Future Propulsion Systems for Space Exploration – Online Short Course 5 April 2027 - 12 May 2027 Online

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Future Propulsion Systems for Space Exploration – Online Short Course


  • From 5 April–12 May 2027 (6 Weeks, 12 Classes, 24 Total Hours)
  • Every Monday and Wednesday at 1–3 p.m. Eastern Time (all sessions will be recorded and available for replay; course notes will be available for download)
  • This new holistic course examines the relationship among propulsion, vehicle configuration, and mission requirements across space transportation and exploration.
  • All students will receive an AIAA Certificate of Completion at the end of the course.

OVERVIEW

Future space missions will place increasingly diverse demands on space transportation systems, ranging from launch and orbital operations to transportation within the Earth–Moon system and exploration of the Solar System. Meeting these requirements will require propulsion systems and vehicle configurations that are appropriately matched to mission objectives, performance requirements, and operational needs.

Explore how propulsion technologies can enable future space transportation and exploration missions, from launch and orbital operations to lunar, planetary, and far-future missions. The course provides a broad, integrated examination of propulsion systems and their relationship to vehicle and mission requirements. It considers the capabilities and limitations of conventional chemical propulsion and examines alternative and emerging technologies that may enable new approaches to space transportation and exploration.

The course begins with the fundamental energy, performance, and operational requirements associated with space missions and examines how those requirements influence vehicle configuration and propulsion-system selection. Topics include rocket propulsion, airbreathing and combined-cycle concepts, on-orbit transportation, nuclear thermal and nuclear electric propulsion, and other emerging propulsion technologies.

Particular emphasis is placed on the relationships among mission requirements, vehicle configuration, propulsion-system characteristics, and overall vehicle performance. A parametric vehicle-sizing methodology is introduced, and representative vehicle concepts, mission scenarios, simulation results, and propulsion-system comparisons are used to illustrate potential solutions across a broad range of transportation and exploration missions. The course concludes with an examination of emerging propulsion technologies and their potential to enable increasingly ambitious space exploration missions.

LEARNING OBJECTIVES
At the conclusion of this course, participants will be able to:

  • Explain how mission objectives, operational requirements, and energy and performance demands influence propulsion-system and vehicle requirements.
  • Describe the principal propulsion-system options applicable to launch, orbital transportation, Earth–Moon missions, and Solar System exploration.
  • Compare the characteristics, capabilities, and limitations of different propulsion approaches and explain their suitability for different mission and vehicle concepts.
  • Use a parametric vehicle-sizing methodology to examine the relationship between mission requirements and potential vehicle solutions.
  • Explain important interactions among propulsion systems, vehicle configuration, structures, materials, thermal considerations, and overall vehicle performance.
  • Assess the potential, limitations, and development challenges associated with emerging propulsion technologies for future space transportation and exploration.

AUDIENCE
This course is intended for engineers, analysts, researchers, scientists, and technical managers who need a broad understanding of propulsion systems and their role in future space transportation and exploration.

It will be particularly useful for professionals involved in mission analysis, systems engineering, conceptual and preliminary vehicle design, propulsion, advanced vehicle concepts, technology assessment, and strategic planning. The course is also appropriate for aerospace professionals who work primarily in one technical discipline and need a broader understanding of the relationships among mission requirements, vehicle configuration, and propulsion-system selection.

COURSE FEES (Sign-In To Register)
– AIAA Member Price: $995 USD
– Non-Member Price: $495 USD
– AIAA Student Member Price: $1,195 USD

CLASSROOM HOURS / CEUs: 24 classroom hours / 2.4 CEU/PDH

CANCELLATION POLICY: A refund less a $50.00 cancellation fee will be assessed for all cancellations made in writing prior to 5 days before the start of the event. After that time, no refunds will be provided.

CONTACT: Please contact Lisa Le if you have any questions about the course or group discounts (for 5+ participants).

Frequently Asked Questions

Outline

OUTLINE

1. Overview
1.1 The Challenge
1.2 Historical Developments
1.3 Challenge of Flying to Space
1.4 Operational Requirements
1.5 Operational Space Distances, Speed, and Times
1.6 Implied Propulsion Performance
1.7 Propulsion Concepts Available for Solar System Exploration

2. Our Progress Appears to Be Impeded
2.1 Meeting the Challenge
2.2 Early Progress in Space
2.3 Historical Analog
2.4 Evolution of Space Launchers from Ballistic Missiles
2.5 Conflicts Between Expendable Rockets and Reusable Airbreathers
2.6 Commercialization and Exploration Roadmap

3. Commercial Near-Earth Space Launcher: Understanding System Integration
3.1 Missions and Geographical Considerations
3.2 Energy, Propellants, and Propulsion Requirements
3.3 Energy Requirements to Change Orbital Altitude
3.4 Operational Concepts Anticipated for Future Missions
3.5 Configuration Concepts
3.6 Takeoff and Landing Mode
3.7 Transatmospheric Launcher Sizing
3.8 Available Solution Space: Examples
3.9 Hypersonic Configurations: Geometric Characteristics

