Hybrid Rocket Propulsion Design Handbook

1st Edition - October 7, 2023
Authors: Ashley Chandler Karp, Elizabeth Therese Jens
Language: English
Paperback ISBN:
9 7 8 - 0 - 1 2 - 8 1 6 1 9 9 - 9
eBook ISBN:
9 7 8 - 0 - 1 2 - 8 1 6 5 9 3 - 5

Hybrid Rocket Propulsion Design Handbook provides system scaling laws, design methodologies, and a summary of available test data, giving engineers all the tools they need to dev… Read more

Purchase options

LIMITED OFFER

Save 50% on book bundles

Immediately download your ebook while waiting for your print delivery. No promo code is needed.

Institutional subscription on ScienceDirect

Request a sales quote

Resources

Textbook support for instructors(opens in new tab/window)

Hybrid Rocket Propulsion Design Handbook provides system scaling laws, design methodologies, and a summary of available test data, giving engineers all the tools they need to develop realistic hybrid system designs.Important supporting theory from chemistry, thermodynamics, and rocket propulsion is addressed, helping readers from a variety of backgrounds to understand this interdisciplinary subject. This book also suggests guidelines for standardized reporting of test data, in response to difficulties researchers have in working with results from different research institutes.

Cover image
Title page
Table of Contents
Copyright
Dedication
List of tables
References
List of figures
References
Nomenclature
Chapter 1: Introduction
Abstract
1.1. Chemical propulsion overview
1.2. What is a hybrid rocket?
1.3. Comparison of chemical propulsion systems
1.4. Benefits and challenges of hybrid propulsion systems
1.5. Applications
1.6. History and current programs
1.7. Commonly used terms
1.8. Book layout
References
Chapter 2: Introduction to rocket propulsion
Abstract
2.1. Introduction
2.2. Key parameters
2.3. Nozzles
2.4. Rocket equation
2.5. Examples of ΔV's
2.6. Staging
References
Chapter 3: Hybrid rocket theory
Abstract
3.1. Introduction
3.2. Classical fuels theory
3.3. Liquefying fuels
3.4. Theory applied to single port hybrid design
3.5. Regression rate enhancements
3.6. Transients
References
Chapter 4: Thermodynamics and chemistry
Abstract
4.1. Introduction
4.2. Key terms
4.3. Ideal gas mixtures
4.4. Real gases
4.5. Enthalpy
4.6. Stoichiometry and complete combustion
4.7. Thermodynamic laws
4.8. Example combustion problem
4.9. Conditions through the nozzle
4.10. Commercial combustion codes
References
Chapter 5: Propellants
Abstract
5.1. Introduction
5.2. Fuels
5.3. Oxidizers
5.4. Additives
5.5. Theoretical performance of common combinations
References
Chapter 6: Hybrid regression rate data
Abstract
6.1. Introduction
6.2. Regression rate reconstruction methods
6.3. Important parameters
6.4. Regression rate prediction method
6.5. Published regression rate data
References
Chapter 7: Hybrid design
Abstract
7.1. Introduction
7.2. Overview
7.3. Mission selection
7.4. Inputs
7.5. Performance calculation
7.6. Motor ballistics, packaging and outputs
7.7. Performance predictions
7.8. Design assessment
7.9. Residuals
7.10. Combustion chamber and nozzle mass
7.11. Tank masses
7.12. Pressurization subsystem
7.13. Other masses
7.14. Mass margin
7.15. Mass evaluation
7.16. Other considerations
References
Chapter 8: Hybrid design challenges
Abstract
8.1. Introduction
8.2. Incompressible feed line analysis
8.3. Compressible feed line analysis
8.4. Combustion instabilities
8.5. Propellant budgeting in flight
References
Chapter 9: Hardware design
Abstract
9.1. Introduction
9.2. Valves
9.3. Tanks
9.4. Other components
9.5. Instrumentation
9.6. Injection
9.7. Combustion chamber design
9.8. Nozzles and thrust vector control
9.9. Ignition
9.10. Component selection
9.11. Reliability
9.12. Range safety
9.13. Qualification
9.14. Design for manufacturability
References
Chapter 10: Design examples
Abstract
10.1. Mission requirements
10.2. Propellant selection
10.3. Staging - Mars Ascent Motor
10.4. Test/performance prediction
10.5. In-space motors
10.6. Pressurization selection
10.7. Large-scale motor
References
Chapter 11: Testing
Abstract
11.1. Introduction
11.2. Fuel characterization testing
11.3. Standard test practices
11.4. Safety
11.5. Oxidizer safety
11.6. Designing a ground feed system
11.7. Reporting test data
11.8. Real world example: Peregrine
References
Appendix A: Derivations
A.1. Launch mission design governing equations
A.2. Thrust
A.3. Rocket equation
A.4. Water hammer pressure surge
A.5. Flow through a venturi
References
Appendix B: Common oxidizer material compatibility
References
Appendix C: Summary of design equations
References
References
Index

