Nuclear Electric Propulsion vs. Nuclear Thermal Propulsion: An In-Depth Comparative Analysis for Nuclear-Powered Spacecraft

• Nuclear Electric Propulsion (NEP) presents a paradigm shift in space travel, enabling efficient and extended missions beyond Earth's orbit, namely Titans Space's Selene Mission, and the Crewed Mars Mission: 2032.
• This White Paper, a follow-up to a previous paper on Titans Space's NEPTUNE (Nuclear Electric Propulsion - Thrust Utilizing Nuclear Energy) project, concerns NEP technology and highlights its superiority for spacecraft that will be used for crewed missions to Mars.
• Key advantages of NEP over Nuclear Thermal Propulsion (NTP) include eliminating the need for refueling during a crewed Mars return mission and avoiding the necessity for cryogenic propellant storage. This also removes the requirement for a complex cooling system.

By Neal S. Lachman, CEO & Chief of Spacecraft Design, Titans Space, and Franklin Ratliff, CTO, Titans Space

Table of Contents

Executive Summary

1. Introduction

1.1 Limitations of Chemical Propulsion

1.2 Introduction to Nuclear Thermal Propulsion (NTP)

1.3 Objective of this Paper

2. History: Ernst Stuhlinger's NEP Mars Spaceship Concept

2.1. Concept and Design Strategy

2.2. Technical Details and Rationale

3. Overview of Nuclear Electric Propulsion (NEP)

3.1 Working Principle of NEP

3.2 Components of an NEP System

3.2.1 Nuclear Reactor

3.2.2 Power Conversion System

3.2.3 Electric Thrusters

3.2.4 Heat Management System

4. Benefits of NEP

4.1 No Need for Refueling

4.2 Extended Mission Durations

4.3 Higher Specific Impulse

4.4 Flexibility in Mission Planning

4.5 Reduced Operational Costs

4.6 Environmental Considerations

4.7 Scientific Applications

5. Challenges of Nuclear Thermal Propulsion (NTP)

5.1 Refueling Requirement

5.2 Logistical Complexities

5.3 Shorter Mission Durations

5.4 Environmental Impact

5.5 Proliferation Risks

6. Comparative Analysis: NEP vs. NTP

6.1 Table Summary of Key Differences

6.2 Scalability of NEP Systems

7. Technological and Operational Considerations for NEP

7.1 Propulsion System Integration

7.2 Propellant Selection

7.3 Radiation Shielding and Safety Protocols

7.4 International Collaboration

8. Research Requirements for NTP and NEP

8.1. NTP Research

8.2. NEP Research

8.3 Benefits of NEP Research Approach

9. Future Prospects and Research Directions

9.1 Advanced Reactor Designs

9.2 Development of New Electric Thrusters

9.3 Potential Applications of NEP Beyond Deep Space Exploration

10. Conclusion 

Executive Summary

Titans Space's upcoming long-duration space missions demand efficient and powerful propulsion systems for exploration endeavors. While traditional chemical propulsion has served as the workhorse for decades, its limitations are evident. Nuclear propulsion technologies offer a significant leap forward in terms of thrust and mission capability.

This white paper offers a comparative analysis of Nuclear Electric Propulsion (NEP) and Nuclear Thermal Propulsion (NTP) technologies, highlighting NEP's advantages for future space missions.

The main reason why the space industry is focusing on NTP is the belief that refueling and/or in-situ (on-site on a celestial body like the Moon or Mars) will be a possibility. 

While In-Situ Resource Utilization (ISRU) holds promise for the future (potentially by the mid-2030s), both large-scale refueling and propellant production on-site still face significant challenges. This makes chemically propelled and NTP spacecraft less feasible in the near term. 

NEP's ability to operate without refueling enables extended mission durations and offers greater flexibility, making it the most reliable choice for crewed Mars missions. As our research and development in NEP technology continue to advance, it presents a transformative potential for the colonization of Mars. 

1. Introduction

1.1 Limitations of Chemical Propulsion 

Chemical propulsion systems, the mainstay of space travel for decades, rely on the combustion of propellants onboard the spacecraft. While offering high thrust for launch and initial maneuvers, they suffer from limitations in terms of specific impulse (efficiency) and propellant capacity. This translates to shorter mission durations and the need for massive amounts of propellant for deep space exploration. 

