Download or read book Thermodynamic Assessment of Rocket Engines written by Boris Aleksandrovitch Nikolaev and published by . This book was released on 1963 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Thermodynamic Assessment of Rocket Engines written by Boris Aleksandrovich Nikolaev and published by . This book was released on 1963 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Thermodynamic Assessment of Rocket Engines written by Boris Aleksandrovich Nikolaev and published by . This book was released on 1963 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Thermofluiddynamics of Optimized Rocket Propulsions written by STRAUB and published by Birkhäuser. This book was released on 2012-12-06 with total page 267 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study has two declared aims: it presents the theoretical basis for a provably ideal comparative process for relaxing flows (ICP) and jus tifies its application to jet and, in particular, rocket engines. This will be treated in two parts. Part I offers a status quo report on current calculation methods, and compiles and explains briefly the most important data on selected pro minent rocket engines. Starting from the phenomenology of the dynamical and physico-chemical conversion processes in the fuel-oxidizer fluid mixture and in the burned gases, the ideal thermodynamic comparative process is then derived - as a defined sequential change of states in the system. In order to render this comparative process readily under standable, it is first applied to an appropriate model gas using alge braic equations for all relevant parameters. This model gas undergoes energy conversion processes without forfeiting the simplicity of pre sentation typical of classical gas dynamics. Above all, examination of this model offers proof that it is generally impermissible to use, as is done in practice, the familiar isentropic equation for flow changes of state continuously propagated in flow tube theory. Elementary calculations immediately indicate essential attributes which are also typical for relaxing, multicomponent, one-phase systems, such as the significant 'pressure drop phenomenon' or the establishment of the steady mass flow rate as an 'eigenvalue' of the comparative pro cess. Their relevance to the RE theory is stressed.
Download or read book Fundamentals of Rocket Propulsion written by DP Mishra and published by CRC Press. This book was released on 2017-07-20 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
Download or read book Thermodynamic Analysis of Combustion Engines written by Ashley S. Campbell and published by John Wiley & Sons. This book was released on 1979-03-15 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt: Intended for a second course in thermodynamics. Explains in detail how the analysis of each engine system can be formulated for a computer program. Examines all present day engines which operate on the internal combustion system, including gas turbines, two-stroke and four-stroke internal combustion engines, both Otto and Diesel cycles, liquid propellant rockets, free piston engines, and powders in guns. Includes chemical equilibrium, explaining how equilibrium compositions in multireaction systems can be calculated. Uses SI units exclusively.
Download or read book Analysis of the Transient Radiation Heat Transfer of an Uncooled Rocket Engine Operating Outside Earth s Atmosphere written by William H. Robbins and published by . This book was released on 1959 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Chemical Rockets written by Subramaniam Krishnan and published by Springer Nature. This book was released on 2019-10-10 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this book is to discuss, at the graduate level, the methods of performance prediction for chemical rocket propulsion. A pedagogical presentation of such methods has been unavailable thus far and this text, based upon lectures, fills this gap. The first part contains the energy-minimization to calculate the propellant-combustion composition and the subsequent computation of rocket performance. While incremental analysis is for high performance solid motors, equilibrium-pressure analysis is for low performance ones. Both are detailed in the book's second part for the prediction of ignition and tail-off transients, and equilibrium operation. Computer codes, adopting the incremental analysis along with erosive burning effect, are included. The material is encouraged to be used and presented at lectures. Senior undergraduate and graduate students in universities, as well as practicing engineers and scientists in rocket industries, form the readership.
Download or read book Thermodynamic Analysis of Cryogenic Rocket Engines with Matlab Tools written by Juan Manuel García Sánchez and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The present Master Thesis discusses the efforts of the author to perform thethermodynamic analysis of two modern cryogenic rocket engines. The first one, withthe name SE21D, will be used as validation case to test the accuracy of the methodologydeveloped. Once it has been approved this simulation, the next step will consist in applythis scheme to the study case, called LE9.The special characteristic that distinguish these two models is the employment offeeding system type: Expander Bleed Cycle. They will be studied all the mechanicalcomponents that are involved in this feeding system, which includes pumps, turbines,mixer and valves. Secondary, the combustion process as well as the engine performanceare assessed. Finally, the heat exchange and regenerative cooling that occurs in theCombustion Chamber walls is modeled. The final results are accurate enough once thevalidity of this thermodynamic analysis model has been approved and this Master Thesisalso leaves room to future researchers to continue with this project.This simulation have been performed by means of an intensive bibliographic researchand the employment of MATLAB software and two additional packages, created in-housePolytechnic University of Catalonia and already validated, called HGS and INIST. Thislast one collects the fluid properties for the most common substances used as rocketpropellants and it was used to define the state of the fuel and oxidizer at each stage of thefeeding system. The latter, however, it is a chemical solver based on NASA's polynomialsand it was utilized mainly in the combustion process that takes places in the CombustionChamber of both rocket engines.Nevertheless, the features of these two additional software packages were not enoughto accomplish the goal of this Master Thesis. For that reason, the author performedmaintenance and updating tasks of INIST package. The capacity of adding new data wasrestored as well as the inclusion of new fluid properties that complements the existing one,such as the transport properties (viscosity and thermal conductivity). Indeed, for thoseconditions that are out of the range of this tool, it was developed an approach based onsemi-empirical models to the obtaining of these magnitudes.
