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Rocket Propulsion Elements, Eighth Edition 9780470080245书籍详细信息
- ISBN：9780470080245
- 作者：暂无作者
- 出版社：暂无出版社
- 出版时间：2010-02
- 页数：784
- 价格：921.10
- 纸张：胶版纸
- 装帧：精装
- 开本：32开
- 语言：未知
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- TAG：暂无
- 豆瓣评分：暂无豆瓣评分
内容简介：
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.
书籍目录：
PREFACE.
1 Classification.
1.1. Duct Jet Propulsion.
1.2. Rocket Propulsion.
1.3. Applications of Rocket Propulsion.
References.
2 Definitions and Fundamentals.
2.1. Definitions.
2.2. Thrust.
2.3. Exhaust Velocity.
2.4. Energy and Efficiencies.
2.5. Multiple Propulsion Systems.
2.6. Typical Performance Values.
Problems.
Symbols.
References.
3 Nozzle Theory and Thermodynamic Relations.
3.1. Ideal Rocket.
3.2. Summary of Thermodynamic Relations.
3.3. Isentropic Flow Through Nozzles.
3.4. Nozzle Configurations.
3.5. Real Nozzles.
3.6. Nozzle Alignment.
Problems.
Symbols.
References.
4 Flight Performance.
4.1. Gravity-Free Drag-Free Space Flight.
4.2. Forces Acting on a Vehicle in the Atmosphere.
4.3. Basic Relations of Motion.
4.4. Space Flight.
4.5. Flight Maneuvers.
4.6. Effect of Propulsion System on Vehicle Performance.
4.7. Flight Vehicles.
4.8. Military Missiles.
4.9. Flight Stability.
Problems.
Symbols.
References.
5 Chemical Rocket Propellant Performance Analysis.
5.1. Background and Fundamentals.
5.2. Analysis of Chamber or Motor Case Conditions.
5.3. Analysis of Nozzle Expansion Processes.
5.4. Computer-Assisted Analysis.
5.5. Results of Thermochemical Calculations.
Problems.
Symbols.
References.
6 Liquid Propellant Rocket Engine Fundamentals.
6.1. Types of Propellants.
6.2. Propellant Tanks.
6.3. Propellant Feed Systems.
6.4. Gas Pressure Feed Systems.
6.5. Tank Pressurization.
6.6. Turbopump Feed Systems and Engine Cycles.
6.7. Rocket Engines for Maneuvering, Orbit Adjustments, or
Attitude Control.
6.8. Engine Families.
6.9. Valves and Pipelines.
6.10. Engine Support Structure.
Problems.
Symbols.
References.
7 Liquid Propellants.
7.1. Propellant Properties.
7.2. Liquid Oxidizers.
7.3. Liquid Fuels.
7.4. Liquid Monopropellants.
7.5. Gelled Propellants.
7.6. Gaseous Propellants.
7.7. Safety and Environmental Concerns.
Problems.
Symbols.
References.
8 Thrust Chambers.
8.1. Injectors.
8.2. Combustion Chamber and Nozzle.
8.3. Low-Thrust Rocket Thrust Chambers or Thrusters.
8.4. Materials and Fabrication.
8.5. Heat Transfer Analysis.
8.6. Starting and Ignition.
8.7. Random Variable Thrust.
8.8. Sample Thrust Chamber Design Analysis.
Problems.
Symbols.
References.
9 Liquid Propellant Combustion and Its Stability.
9.1. Combustion Process.
9.2. Analysis and Simulation.
9.3. Combustion Instability.
Problems.
References.
10 Turbopumps and Their Gas Supplies.
10.1. Introduction.
10.2. Descriptions of Several Turbopumps.
10.3. Selection of Turbopump Configuration.
10.4. Flow, Shaft Speeds, Power, and Pressure Balances.
10.5. Pumps.
10.6. Turbines.
10.7. Approach to Turbopump Preliminary Design.
10.8. Gas Generators and Preburners.
Problems.
Symbols.
References.
11 Engine Systems, Controls, and Integration.
11.1. Propellant Budget.
11.2. Performance of Complete or Multiple Rocket Propulsion
Systems.