1.2 Introduction to Nuclear Thermal Propulsion

Nuclear Thermal Propulsion (NTP) technology uses a nuclear reactor to generate heat. This heat is transferred directly to a liquid propellant, such as hydrogen, which then undergoes a phase change into a gas. As the hydrogen gas heats up and expands, it is expelled at high velocity through a rocket nozzle, producing thrust.

Advantages:

• Higher specific impulse than chemical rockets: NTP thrust is comparable to chemical rocket thrust, but it offers twice the specific impulse, making it more efficient. Additionally, NTP eliminates the need for an oxidizer like liquid oxygen (LOX), simplifying the propulsion system and reducing the overall mass of the rocket.
• Higher thrust than NEP: NTP provides significantly higher thrust compared to NEP.

Challenges:

• Refueling Requirements:

Propellant Needs: NTP spacecraft require substantial amounts of propellant for extended missions. Given current limitations in storage and resupply capabilities, this necessity poses a significant logistical challenge. The need to carry or refuel propellant restricts mission duration and complicates mission planning.

Logistical Complexity: Ensuring a steady supply of propellant adds layers of complexity to mission logistics, including the design of storage solutions and the planning of refueling missions. This increases both the cost and risk associated with NTP missions.

• Shorter Mission Durations:

Limited Propellant Capacity: The capacity to carry propellant is inherently limited, leading to shorter mission durations. This constraint means that NTP, while capable of providing high thrust, is unsuitable for long-duration missions compared to Nuclear Electric Propulsion.

Impact on Mission Scope: The need for refueling or the inability to carry sufficient propellant limits the scope and flexibility of NTP missions. This can affect the mission's objectives and overall success.

While NTP technology offers the advantage of higher thrust than NEP, making it beneficial for certain types of space missions, it faces significant challenges related to propellant requirements and mission duration. The need for large quantities of propellant and the logistical complexities of refueling limit the practicality of NTP for extended missions.

1.3 Objective of this Paper 

This paper focuses on the advantages of NEP and how it overcomes some of the limitations inherent in NTP technology. By examining the working principles, benefits, and current challenges of NEP, we demonstrate its role as a transformative technology for future space applications. 

2. History: Ernst Stuhlinger's NEP Mars Spaceship Concept

Ernst Stuhlinger was among the 126 scientists who emigrated to the U.S. with Wernher von Braun after WWII as part of Operation Paperclip. He was known as the nr. 3 man on von Braun's famed rocket team. Stuhlinger served as the director of the Advanced Research Projects Division at the Army Ballistic Missile Agency (ABMA).

In 1960, ABMA's major portion became NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama. Stuhlinger directed the MSFC Space Science Laboratory from 1960 to 1968 and was MSFC's associate director for science until 1975. He played key roles in lunar exploration planning, the Apollo Telescope Mount, the High Energy Astronomical Observatories, and the early phases of the Hubble Space Telescope.

In the 1950s, Stuhlinger introduced his groundbreaking concept for a crewed mission to Mars. Stuhlinger's design, often referred to as the "Umbrella," "Atomic Umbrella," and "Giant Butterfly," due to its distinctive radiator configuration, revolutionized the idea of interplanetary travel by proposing NEP technology for long-duration missions. 

2.1. Concept and Design Strategy 

Stuhlinger's nuclear-powered spacecraft, initially proposed in the 1950s, marked a radical departure from traditional chemical propulsion systems. His design philosophy was driven by several key considerations:

• Overcoming the Tyranny of the Tsiolkovsky Rocket Equation: The Tsiolkovsky rocket equation dictates the relationship between a rocket's final velocity, its propellant mass fraction (propellant mass divided by total mass), and exhaust velocity. For chemical rockets, achieving the delta-v (change in velocity) necessary for interplanetary travel necessitates an enormous amount of propellant, making missions impractical. Stuhlinger envisioned NEP as a solution. By utilizing a nuclear reactor to generate electricity for powering electric thrusters, NEP offered continuous, low-thrust propulsion with significantly higher specific impulse (efficiency) compared to chemical rockets. This translated to achieving the required delta-v with a much smaller propellant mass, making a manned Mars mission more feasible.
• Extended Mission Durations for Crewed Mars Exploration: A manned mission to Mars necessitates a long journey, with months spent in transit. The continuous, low-level power generation capability of NEP, eliminating the need for massive amounts of propellant that require refueling, made it ideal for sustaining a crew on such a voyage. Additionally, NEP allows for course corrections and maneuvers during the transit, offering greater mission flexibility compared to a ballistic trajectory dictated by chemical rockets.
• Efficient Use of Propellant: Stuhlinger's design focused on maximizing propellant efficiency. NEP's high specific impulse allows for achieving the necessary delta-v for Mars travel with a much smaller propellant mass compared to chemical rockets. This not only simplifies launch requirements but also reduces the overall spacecraft mass, allowing for a larger payload capacity for essential supplies and habitat modules for the crew.