Download or read book Thermodynamic Calculations for Rocket Engines written by Boris Aleksandrovich Nikolaev and published by . This book was released on 1962 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents an approximate method for the calculation of thermodynamic parameters of the products of combustion in a rocket engine, as well as a method for the calculation of the specific thrust, without a determination of the composition of the products of combustion. The proposed method will make it possible to calculate these parameters with relatively little effort but with a sufficient degree of accuracy from the practical standpoint. This method is valid for the products of combustion of fuels composed of C, H, N, and O, with some reservations with regard to the method for the latter. E amples of the calculations are presented. In addition, there is a description of a method for the determination of the composition of the products of combustion from the indicated fuels. (Author).
Download or read book Thermodynamic and Ballistic Design Fundamentals of Solid propellant Rocket Engines written by Boris Viktorovich Orlov and published by . This book was released on 1966 with total page 422 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this book, on the basis of materials published in the Soviet and foreign press, there are expounded thermo-gas-dynamic principles of designing of rocket engines, engineering methods of calculation of processes of heat exchange, principles of the theory of burning of solid fuels and calculation of the indicated pressure curve in the combustion chamber of the engine. In it there is given basic information about solid rocket propellants applied in solid-propellant rocket engines (SPRE). There is considered regulation of thrust in SPRE in magnitude and direction, and also a general method of ballistic designing of solid-fuel rockets. (Author).
Download or read book Thermofluiddynamics of Optimized Rocket Propulsions written by STRAUB and published by Birkhäuser. This book was released on 1989-04-01 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study has two declared aims: it presents the theoretical basis for a provably ideal comparative process for relaxing flows (ICP) and jus tifies its application to jet and, in particular, rocket engines. This will be treated in two parts. Part I offers a status quo report on current calculation methods, and compiles and explains briefly the most important data on selected pro minent rocket engines. Starting from the phenomenology of the dynamical and physico-chemical conversion processes in the fuel-oxidizer fluid mixture and in the burned gases, the ideal thermodynamic comparative process is then derived - as a defined sequential change of states in the system. In order to render this comparative process readily under standable, it is first applied to an appropriate model gas using alge braic equations for all relevant parameters. This model gas undergoes energy conversion processes without forfeiting the simplicity of pre sentation typical of classical gas dynamics. Above all, examination of this model offers proof that it is generally impermissible to use, as is done in practice, the familiar isentropic equation for flow changes of state continuously propagated in flow tube theory. Elementary calculations immediately indicate essential attributes which are also typical for relaxing, multicomponent, one-phase systems, such as the significant 'pressure drop phenomenon' or the establishment of the steady mass flow rate as an 'eigenvalue' of the comparative pro cess. Their relevance to the RE theory is stressed.
Download or read book A Thermodynamic Analysis of Thrust Augmentation for Nuclear Rockets written by Hugh M. Henneberry and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Design and Thermodynamic Analysis of a Hydrogen oxygen Rocket Engine Test Facility written by Edward Herbert Stanton and published by . This book was released on 1969 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computer Code for Single Point Thermodynamic Analysis of Hydrogen Oxygen Expander Cycle Rocket Engines written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-16 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This analysis and this computer code apply to full, split, and dual expander cycles. Heat regeneration from the turbine exhaust to the pump exhaust is allowed. The combustion process is modeled as one of chemical equilibrium in an infinite-area or a finite-area combustor. Gas composition in the nozzle may be either equilibrium or frozen during expansion. This report, which serves as a users guide for the computer code, describes the system, the analysis methodology, and the program input and output. Sample calculations are included to show effects of key variables such as nozzle area ratio and oxidizer-to-fuel mass ratio. Glassman, Arthur J. and Jones, Scott M. Glenn Research Center NASA-TM-4275, E-5652, NAS 1.15:4275 RTOP 505-69-01...
Download or read book Analysis of Effects of Rocket engine Design Parameters on Regenerative cooling Capabilities of Several Propellants written by Arthur N. Curren and published by . This book was released on 1959 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computer Code for Single point Thermodynamic Analysis of Hydrogen oxygen Expander cycle Rocket Engines written by Arthur J. Glassman and published by . This book was released on 1991 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
