayas, Ali A A A

“…Application of Computational Fluid Dynamics (CFD) in studying solid propellant rocket motor have been growing steadily. …”
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Design, Fabrication And Testing Of A Solid Propellant Rocket Motor by Ang , Kiang Long

“…The objectives of this paper are to design, fabricate and test a solid propellant rocket motor. First, Literature studies on rocket motor fundamental which covered existing motor designs and theories for determining the properties of the rocket motor. …”
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Investigation of solid propellant rocket motor nozzle via CFD simulation by Aolin, Chen, A. A., Al Mayas, Abdul Aziz, Faieza, Yidris, Noorfaizal, Ahmad, Kamarul Arifin

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Static Firing Tests of Solid Propellant Rocket Motors: Uncertainty Levels of Thrust Measurements by Fernando Augusto Catalano Fernandes, Carlos d’Andrade Souto, Rogerio Pirk

“… Static firing tests of solid propelled rocket motors (SRMs) are important tests in aerospace industry during the development of new motors as well as to assure the quality of a motor batch. …”
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Static Firing Tests of Solid Propellant Rocket Motors: Uncertainty Levels of Thrust Measurements by Fernando Augusto Catalano Fernandes, Carlos d’Andrade Souto, Rogerio Pirk

“… Static firing tests of solid propelled rocket motors (SRMs) are important tests in aerospace industry during the development of new motors as well as to assure the quality of a motor batch. …”
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Performance Comparison of Control Strategies for a Variable-Thrust Solid-Propellant Rocket Motor by Jihyoung Cha, Élcio Jeronimo de Oliveira

Subjects: “…variable-thrust solid-propellant rocket motor…”
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Verification of Model of Calculation of Intra-Chamber Parameters In Hybrid Solid-Propellant Rocket Engines by Zhukov Ilya S., Borisov Boris V., Bondarchuk Sergey S., Zhukov Alexander S.

“…On the basis of obtained analytical estimate of characteristics of hybrid solid-propellant rocket engine verification of earlier developed physical and mathematical model of processes in a hybrid solid-propellant rocket engine for quasi-steady-state flow regime was performed. …”
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Gas-dynamic losses in the flow part of the channel charge of a solid-propellant rocket engine by A. N. A. N. Sabirzyanov, Ch. B. Khamatnurova, V. V. Kuzmin

Subjects: “…solid-propellant rocket motor…”
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Combined Effect of Some Internal Ballisting Parameters on the Pressure Behavior of Solid Propellant Rocket Motor by Abdulhassan A Karamalla

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THE PROBLEM OF THE OPTIMIZATION THE DESIGN PARAMETERS AND CONTROL PROGRAMS OF THE CONTROLLED ROCKET WITH SOLID PROPELLANT ROCKET ENGINE by Светлана Васильевна Сюткина-Доронина

“…The structure of the optimized parameters of the solid propellant rocket engine includes design parameters of the controlled solid propellant rocket and parameters characterizing the programs of the motion control of the controlled solid propellant rocket and parameters characterizing the motion at the active section of the trajectory. …”
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A Numerical Study on Carbon-Fiber-Reinforced Composite Cylindrical Skirts for Solid Propeller Rockets by Ferdinando Baldieri, Emanuele Martelli, Aniello Riccio

Subjects: “…solid propeller rocket…”
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Study on the influence of grain shape on solid propellant performance / by Mohd. Muzamil Wahab, 1984-, Mohammad Nazri Mohd. Jaafar, Fakulti Kejuruteraan Mekanikal

Subjects: “…Solid propellant rockets…”

Study on the influence of grain shape on solid propellant performance [electronic resource] / by Mohd. Muzamil Wahab, 1984-

Subjects: “…Solid propellant rockets…”

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review by Amado Javier Carlos Quagliano, Ross Pablo Germán, Sanches Natália Beck, Pinto Juliano Ribeiro Aguiar, Dutra Jorge Carlos Narciso

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The properties of Sn–Zn–Al–La fusible alloy for mitigation devices of solid propellant rocket motors by Zi-ting Wei, Nan Li, Jian-xin Nie, Jia-hao Liang, Xue-yong Guo, Shi Yan, Tao Zhang, Qing-jie Jiao

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Pembakaran propelan roket kimia berasaskan kalium nitrat / by Mohammad Nazri Mohd. Ja'afar, Wan Khairuddin Wan Ali, Rizalman Mamat, Malaysian Science and Technology Congress (2001 : Melaka)

Subjects: “…Solid propellant rockets…”