Performance Analysis of a Liquid/Gel Rocket Engine During Operation
Performance Analysis of a Liquid/Gel Rocket Engine During Operation

Author: Minchao Huang

Publisher: Springer

Published: 2024-10-30

Total Pages: 0

ISBN-13: 9789819764846

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This open access book takes space propulsion system, gel propulsion system, and pumped liquid rocket engine as research objects and establishes and describes the theory, dynamic model, and numerical calculation method of working process of liquid/gel rocket engine. The first part of this book establishes a mathematical model for the working process of the space propulsion system, including a mathematical model for gas cylinders, an electric explosion valve, a pressure reducing valve, a storage tank, a liquid pipeline, an orifice and filter, an electromagnetic valve, a filling pipeline, and a thrust chamber. The simulation analyzes the characteristics of the start-up, steady-state, and shutdown processes of the space propulsion system. In the second part, the mathematical model of the working process of gel propulsion system is established, and the flow distribution law, water hammer characteristics, and thrust regulation characteristics of gel propulsion system are simulated and analyzed. The third part establishes a mathematical model for the working process of a pumped liquid rocket engine and simulates and analyzes the starting process characteristics of the pumped liquid rocket engine. The above theory or dynamic model reflects the latest research results of the working process of liquid/gel rocket engine. This book is used as a teaching material or reference book for teachers, students, and scientific and technological personnel engaged in the simulation analysis of the working process of liquid/gel rocket engines in the fields of aerospace, aviation, power, etc.

Liquid Rocket Engine
Liquid Rocket Engine

Author: Rene Nardi Rezende

Publisher: SAE International

Published: 2018-11-15

Total Pages: 158

ISBN-13: 0768095425

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The great engineering achievement required to overcome most of the challenges and obstacles that prevented turning rocket design from art into science took place in Europe and the United States between the 1930s and the 1950s. With the vast majority of the engines currently in operation developed in the “pre-computer” age, there are new opportunities to update the design methodologies using technology that can now handle highly complex calculations fast. The space sector with an intense focus on efficiency is driving the need for updating, adapting or replacing the old modeling practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book 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. It addresses the operating characteristics and dimensioning of some thrust chamber elements through a set of equations and parameters, which include thrust or propellant characteristics. The model degree of sophistication was adjusted to the requirements of the Project Life Cycle Phase B, while also enabling quick analysis of new configurations from changes in initial project parameters.

Fundamentals of Rocket Propulsion
Fundamentals of Rocket Propulsion

Author: DP Mishra

Publisher: CRC Press

Published: 2017-07-20

Total Pages: 364

ISBN-13: 1351708414

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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.

An Analysis of the Accuracy of Liquid-propellant Rocket Engine Performance Measurements in the Propulsion Engine Test Cell (j-2a).
An Analysis of the Accuracy of Liquid-propellant Rocket Engine Performance Measurements in the Propulsion Engine Test Cell (j-2a).

Author: C. W. Harper

Publisher:

Published: 1965

Total Pages: 39

ISBN-13:

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Measurements obtained during recent testing in the Propulsion Engine Test Cell (J-2A) are analyzed to determine the accuracy of measuring liquid-propellant rocket engine performance. The equipment and calibration techniques used to obtain the data and the statistical methods employed for error analysis are discussed. The results demonstrated that the one standard deviation errors in thrust, chamber pressure, cell pressure, oxidizer flow rate, and fuel flow rate measurements are less than =0.110, =0.198, =0.769, =0,181, and =0.150%, respectively. The accuracy of the primary calculated performance parameters, thrust coefficient, specific impulse, and characteristic velocity, are =0.226, =0.166, and =0.234% (one standard deviation), respectively. (Author).

Liquid Rocket Engine Combustion Instability
Liquid Rocket Engine Combustion Instability

Author: Vigor Yang

Publisher: AIAA (American Institute of Aeronautics & Astronautics)

Published: 1995

Total Pages: 600

ISBN-13:

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Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASAs Liquid Rocket Combustion Instability (NASA SP-194) in 1972. Improved computational and experimental techniques, coupled with a number of experiences with full-scale engines worldwide, have offered opportunities for advancement of the state of the art. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and Chinaa first. Engineers and scientists in propulsion, power generation, and combustion instability will find the 20 chapters valuable as an extension of prior work and as a reference.

Simplified Liquid Rocket Engine Performance and Weight Model
Simplified Liquid Rocket Engine Performance and Weight Model

Author:

Publisher:

Published: 2003

Total Pages: 0

ISBN-13:

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The Air Force Research Laboratory is developing a tool to analyze liquid propellant launch systems. This tool, called Integrated Propulsion Analysis Tool (IPAT), requires the capability to predict the weight of the vehicle components as well as the performance of the rocket engines. For IPAT, a simplified model was developed to predict liquid rocket engine (LRE) performance and weight. The LRE model was developed to be very flexible and model a wide variety of rocket engines. The model allows the user to select the propellants used for the fuel and oxidizer from a list that includes hydrogen, hydrocarbons such as RP-1, storable propellants, and oxygen. The user can select the engine power cycle from a list that includes expander, staged combustion, gas generator, and pressure fed. Other parameters used by the model include engine thrust, chamber pressure, overall engine mixture ratio, nozzle exit area ratio, and materials of manufacture. The model uses a combination of physical relationships and weight correlations to calculate the weight of individual rocket engine components. The model predicts liquid rocket engine performance using combustion gas properties provided by the Chemical Equilibrium with Applications (CEA) computer code. This paper will describe the analysis approach used in the model and show comparisons of weight predictions to actual flight rocket engines.