Liquid Propellant Rockets

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History Of Liquid Propellant Rocket Engines

Author : George Paul Sutton
ISBN : 1563476495
Genre : Science
File Size : 85.95 MB
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Liquid propellant rocket engines have propelled all the manned space flights, all the space vehicles flying to the planets or deep space, virtually all satellites, and the majority of medium range or intercontinental range ballistic missiles.
Category: Science

Liquid Propellant Rockets

Author : David Altman
ISBN : 9781400879953
Genre : Science
File Size : 78.41 MB
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David Altman, James M. Carter, S. S. Penner, Martin Summerfield. High Temperature Equilibrium, Expansion Processes, Combustion of Liquid Propellants, The Liquid Propellants Rocket Engine. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Category: Science

Fundamental Concepts Of Liquid Propellant Rocket Engines

Author : Alessandro de Iaco Veris
ISBN : 9783030547042
Genre : Technology & Engineering
File Size : 90.98 MB
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This book is intended for students and engineers who design and develop liquid-propellant rocket engines, offering them a guide to the theory and practice alike. It first presents the fundamental concepts (the generation of thrust, the gas flow through the combustion chamber and the nozzle, the liquid propellants used, and the combustion process) and then qualitatively and quantitatively describes the principal components involved (the combustion chamber, nozzle, feed systems, control systems, valves, propellant tanks, and interconnecting elements). The book includes extensive data on existing engines, typical values for design parameters, and worked-out examples of how the concepts discussed can be applied, helping readers integrate them in their own work. Detailed bibliographical references (including books, articles, and items from the “gray literature”) are provided at the end of each chapter, together with information on valuable resources that can be found online. Given its scope, the book will be of particular interest to undergraduate and graduate students of aerospace engineering.
Category: Technology & Engineering

Fundamentals Of Theory And Calculation Of Liquid Propellant Rocket Engines Volume I

Author :
ISBN : OCLC:227536375
Genre :
File Size : 58.62 MB
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Theoretical and design principles of liquid rocket engines are presented. Extensive coverage is given to processes taking place in the combustion chamber, calculations of mixing systems, the cooling and contour calculation of the nozzles, calculation and selection of optimal parameters, turbopump and fuel feed pressurization systems, generation of the working medium for the turbine and fuel feed pressurization system, design and integration of pneumohydraulic systems for liquid rocket engines, calculation methods and selection of a liquid rocket engine parameters with a closed generation circuit of the working medium for the turbine. Basic theoretical and design principles of processes taking place in different types of liquid rocket engines are presented. The operation of main subsystems and the calculation of their characteristics are discussed. (Author).
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Liquid Propellant Rocket Combustion Instability

Author : David T. Harrje
ISBN : UIUC:30112001236741
Genre : Liquid propellant rockets
File Size : 79.10 MB
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The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.
Category: Liquid propellant rockets

Modern Engineering For Design Of Liquid Propellant Rocket Engines

Author : James R.
ISBN : 1948117940
Genre : Science
File Size : 26.91 MB
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This book intends to build a bridge for the student and the young engineer: to link the rocket propulsion fundamentals and elements with the actual rocket engine design and development work as it is carried out in the industry. The book attempts to further the understanding of the realistic application of liquid rocket propulsion theories, and to help avoid or at least reduce time and money consuming errors and disappointments. This book was written "on the job" for use by those active in all phases of engine systems, design, development, and application, in industry.
Category: Science

Theory And Calculation Of Feed Units Of Liquid Propellant Rocket Engines

Author : B. V. Ovsyannikov
ISBN : OCLC:227529821
Genre :
File Size : 80.85 MB
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In the book information on the theory and hydraulic design of pumps and turbines of turbopump units (TU) (THA) of liquid-propellant rocket engines (LPRE) is given. Principles of the general theory of vane machines are given. The basic calculated relations for the design of the flow part of pumps and turines are derived. The selection of the basic parameters of turbopump units is substantiated, and conditions of their operation are analyzed. Methods of the calculation of pumps and turbines of LPRE are briefly set forth. Examples of the calculation are given.
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Rocket Propulsion Elements

Author : George P. Sutton
ISBN : 9781118174203
Genre : Science
File Size : 66.29 MB
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The definitive text on rocket propulsion—now revised to reflect advancements in the field For sixty years, Sutton's Rocket Propulsion Elements has been regarded as the single most authoritative sourcebook on rocket propulsion technology. As with the previous edition, coauthored with Oscar Biblarz, the Eighth Edition of Rocket Propulsion Elements offers a thorough introduction to basic principles of rocket propulsion for guided missiles, space flight, or satellite flight. It describes the physical mechanisms and designs for various types of rockets' and provides an understanding of how rocket propulsion is applied to flying vehicles. Updated and strengthened throughout, the Eighth Edition explores: The fundamentals of rocket propulsion, its essential technologies, and its key design rationale The various types of rocket propulsion systems, physical phenomena, and essential relationships The latest advances in the field such as changes in materials, systems design, propellants, applications, and manufacturing technologies, with a separate new chapter devoted to turbopumps Liquid propellant rocket engines and solid propellant rocket motors, the two most prevalent of the rocket propulsion systems, with in-depth consideration of advances in hybrid rockets and electrical space propulsion Comprehensive and coherently organized, this seminal text guides readers evenhandedly through the complex factors that shape rocket propulsion, with both theory and practical design considerations. Professional engineers in the aerospace and defense industries as well as students in mechanical and aerospace engineering will find this updated classic indispensable for its scope of coverage and utility.
Category: Science