2.2. Technical Details and Rationale 

Stuhlinger's spaceship design possessed several distinctive features, each playing a crucial role in achieving the goals as mentioned above:

• Nuclear Reactor: At the heart of the spacecraft sits a nuclear reactor, likely a fission reactor, generating the thermal energy needed for electricity production. The specific design of the reactor remains unclear, but it was envisioned to be highly efficient, reliable, and compact for space travel. Stuhlinger may have considered concepts like the Kiwi nuclear thermal rocket project, which explored compact and lightweight reactor designs for space applications.
• Electric Thrusters: The spaceship concept relied on electric thrusters, most likely ion thrusters, to convert the electrical power from the reactor into continuous, low-thrust propulsion. Ion thrusters accelerate propellant ions (charged atoms) to high speeds, resulting in high specific impulse but lower overall thrust compared to chemical engines. However, for a long-duration Mars mission, continuous low thrust was more advantageous than the short bursts of high thrust offered by chemical engines. Stuhlinger may have envisioned advancements in thruster technology beyond those available in the 1950s, considering concepts with higher thrust-to-power ratios for faster mission times.
• Radiative Cooling System: One of the most striking features of the design was the large umbrella- and later butterfly-shaped radiator system. This radiator played a critical role in dissipating the excess heat generated by the nuclear reactor. The vast surface area of the "umbrella" maximized heat transfer into space, ensuring efficient operation of the reactor and preventing overheating of the spacecraft systems. The primary function of the radiators was to act as condensers, converting the silicon oil steam back into liquid silicon oil. This process allows the reactor to reheat the liquid and turn it back into steam, maintaining the cycle. Stuhlinger may have considered lightweight and deployable radiator concepts to minimize the launch mass of the spacecraft.
• Modular Design: Stuhlinger envisioned a modular design for the spacecraft. This modularity offered several advantages, including offering flexibility for future mission configurations and the potential reusability of certain components, such as the propulsion module, for multiple missions.

Stuhlinger's design remains a landmark in the history of spacecraft concepts. It served as a significant inspiration for future NEP research and development. The concept highlighted the potential of NEP for sustained interplanetary travel and efficient use of propellant. Stuhlinger's visionary design continues to influence contemporary NEP research, including Titans Space, and serves as a reminder of the crucial role innovative concepts play in shaping the future of space exploration. 

3. Overview of Nuclear Electric Propulsion

3.1 Working Principle of NEP 

NEP systems utilize a nuclear reactor to generate electricity. This electricity then powers electric thrusters, which create thrust by accelerating propellant to high speeds using electromagnetic fields. Unlike NTP, NEP does not directly use the heat from the reactor for propulsion. This allows for more efficient use of propellant and continuous, low-thrust operation ideal for extended missions. 

3.2 Components of an NEP System 

• Nuclear Reactor: The heart of the NEP system, the reactor generates heat through nuclear fission. This heat is then used to produce electricity. Advanced reactor designs aim for high efficiency, long operational lifetimes, and robust safety features.
• Power Conversion System: Converts the heat generated by the reactor into usable electrical power for the electric thrusters and other spacecraft systems. This conversion process typically utilizes a Brayton cycle, similar to a gas turbine engine on Earth. In an NEP system, a working fluid (often helium or a mixture of helium and xenon) is heated by the reactor core. This hot, high-pressure gas expands through a turbine, which extracts energy to spin a shaft connected to an alternator. The alternator then converts the rotational energy into the direct current (DC) electricity needed to power the electric thrusters and other critical spacecraft systems. Waste heat from the cycle is ultimately rejected to space through a radiator system.
• Electric Thrusters: These are the workhorses of the NEP system, converting electrical energy into thrust. Common types include:

- Ion Thrusters: Use electric fields to accelerate ions (charged atoms) of propellant to very high speeds, resulting in high specific impulse but lower thrust.