Ashley Chandler Karp

Dr. Ashley Chandler Karp is the Mars Launch System Manager for the Sample Retrieval Lander at the Jet Propulsion Laboratory. Dr. Karp has designed and built multiple hybrid rocket test facilities. She was the Principal Investigator for the Hybrid Propulsion Test Facility, where she designed, built and tested hybrid rocket motors for Mars In Situ Resource Utilization (ISRU) and interplanetary CubeSats/SmallSats (6U+). Dr. Karp led a hybrid technology development program for a potential Mars Ascent Vehicle from a clean sheet design using a new propellant combination, through subscale and full scale testing, towards technology infusion. As a technologist and propulsion engineer at JPL, she worked on a low-cost ventilator, lead the technology development for pyrotechnic paint for planetary protection, contributed to the ballute inflation aide for the Low Density Supersonic Decelerator. She was also the cognizant engineer for multiple propulsion components on the Mars 2020 cruise and descent stage propulsion systems. Dr. Karp earned an M.S. and Ph.D. in Aeronautics and Astronautics from Stanford University, where she specialized in hybrid rocket propulsion. While at Stanford, she designed, built and operated a test facility to visualize hybrid rocket combustion (slab burner). She completed her bachelor’s degree at the University of California, Berkeley, with a triple major in Astrophysics, Physics and Political Science. She is a former Chair of the AIAA Hybrid Rocket Propulsion Technical Committee.

Affiliations and expertise

Mars Launch System Manager, Sample Retrieval Lander, Jet Propulsion Laboratory, CA, USA

Elizabeth Therese Jens

Dr. Elizabeth Jens is a Propulsion and Systems Engineer at the NASA Jet Propulsion Laboratory in California. She is currently the Assistant Product Delivery Manager for the propulsion subsystem of the Sample Retrieval Lander. She is also active in technology development for hybrid rocket propulsion systems and was the cognizant engineer for the gas Dust Removal Tool on the turret of the Perseverance Rover. Dr. Jens has conducted over 70 successful hybrid rocket hot fire tests and has conducted a variety of propulsion system trades for a range of space missions. Dr. Jens was recognized as a Global Australian Award Game Changer in 2022, a Vogue Game Changer in 2018 and as one of Australia’s Most Innovative Engineers of 2017 as Determined by Engineers Australia. She has twice been an Amelia Earhart Fellow (2012 and 2014), was a Rotary Ambassadorial Scholar (2010) and the Australian Fulbright Scholar in Science and Engineering (2010). Dr. Jens received a Ph.D. in Aeronautics and Astronautics from Stanford University in 2016. She received a bachelor of science in physics and a bachelor of mechanical engineering from the University of Melbourne, Australia in 2008. She was the former chair of the ASME Propulsion Technical Committee and is a current member of the ASME Aerospace Division Executive Committee, the Propulsion Technical Committee of the IAF, and the Hybrid Rocket Technical Committee of AIAA

Affiliations and expertise

Propulsion and Systems Engineer, NASA Jet Propulsion Laboratory and Assistant Product Delivery Manager, Propulsion Subsystem of the Sample Retrieval Lander, CA, USA