4. Commercial Near-Earth Launcher: Propulsion Choices
4.1 Propulsion System Alternatives
4.2 Propulsion System Characteristics
4.3 Airflow Energy Entering the Engine
4.4 Internal Flow Energy Losses
4.5 Spectrum of Airbreathing Operation
4.6 Design Space Available – Interaction of Propulsion and Materials/Structures
4.7 Major Sequence of Propulsion Cycles
4.8 Rocket-Derived Propulsion
4.9 Airbreathing Rocket Propulsion
4.10 Thermally Integrated Combined-Cycle Propulsion
4.11 Engine Thermal Integration
4.12 Total System Thermal Integration
4.13 Thermally Integrated Enriched Air Combined-Cycle Propulsion
4.14 Comparison of Continuous Operation Cycles
4.15 Conclusions with Respect to Continuous Operation Cycles
4.16 Pulse Detonation Engines
4.17 Conclusions with Respect to Pulse Detonation Cycles
4.18 Comparison of Continuous Operation and Pulsed Cycles
4.19 Integrated Launcher Sizing with Different Propulsion Systems
4.20 Structural Concept and Structural Index
4.21 Sizing Results for Continuous and Pulse Detonation Engines
4.22 Operational Configuration Concepts: SSTO And TSTO
4.23 Emerging Propulsion System Concepts in Development

5. Earth Orbit on-Orbit Operations in Near-Earth
5.1 Energy Requirements
5.2 Launcher Propulsion System Characteristics
5.3 Maneuver Between LEO And GEO, Change in Altitude at Same Orbital Inclination
5.4 Changes in Orbital Inclination
5.5 Representative Space Transfer Vehicles
5.6 Operational Considerations
5.7 Observations and Recommendations

6. Earth–Moon System: Establishing a Solar System Presence
6.1 Earth–Moon Characteristics
6.2 Requirements to Travel to the Moon
6.3 History
6.4 Natural Versus Artificial Orbital Station Environments
6.5 Moon Base Functions

7. Exploration of Our Solar System
7.1 Review of Our Solar System Distances, Speeds, and Propulsion Requirements
7.2 Alternative Energy Sources: Nuclear Energy
7.3 Limits of Chemical Propulsion and Alternatives
7.4 Nuclear Propulsion Strategies
7.5 Nuclear Propulsion: A Historical Perspective
7.6 Nuclear Propulsion: Current Scenarios
7.7 Fundamentals of Nuclear Fission
7.8 Solid Core NTR
7.9 Particle Bed Reactor Technology
7.10 CERMET Technology
7.11 MITEE NTR
7.12 Gas Core NTR
7.13 Rubbia’s Engine
7.14 Considerations About NTR Propulsion
7.15 Hybrid Nuclear Rockets
7.16 Nuclear Electric Propulsion (NEP)
7.17 Nuclear Arcjet Rockets
7.18 Nuclear Electric Rockets
7.19 Electrostatic Ion Thrusters
7.20 MPD/MHD Thrusters
7.21 Hybrid NTR/NER Engines
7.22 Inductively Heated NTR
7.23 VASIMR (Variable Specific Impulse Magneto-Plasma-Dynamic Rocket)
7.24 Propulsion Strategies Compared
7.25 Conclusions

8. Stellar and Interstellar Precursor Missions
8.1 Introduction
8.2 Propulsion for Quasi-Interstellar and Stellar Missions
8.3 Traveling at Relativistic Speeds
8.4 Power for Quasi-Interstellar and Stellar Propulsion
8.5 Fusion Propulsion
8.6 Fusion Fuels and Their Kinetics
8.7 Fusion Propulsion Strategies
8.8 Fusion Propulsion Reactor Concepts
8.9 Magnetic Confinement Reactors (MCR)
8.10 Mirror Magnetic Confinement Rockets (Mirror MCR)
8.11 Inertial Confinement Fusion
8.12 Inertial Electrostatic Confinement (IEC) Fusion
8.13 MCF and ICF Fusion: A Comparison
8.14 Magnetic-Inertial Confinement (MIC) Fusion
8.15 Fusion Propulsion Summary
8.16 Antimatter Propulsion
8.17 Impulsive Propulsion
8.18 Photonic Propulsion
8.19 Conclusions: Can We Reach Stars?

9. View to the Future and Exploration of Our Galaxy
9.1 Introduction
9.2 Issues in Developing Near- and Far-Galactic Space Exploration
9.3 Black Holes and Galactic Travel
9.4 Breakthrough Physics and Propulsion
9.5 Superluminal Speed: Is It Required?
9.6 Conclusions

Supplemental Notes:
Radiation – Risks, Dose Assessment and Shielding
Assessment of Open Magnetic Fusion for Space Propulsion

Materials

COURSE DELIVERY AND MATERIALS

  • The course lectures will be delivered via Zoom. Access to the Zoom classroom will be provided to registrants near to the course start date.
  • All sessions will be available on-demand within 1-2 days of the lecture. Once available, you can stream the replay video anytime, 24/7.
  • All slides will be available for download after each lecture. No part of these materials may be reproduced, distributed, or transmitted, unless for course participants. All rights reserved.
  • This course material refers to the well-known Future Spacecraft Propulsion Systems and Integration – Enabling Technologies for Space Exploration by P.A. Czysz, C. Bruno and B. Chudoba, Third Edition, Springer Praxis Books, 2018.
  • Between lectures during the course, the instructor(s) will be available via email for technical questions and comments.
Instructor

Dr. Bernd Chudoba
Dr. Chudoba earned the PhD at Cranfield University, England, in 2001. From 1989 to today, Dr. Chudoba is systematically building an understanding of the multi-disciplinary complexity inherent in conventional & unconventional aerospace vehicle applications. The development of this aerospace synthesis mindset and capability has been triggered while working with the future project departments of EADS Airbus GmbH, Airbus UK (British Aerospace), Airbus France (Aérospatiale Aéronautique), Airbus Industrie, and Fairchild Dornier, where he was responsible for conceptual/preliminary multi-disciplinary design processes. Since 2002, he is the Director of the AVD Laboratory at The University of Texas at Arlington. Professor Chudoba focuses on the development of the cutting edge 21st Century Future Project Office aerospace vehicle design & strategic planning/forecasting capability and AVDS software, efforts supported by NASA, Boeing, AFRL, AFOSR and others.

 

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