NASA Funds Breakthrough Nuclear Rocket

A breakthrough pulsed plasma rocket is getting NASA phase 2 innovative concepts funding. It will have 15 times the efficiency of chemical rockets and with high levels of thrust at the level of a medium sized chemical rocket.

Howe Industries is currently developing a propulsion system that may generate up to 100,000 Newtons of thrust with a specific impulse (Isp) of 5,000 seconds. Chemical rockets have about 300-400 specific impulse which means less fuel efficiency so that the time an engine can be used before running out of fuel is less.

The SpaceX Merlin chemical rocket engine used on a Falcon 9 has about 340,000 newtons of thrust. A pulsed plasma fission fusion engine will enable spaceships to go ten to thirty times faster than chemical rockets.

The Pulsed Plasma Rocket (PPR) is originally derived from the Pulsed Fission Fusion concept, but is smaller, simpler, and more affordable. The exceptional performance of the PPR, combining high Isp and high thrust, holds the potential to revolutionize space exploration. The system’s high efficiency allows for manned missions to Mars to be completed within a mere two months. Alternatively, the PPR enables the transport of much heavier spacecraft that are equipped with shielding against Galactic Cosmic Rays, thereby reducing crew exposure to negligible levels. The system can also be used for other far range missions, such as those to the Asteroid Belt or even to the 550 AU location, where the Sun’s gravitational lens focuses can be considered. The PPR enables a whole new era in space exploration.

The NIAC Phase II conceptual studies will receive up to $600,000 to continue working over the next two years to address key remaining technical and budget hurdles and pave their development path forward. When Phase II is complete, these studies could advance to the final NIAC phase, earning additional funding and development consideration toward becoming a future aerospace mission.

The NIAC Phase I study focused on a large, heavily shielded ship to transport humans and cargo to Mars for the development of a Martian base. The main topics included: assessing the neutronics of the system, designing the spacecraft, power system, and necessary subsystems, analyzing the magnetic nozzle capabilities, and determining trajectories and benefits of the PPR. Phase II will build upon these assessments and further the PPR concept.

In Phase II, they plan to:

* Optimize the engine design for reduced mass and higher Isp
* Perform proof-of-concept experiments of major components
* Complete a ship design for shielded human missions to Mars