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20231017213018.0 |
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191214s2018 pau o 000 0 eng d |
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|q (electronic bk.)
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|a 9780768093339
|q (electronic bk.)
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|a (OCoLC)1130680055
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|a 621.43/56
|2 23
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| 049 |
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|a UAMI
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|a Rezende, Rene Nardi,
|e author.
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| 245 |
1 |
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|a LIQUID ROCKET ENGINE :
|b THRUST CHAMBER PARAMETRIC MODELING
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| 260 |
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|a WARRENDALE :
|b SAE SOC OF AUTOMOTIVE ENG,
|c 2018.
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|a 1 online resource
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|a text
|b txt
|2 rdacontent
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|a computer
|b c
|2 rdamedia
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|a online resource
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|2 rdacarrier
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|a 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
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|a 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
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|a 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
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|a 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
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|a 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
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|a Liquid propellant rocket engines.
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|2 fast
|0 (OCoLC)fst01749749
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