- Hall-Effect Thrusters: Employ electromagnetic fields to create a region where propellant ions are accelerated, offering a balance between thrust and specific impulse.

- Heat Management System: The nuclear reactor generates significant heat that needs to be efficiently dissipated to prevent damage to the spacecraft. This system may involve radiators and heat exchangers to transfer heat away from the reactor core. In his system, Stuhlinger specified silicon oil as the working fluid to be heated by the reactor.

4. Benefits of NEP 

4.1 No Need for Refueling 

One of the most significant advantages of NEP is its ability to operate without refueling. The nuclear reactor provides a continuous source of electricity, allowing the spacecraft to function for extended periods with minimal propellant. This is particularly crucial for missions to distant destinations where refueling is not currently feasible. 

4.2 Extended Mission Durations 

Unlike NTP, which is limited by the amount of propellant it can carry, NEP systems can support much longer missions. The continuous power supply from the nuclear reactor enables NEP-powered spacecraft to undertake ambitious exploration missions, including journeys to the outer planets and beyond. 

4.3 Higher Specific Impulse 

Specific impulse (Isp) is a measure of how efficiently a propulsion system uses propellant. NEP systems boast a significantly higher Isp compared to traditional chemical or even NTP systems. This translates to needing less propellant to achieve the same delta-v (change in velocity) required for maneuvers and mission objectives. 

4.4 Flexibility in Mission Planning 

The continuous power generation capability of NEP systems provides considerable flexibility in mission planning and execution. Spacecraft can alter trajectories, extend mission durations, or even change destinations without the constraint of limited propellant. This adaptability is particularly valuable for exploratory missions where unforeseen opportunities or challenges may arise. 

4.5 Reduced Operational Costs 

Eliminating the need for propellant storage (and cooling), transportation, and potential refueling missions translates to significant cost savings for NEP missions. Additionally, the reusability of the nuclear reactor (after proper decommissioning) has the potential to further reduce operational costs over multiple missions. 

4.6 Environmental Considerations 

While both NEP and NTP utilize nuclear technology, NEP offers a potential environmental advantage. Chemical propulsion systems often use toxic propellants, posing environmental risks during launch and potential accidents. NEP, on the other hand, can utilize inert propellants like xenon, minimizing environmental impact. 

4.7 Scientific Applications 

The continuous, low-thrust nature of NEP propulsion makes it ideal for scientific missions requiring precise maneuvers or station keeping at specific locations. This capability can be invaluable for studying celestial bodies in detail or deploying scientific instruments in precise orbits. 

5. Challenges of Nuclear Thermal Propulsion 

5.1 Refueling Requirement 

As mentioned earlier, NTP relies on carrying a substantial amount of propellant or developing In-Situ Resource Utilization (ISRU) capabilities to produce propellant at the destination. With current limitations in ISRU technology, early missions using NTP face significant challenges in ensuring propellant availability for the return journey. 

5.2 Logistical Complexities 

The need for refueling adds significant complexity to mission logistics. Planning for propellant storage, transfer, and management in space increases the risk and cost of missions. Additionally, the infrastructure required for these operations (e.g., propellant depots) adds to the overall mission complexity. 

5.3 Shorter Mission Durations 

NTP systems are generally limited by the amount of propellant they can carry. This limitation results in shorter mission durations compared to NEP, restricting the potential for long-term exploration and scientific research on distant celestial bodies. 

5.4 Environmental Impact 

While the environmental impact of NEP is generally considered lower than chemical propulsion, concerns exist regarding potential radioactive releases in case of accidents. Robust safety protocols and mission planning are crucial to mitigate these risks. 

5.5 Proliferation Risks 

The use of fissile materials in NTP technology raises concerns about potential proliferation risks. International cooperation and stringent safeguards are essential to ensure peaceful applications of this technology. 

6. Comparative Analysis: NEP vs. NTP 

• Key advantages of NEP over NTP also include eliminating the need for refueling during a crewed Mars return mission and avoiding the necessity for cryogenic propellant storage. This also removes the requirement for a complex cooling system.

6.2 Scalability of NEP Systems

One of the promising aspects of NEP technology is its potential for scalability. Unlike NTP, which faces challenges in scaling up thrust due to limitations in propellant heating, NEP systems can be theoretically designed to accommodate larger spacecraft and missions. By increasing the reactor power and the number of electric thrusters, NEP can potentially propel heavier payloads on deep space exploration endeavors. 

