Liquid Rocket Engine : Thrust Chamber Parametric Modeling.

Cover -- Table of contents -- Acknowledgments -- Nomenclature -- CHAPTER 1 Introduction -- 1.1 Background -- 1.2 Work Objectives -- 1.3 Scope of the Work -- 1.4 Comments on the Project Life Cycle -- 1.5 Parametric Modeling Basics -- References -- CHAPTER 2 Fundamentals of Rocket Propulsion -- 2.1 Introduction -- 2.2 The Main References: A Historical Perspective -- 2.3 Parametric Modeling Application Review -- 2.4 What Is Jet Propulsion? -- 2.5 The de Laval Nozzle -- 2.6 Thrust Equation -- 2.7 Standard Atmosphere -- References -- CHAPTER 3 Methodology -- 3.1 Project Flowchart -- 3.2 High-Level Requirements -- 3.3 Combustion Gases Properties -- 3.3.1 Mixture Ratio -- 3.3.2 Adiabatic Flame Temperature -- 3.3.3 Molar Mass -- 3.3.4 Specific Heats Ratio -- 3.3.5 Sources of Data -- 3.4 Propellant Properties -- 3.4.1 Fuels -- 3.4.2 Oxidizers -- References -- CHAPTER 4 Thrust Chamber Performance Assessment -- 4.1 A Parameter for Thrust Chamber Performance Assessment -- 4.2 Conditions for an Ideal Thrust Chamber -- 4.3 Theoretical Performance -- 4.4 Correction Factors -- 4.5 Validations -- References -- CHAPTER 5 Nozzle Dimensioning -- 5.1 Throat Section Dimensioning -- 5.1.1 Throat Section Dimensioning: First Method -- 5.1.2 Throat Section Dimensioning: Second Method -- 5.2 Exhaust Section Dimensioning -- 5.2.1 Exhaust Section Dimensioning: First Method -- 5.2.2 Exhaust Section Dimensioning: Second Method -- 5.3 When Nozzle Operates Out of the Optimal Point -- 5.4 Validations -- References -- CHAPTER 6 Combustion Chamber Dimensioning -- 6.1 Introduction -- 6.2 Combustion Chamber Volume -- 6.3 Combustion Chamber Diameter -- 6.4 Combustion Chamber Length -- 6.5 Chamber Wall Thickness -- 6.6 Model Assessment -- 6.7 Validations -- References -- CHAPTER 7 Nozzle Configuration -- 7.1 Introduction -- 7.2 Conical Nozzle -- 7.3 Parabolic Nozzle -- 7.4 Validation.

References -- CHAPTER 8 Complementing the Performance Calculation -- 8.1 Propellant Consumption -- 8.2 Nozzle Flow Equations -- 8.3 Validations -- References -- CHAPTER 9 The Cold Section -- 9.1 Introduction -- 9.2 Impinging Jets -- 9.3 Shower Head -- 9.4 Swirl, Pressure Swirl, or Spray -- 9.5 Pintle -- References -- CHAPTER 10 The Simplex Swirl Injector -- 10.1 Introduction -- 10.2 Swirl Injection Operation -- 10.3 Problem Statement -- 10.4 The Outlet Orifice -- 10.5 The Inlet Orifices -- 10.6 Sizing Methodology -- 10.7 Validation -- References -- CHAPTER 11 The Pintle Injector -- 11.1 Introduction -- 11.2 General Characteristics -- 11.3 Qualitative Analyses: Flow Visualization -- 11.4 Quantitative Analyses: Design Parameters -- 11.5 Validation -- 11.5.1 The 1000-N Injector -- 11.5.2 Validation: The 5000-N Injector -- References -- CHAPTER 12 Appendix -- 12.1 Ground Test -- 12.1.1 Testing a Complete Engine - Hot Test -- 12.1.2 Testing the Propellant Injector - Cold Test -- 12.2 Propellants Charts -- 12.2.1 Liquid Oxygen and Ethanol -- 12.2.2 Liquid Oxygen and Kerosene -- 12.2.3 Liquid Oxygen and Liquid Methane -- 12.2.4 Liquid Oxygen and Liquid Hydrogen -- 12.2.5 Hydrogen Tetroxide and UDMH -- References -- About the Author -- Index.

Presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and accuracy appropriate to the preliminary design phase.

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Electronic reproduction. Ann Arbor, Michigan : ProQuest Ebook Central, 2024. Available via World Wide Web. Access may be limited to ProQuest Ebook Central affiliated libraries.