11.3. Engine Design.
11.4. Engine Controls.
11.5. Engine System Calibration.
11.6. System Integration and Engine Optimization.
Problems.
Symbols.
References.
12 Solid Propellant Rocket Fundamentals.
12.1. Basic Relations and Propellant Burning Rate.
12.2. Other Performance Issues.
12.3. Propellant Grain and Grain Configuration.
12.4. Propellant Grain Stress and Strain.
12.5. Attitude Control and Side Maneuvers with Solid Propellant
Rocket Motors.
Problems.
Symbols.
References.
13 Solid Propellants.
13.1. Classification.
13.2. Propellant Characteristics.
13.3. Hazards.
13.4. Propellant Ingredients.
13.5. Other Propellant Categories.
13.6. Liners, Insulators, and Inhibitors.
13.7. Propellant Processing and Manufacture.
Problems.
References.
14 Solid Propellant Combustion and Its Stability.
14.1. Physical and Chemical Processes.
14.2. Ignition Process.
14.3. Extinction or Thrust Termination.
14.4. Combustion Instability.
Problems.
References.
15 Solid Rocket Components and Motor Design.
15.1. Motor Case.
15.2. Nozzles.
15.3. Igniter Hardware.
15.4. Rocket Motor Design Approach.
Problems.
References.
16 Hybrid Propellant Rockets.
16.1. Applications and Propellants.
16.2. Interior Hybrid Motor Ballistics.
16.3. Performance Analysis and Grain Configuration.
16.4. Design Example.
16.5. Combustion Instability.
Problems.
Symbols.
References.
17 Electric Propulsion.
17.1. Ideal Flight Performance.
17.2. Electrothermal Thrusters.
17.3. Nonthermal Electrical Thrusters.
17.4. Optimum Flight Performance.
17.5. Mission Applications.
17.6. Electric Space-Power Supplies and Power-Conditioning
Systems.
Problems.
Symbols.
References.
18 Thrust Vector Control.
18.1. TVC Mechanisms with a Single Nozzle.
18.2. TVC with Multiple Thrust Chambers or Nozzles.
18.3. Testing.
18.4. Integration with Vehicle.
Problems.
References.
19 Selection of Rocket Propulsion Systems.
19.1. Selection Process.
19.2. Criteria for Selection.
19.3. Interfaces.
References.
20 Rocket Exhaust Plumes.
20.1. Plume Appearance and Flow Behavior.
20.2. Plume Effects.
20.3. Analysis and Mathematical Simulation.
Problems.
References.
21 Rocket Testing.
21.1. Types of Tests.
21.2. Test Facilities and Safeguards.
21.3. Instrumentation and Data Management.
21.4. Flight Testing.
21.5. Postaccident Procedures.
References.
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.
作者介绍：
George P. Sutton is a consultant for the aerospace industry.
He formerly served as executive director of engineering at
Rocketdyne (Rocketdyne Division of The Boeing Company, now Pratt
& Whitney Rocketdyne) and as a laboratory associate at Lawrence
Livermore National Laboratory.
Oscar Biblarz is a Professor Emeritus in the Department of
Mechanical and Astronautical Engineering at the Naval Postgraduate
School in Monterey, California.
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原文赏析：
The chinese developed and used solid propellant in rocket missiles over 800 years ago and military bmbardment rockets were used frequently in the eighteenth and nineteenth centuries.
In solid propellant rockets it is difficult to measure the propellant flow rate accurately. Therefore, the specific impulse is often calculated from total impulse and the propellant weight (using the difference between initial and final motor weights and Eq. 2-5). In turn the total impulse is obtained from the integral of the measured thrust with time, using Eq. 2-1. In liquid propellant units it is possible to measure thrust and instantaneous propellant flow rate and thus to use Eq. 2-3 for calculation of specific impulse. Eq. 2-4 allows
another definition for specific impulse, namely, the amount of impulse imparted to a vehicle per unit sea-level weight of propellant expended.
其它内容：
书籍介绍
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.
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