Fundamentals Of Theory And Calculation Of Liquid Propellant Rocket Engines

Author : A. P. Vasilyev
ISBN : OCLC:227536375
Genre : Liquid propellant rockets
File Size : 75.85 MB
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Theoretical and design principles of liquid rocket engines are presented. Extensive coverage is given to processes taking place in the combustion chamber, calculations of mixing systems, the cooling and contour calculation of the nozzles, calculation and selection of optimal parameters, turbopump and fuel feed pressurization systems, generation of the working medium for the turbine and fuel feed pressurization system, design and integration of pneumohydraulic systems for liquid rocket engines, calculation methods and selection of a liquid rocket engine parameters with a closed generation circuit of the working medium for the turbine. Basic theoretical and design principles of processes taking place in different types of liquid rocket engines are presented. The operation of main subsystems and the calculation of their characteristics are discussed. (Author).
Category: Liquid propellant rockets

Rocket Propulsion

Author : Books Llc
ISBN : 1156588707
Genre : Science
File Size : 40.96 MB
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Please note that the content of this book primarily consists of articles available from Wikipedia or other free sources online. Pages: 38. Chapters: Specific impulse, Aerospike engine, Rocket engine, Liquid-propellant rocket, Rocket engine nozzle, De Laval nozzle, Laser propulsion, Expansion deflection nozzle, Staged combustion cycle, Expander cycle, Regenerative cooling, Rocket engine test facility, Group for the Study of Reactive Motion, Cryogenic rocket engine, Nozzle extension, Retrorocket, Pressure-fed cycle, Ullage, Opel-RAK, Altitude compensating nozzle, Pulsed rocket motor, Thrust-decay time, Jet damping, Stepped nozzle, Characteristic velocity. Excerpt: A rocket engine, or simply "rocket," is a jet engine that uses only propellant mass for forming its high speed propulsive jet. Rocket engines are reaction engines and obtain thrust in accordance with Newton's third law. Since they need no external material to form their jet, rocket engines can be used for spacecraft propulsion as well as terrestrial uses, such as missiles. Most rocket engines are internal combustion engines, although non combusting forms also exist. Rocket engines as a group have the highest exhaust velocities, are by far the lightest, but are the least propellant efficient of all types of jet engines. Chemical rockets are rockets powered by exothermic chemical reactions of the propellant. Rocket motor (or solid-propellant rocket motor) is a synonymous term with rocket engine that usually refers to solid rocket engines. Liquid rockets (or liquid-propellant rocket engine) use one or more liquid propellants that are held in tanks prior to burning. Hybrid rockets have a solid propellant in the combustion chamber and a second liquid or gas propellant is added to permit it to burn. Thermal rockets are rockets where the propellant is inert, but is heated by a power source such as solar or nuclear power or beamed energy. Monopropellant rockets are rockets where the propellant is one chemical, t...
Category: Science

Practical Bases For The Design Of Liquid Propellant Rocket Engines

Author : Ph. D. James R.
ISBN : 1948117959
Genre : Science
File Size : 32.12 MB
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This volume sets forth the foundations for the design of liquid-fueled rocket engines. It discusses the operating modes, working process, and characteristics of the rocket and its chamber, the planning and design of atomizing devices and systems for delivering fuel into the chamber, as well as the specifications of the fuels used. The book also illuminates the problems of chamber cooling and operation and testing. This book is designed as a study aid for the higher technical schools in the corresponding specialties. It can also be used as a textbook for engineers and technicians working in this field.
Category: Science

Liquid Propellant Rocket Engine Injector Dynamics And Combustion Processes At Supercritical Conditions

Author :
ISBN : OCLC:74274847
Genre :
File Size : 41.50 MB
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The present AFOSR project focuses on the theoretical modeling and numerical simulation of liquid-propellant rocket engine injector flow and combustion dynamics. Emphasis is placed on cryogenic propellants in both shear and swirl co-axial injectors at supercritical conditions. The formulation is based on the full conservation equations in three dimensions, and accommodates variable properties and finite-rate chemical kinetics. Full account is taken of various high-pressure phenomena such as thermodynamic non- idealities and transport anomalies commonly observed in the transcritical regime. Furthermore, an efficient numerical framework utilizing state-of-the-art computer software and hardware technologies is implemented, such that sweeping calculations can be conducted within a realistic time frame. Various fundamental physiochemical mechanisms associated with cryogenic propellant injection, mixing, and combustion are studied systematically. Results have not only enhanced basic understanding of the subject problem, but also established a quantitative basis to identify and prioritize the key design parameters and flow variables that exert strong influences on the injector behavior in different environments.
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