7. Technological and Operational Considerations for NEP

7.1 Propulsion System Integration 

Integrating the various components of an NEP system – the nuclear reactor, power conversion system, and electric thrusters – presents a significant technological challenge. Ensuring optimal performance, efficiency, and compatibility between these components requires advanced engineering and ongoing research. 

7.2 Propellant Selection 

The choice of propellant for NEP systems is crucial. Ideally, the propellant should be:

• Inert: To minimize environmental impact and avoid potential contamination of spacecraft systems.
• High Specific Impulse: To maximize efficiency and minimize propellant requirements.
• Readily Available: For ease of storage and potential resupply in the future.

Common propellants used in NEP concepts include inert gases like xenon, which offer a good balance of these desired characteristics. While cesium was Stuhlinger's preferred choice for propellant, we will research argon and even iodine as potential candidates.

7.3 Radiation Shielding and Safety Protocols 

As with any nuclear technology, radiation shielding is paramount for NEP systems. The crew and spacecraft electronics need robust protection from radiation emitted by the reactor. Developing advanced shielding materials and implementing stringent safety protocols are critical aspects of NEP development. 

7.4 International Collaboration 

The advancement and deployment of NEP technology can benefit significantly from international collaboration. Sharing expertise, resources, and best practices can accelerate research and development efforts. Additionally, international cooperation can help address concerns regarding proliferation risks associated with nuclear propulsion technologies. 

8. Research Requirements for NTP and NEP

The key distinction between NTP and NEP research lies in the necessity of a nuclear reactor. NEP research benefits from a more straightforward, cost-effective, and safer initial research phase, allowing for progressive development and testing of individual components before integrating them into a complete system.

8.1. NTP Research

Nuclear Thermal Propulsion (NTP) research necessitates the use of a nuclear reactor. This requirement introduces several complexities: 

1. Regulatory Approvals: Establishing and operating a nuclear reactor involves stringent regulatory approvals and compliance with safety protocols.
2. Infrastructure: Building and maintaining the infrastructure needed for reactor research is resource-intensive and costly.
3. Safety Concerns: Handling and testing nuclear reactors pose significant safety risks, requiring robust safety measures to protect researchers and the environment.

8.2. NEP Research

Nuclear Electric Propulsion (NEP) research does not require an operational nuclear reactor for the initial stages of development. Instead, researchers can focus on components such as:

1. Electric Thrusters: Development and testing of ion or Hall-effect thrusters can be conducted using conventional power sources before integrating with a nuclear reactor.
2. Power Conversion Systems: Research on power conversion from heat to electricity can proceed using simulated heat sources.
3. Thermal Management: Studying heat dissipation and thermal management techniques can be done with electrical heating elements.

8.3 Benefits of NEP Research Approach

1. Reduced Complexity: Without the immediate need for a nuclear reactor, the initial phases of NEP research are less complex and can be conducted in more standard laboratory settings.
2. Cost Efficiency: Avoiding the costs associated with nuclear reactors, such as construction, maintenance, and regulatory compliance, makes NEP research more cost-effective.
3. Safety: Research can proceed with fewer safety concerns and lower risks, focusing on system integration and optimization before introducing nuclear elements.

9. Future Prospects and Research Directions

9.1 Advanced Reactor Designs 

Ongoing research focuses on developing advanced reactor designs for NEP applications. These new designs aim to achieve:

• Higher Efficiency: Extracting more usable energy from nuclear fission reactions, translating to improved performance and longer mission durations.
• Improved Safety Features: Developing inherently safe reactor designs that minimize the risk of accidents and radioactive releases.
• Longer Operational Lifetimes: Extending the lifespan of the reactor core to support extended space missions.

8.2 Development of New Electric Thrusters 

Research is also underway to develop new and improved electric thruster designs. These advancements aim to achieve:

• Higher Thrust-to-Power Ratio: Generating more thrust with the same amount of electrical power, enabling faster missions or maneuvers.
• Greater Efficiency: Optimizing the conversion of electrical energy into thrust for improved propellant utilization.
• Increased Operational Lifespan: Developing electric thrusters with longer operational lifetimes to minimize maintenance requirements during extended missions.

