Rocket Propulsion Elements

George P. Sutton, Oscar Biblarz

• Publisher: Wiley
• Year: 2016
• Print ISBN: 9781118753651
• eBook ISBN: 9781118753910
• Edition: 9
• Topic: Technology & Engineering
• Subtopic: Aeronautic & Astronautic Engineering
• Index: Technology & Engineering

ROCKET PROPULSION ELEMENTS

THE DEFINITIVE INTRODUCTION TO ROCKET PROPULSION THEORY AND APPLICATIONS

The recent upsurge in global government and private spending and in space flight events has resulted in many novel applications of rocket propulsion technology. Rocket Propulsion Elements remains the definitive guide to the field, providing a comprehensive introduction to essential concepts and applications. Led by industry veteran George P. Sutton and by Professor Oscar Biblarz, this book provides interdisciplinary coverage including thermodynamics, aerodynamics, flight performance, propellant chemistry and more.

This thoroughly revised ninth edition includes discussion and analysis of recent advances in the field, representing an authoritative reference for students and working engineers alike. In any engineering field, theory is only as useful as it is practical; this book emphasizes relevant real-world applications of fundamental concepts to link "thinking" and "doing". This book will help readers:

• Understand the physics of flight and the chemistry of propulsion
• Analyze liquid, solid, gas, and hybrid propellants, and the engines they fuel
• Consider high-temperature combustion, stability, and the principles of electric and chemical propulsion
• Dissect the workings of systems in common use around the world today
• Delve into the latest advances in materials, systems, propellants, and more

Broad in scope, rich in detail, and clear in explanation, this seminal work provides an unparalleled foundation in aerospace engineering topics. Learning through the lens of modern applications untangles complex topics and helps students fully grasp the intricacies on a more intuitive level. Rocket Propulsion Elements, Ninth Edition merges information and utility building a solid foundation for innovation.

CHAPTER 1
CLASSIFICATION

In general terms, propulsion is the act of changing the motion of a body with respect to an inertial reference frame. Propulsion systems provide forces that either move bodies initially at rest or change their velocity or that overcome retarding forces when bodies are propelled through a viscous medium. The word propulsion comes from the Latin propulsus, which is the past participle of the verb propellere, meaning “to drive away.” Jet propulsion is a type of motion whereby a reaction force is imparted to a vehicle by the momentum of ejected matter.

Rocket propulsion is a class of jet propulsion that produces thrust by ejecting matter, called the working fluid or propellant, stored entirely in the flying vehicle. Duct propulsion is another class of jet propulsion and it includes turbojets and ramjets; these engines are more commonly called air‐breathing engines. Duct propulsion devices mostly utilize their surrounding medium as the propellant, energized by its combustion with the vehicle's stored fuel. Combinations of rockets and duct propulsion devices have been attractive for some applications, and one is briefly described in this chapter.

The energy source most commonly used in rocket propulsion is chemical combustion. Energy can also be supplied by solar radiation and by a nuclear reactor. Accordingly, the various propulsion devices in use can be divided into chemical propulsion, nuclear propulsion, and solar propulsion. Table 1–1 lists many important propulsion concepts according to their energy source and type of propellant. Radiant energy may originate from sources other than the sun and theoretically includes the transmission of energy by ground‐based microwaves and laser beams. Nuclear energy originates in transformations of mass within atomic nuclei and is generated by either fission or fusion. Energy sources are central to rocket performance and several kinds, both within and external to the vehicle, have been investigated. The useful energy input modes in rocket propulsion systems are either heat or electricity. Useful output thrust comes from the kinetic energy of the ejected matter and from the propellant pressure on inner chamber walls and at the nozzle exit; thus, rocket propulsion systems primarily convert input energies into the kinetic energy of the exhausted gas. The ejected mass can be in a solid, liquid, or gaseous state. Often, combinations of two or more phases are ejected. At very high temperatures, ejected matter can also be in a plasma state, which is an electrically conducting gas.

Table 1–1 Energy Sources and Propellants for Various Propulsion Concepts

	Energy Source^a
Propulsion Device	Chemical	Nuclear	Solar	Propellant or Working Fluid
Turbojet	D/P			Fuel + air
Turbo–ramjet	TFD			Fuel + air
Ramjet (hydrocarbon fuel)	D/P	TFD		Fuel + air
Ramjet (H2 cooled)	TFD			Hydrogen + air
Rocket (chemical)	D/P	TFD		Stored propellant
Ducted rocket	TFD			Stored solid fuel + surrounding air
Electric rocket	D/P		D/P	Stored propellant
Nuclear fission rocket		TFD		Stored H2
Solar‐heated rocket			TFD	Stored H2
Photon rocket (big light bulb)		TFND		Photon ejection (no stored propellant)
Solar sail			TFD	Photon reflection (no stored propellant)

^aD/P developed and/or considered practical; TFD, technical feasibility has been demonstrated, but development is incomplete; TFND, technical feasibility has not yet been demonstrated.

1.1 DUCT JET PROPULSION

This class, commonly called air‐breathing engines, comprises devices which entrain and energize air flow inside a duct. They use atmospheric oxygen to burn fuel stored in the flight vehicle. This class includes turbojets, turbofans, ramjets, and pulsejets. These are mentioned here primarily to provide a basis for comparison with rocket propulsion and as background for combined rocket–duct engines, which are mentioned later. Table 1–2 compares several performance characteristics of specific chemical rockets with those of typical turbojets and ramjets. A high specific impulse (which is a measure of performance to be defined later) relates directly to long‐flight ranges and thus indicates the superior range...

Table of contents

• Cover
• Title Page
• Copyright
• Table of Contents
• Preface
• Chapter 1: Classification
• Chapter 2: Definitions and Fundamentals
• Chapter 3: Nozzle Theory and Thermodynamic Relations
• Chapter 4: Flight Performance
• Chapter 5: Chemical Rocket Propellant Performance Analysis
• Chapter 6: Liquid Propellant Rocket Engine Fundamentals
• Chapter 7: Liquid Propellants
• Chapter 8: Thrust Chambers
• Chapter 9: Liquid Propellant Combustion and Its Stability
• Chapter 10: Turbopumps and Their Gas Supplies
• Chapter 11: Engine Systems, Controls, and Integration
• Chapter 12: Solid Propellant Rocket Motor Fundamentals
• Chapter 13: Solid Propellants
• Chapter 14: Solid Propellant Combustion and Its Stability
• Chapter 15: Solid Rocket Motor Components and Design
• Chapter 16: Hybrid Propellants Rocket Propulsion
• Chapter 17: Electric Propulsion
• Chapter 18: Thrust Vector Control
• Chapter 19: Selection of Rocket Propulsion Systems
• Chapter 20: Rocket Exhaust Plumes
• Chapter 21: Rocket Testing
• Appendix 1: Conversion Factors and Constants
• Appendix 2: Properties of the Earth's Standard Atmosphere
• Appendix 3: Summary of Key equations for Ideal Chemical Rockets
• Index
• Wiley End User License Agreement