Nuclear Space Propulsion

In my previous rocket design proposals that included a nuclear reactor, I simply placed a nuclear core in the center and assumed it functioned like a combustion engine—compact and easy to control. However, the engineering reality is more complex. Recently, I developed an energy multiplier that generates immense fission energy through an electrically controlled, self-contained, and compact module. Having a validated power source allows for its integration into a dedicated rocket engine architecture.

I propose utilizing this energy multiplier exclusively for LEO-assembled space rockets. Operating in orbital microgravity, these vehicles do not require the extreme thrust-to-weight ratios necessary to counteract Earth's gravity during launch. Instead, the priority shifts to high specific impulse Iₛₚ and system reliability. Furthermore, because orbital assembly is a time-intensive process, the propellant must remain stable without significant boil-off.

In my previous nuclear designs, I proposed dry ice (solid carbon dioxide) as a monopropellant to be heated by fission energy. Technical analysis indicates that ammonia (NH₃) is a superior alternative for the primary mission phases. When heated above 800°C, ammonia decomposes into nitrogen and hydrogen gases (N₂ + 3H₂). This dissociation converts the liquid propellant into two lightweight gases, dramatically increasing the Iₛₚ.

Furthermore, the Energy Multiplier operates in a "Dual-Mode" capacity. While the primary thermal output drives propulsion, the integrated GaAs solar panels and Peltier modules continue to generate consistent electrical power. This ensures that even during long coasting phases between planets, the rocket has a reliable energy source for life support, deep-space communications, and active magnetic radiation shielding without requiring auxiliary reactors.

These LEO-assembled rockets will utilize multiple stages. The initial stages for Earth-escape maneuvers and the subsequent stages for Trans-X-Injection will utilize ammonia as the monopropellant. Even the descent stages for deploying payloads on celestial surfaces will leverage ammonia's efficiency. Dry ice remains a logical choice for ascent modules, where carbon dioxide harvested from a planet's atmosphere can be utilized for in-situ refueling.