9.3 Potential Applications of NEP Beyond Deep Space Exploration 

NEP technology has several additional applications beyond space transport, including:

• High-orbital Maneuvering: NEP thrusters could be used for efficient station keeping and maneuvering of large spacecraft in high Earth orbit.
• In-Space Habitat Maintenance: NEP systems could provide power and low-thrust propulsion for future space habitats or lunar bases.
• Asteroid Redirection Missions: The high thrust-to-propellant ratio of NEP could be beneficial for missions aiming to deflect potentially hazardous asteroids.

10. Conclusion 

Nuclear Electric Propulsion (NEP) presents a compelling alternative to Nuclear Thermal Propulsion (NTP) for Titans Space's long-duration missions. NEP's ability to operate without refueling enables extended mission durations and offers greater flexibility, making it a transformative technology. As Titans Space continues research and development in NEP technology, and with continued international collaboration, advancements in reactor design, and the development of more efficient electric thrusters will be crucial in realizing the full potential of NEP. With our sustained commitment and innovation, NEP technology will pave the way for a new era of exploration, enabling us to establish a permanent presence beyond Earth.

For inquiries, please contact Marcus Beaufort , Director of Communications and Business Strategy.

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About Titans Space Industries

Titans Space Industries (TSI) is creating a streamlined Earth-to-lunar surface transport infrastructure with spaceplanes, space stations, spaceships, and dedicated lunar vehicles.

Titans Space intends to:

✓ Become the largest LEO and Lunar Space tourism company

✓ Become the largest Real Estate owner in Space and the Moon

✓ Become the largest Lunar commerce and mining company (from 2031 onwards)

TSI, a division of Titans Universe, comprises a vast portfolio of incredible, revolutionary space infrastructure that will allow safe and efficient end-to-end space transportation, including spaceplanes and space stations for space tourism, commercial, and industrial purposes, as well as for research, governments, and military usage.

• TSI, Titans Universe, and associated companies are currently being structured as Delaware, USA, corporations.

Titans Space’s single-stage-to-orbit spaceplanes will facilitate orbital space flights for orbital cruises or going to Low-Earth Orbit, sub-orbital flights for zero-g space tourism flights, as well as ultra-fast point-to-point transportation for humans and cargo.

TSI's space tourism division is building the future of luxury space exploration with spaceplanes, spaceships, space stations, and lunar transport vehicles. TSI’s revolutionary LEO Space Station and Lunar Space Station will redefine humanity’s place amongst the stars, with lunar tourism, scientific research, commercial mining applications, lunar factories, and lunar real estate.

About the Founding Team

TSI was founded by a group of partners with a combined 550 years of business experience, representing investor interests in Titans Universe/TSI. They worked together on numerous projects for a combined 200+ years.

The founding team includes a 28-year-veteran space entrepreneur and satellite broadband pioneer, a PE fund manager who raised more than $6 billion in capital, a 40+ year rocketry and aerodynamics veteran, a 40+ year Space entrepreneur and activist, a Hall-of-Fame NBA basketball legend, a former Head of Business Development at Apple, a multi-billion-dollar business strategist, a former MD of KPMG NYC who advised on 100+ PE and M&A transactions, and the former CFO of a Formula One racing team and public listed companies.

Our Founding CEO, Neal S. Lachman is a serial entrepreneur with 35 years of investment, business, space, technology, and telecom experience. In 1992, he picked up the phone and started communicating with companies like PanAmSat. He has been a space entrepreneur since 1994/1995 when he and two of his brothers applied for and received three international digital satellite broadcast licenses.

For more information

Lunar

www.TitansSpace.com/Selene-Mission

www.TitansSpace.com/Titania-Lunar-Colony

www.TitansSpace.com/Titania-Lunar-Industry-Commerce

www.TitansSpace.com/Titania-Lunar-Resort

www.TitansSpace.com/Lunar-OrbitalPort-Space-Station

www.TitansSpace.com/SpaceShip

www.TitansSpace.com/Lunar-Yacht-Transporter

Other

Titans Space Industries - Executive Summary

www.TitansSpace.com/FAQ

www.TitansSpace.com/About-Titans-Space

www.TitansSpace.com/Titans-Spaceplanes

www.TitansSpace.com/Titans-Engines-Systems

www.TitansSpace.com/Space-Tourism

www.TitansSpace.com/Orbital-Cruise

www.TitansSpace.com/Sub-Orbital-Zero-G

www.TitansSpace.com/Ultra-Fast-Travel

www.TitansU.com/Founding-Team