SC17: John Bucknell

SC17: John Bucknell

John R. Bucknell graduated from Cleveland State University in 1995 with a bachelor’s in mechanical engineering and the University of Michigan in 1999 with a master’s in systems engineering.  

He has led advanced engineering teams at Chrysler and General Motors for three production high performance engine families, was Senior Propulsion Engineer for the Raptor full-flow staged combustion methalox rocket at Space Exploration Technologies and is currently the Senior Propulsion Scientist for Divergent3D in Torrance, CA developing additively manufactured vehicle technologies.

Published technical work includes high efficiency/low operational cost internal combustion engines, economic carbon-neutral synthetic fuel processes and high performance air-breathing nuclear rockets as well as ten US patents.

John certainly knows his stuff! Please enjoy his wonderful talk on Nuclear Thermal Turbo Rockets from Starship Congress 2015...

Single Stage to Orbital Habitats Constructed from Lunar Ice Water


Access to space is driven by the economics of launch vehicles.  A previously published rocket propulsion cycle called the Nuclear Thermal Turbo Rocket (NTTR) is able to achieve payload fractions of more than 45% to Low Earth Orbit (LEO).  This rocket is intended to be completely reusable for the launch mission as it is a Single Stage to Orbit (SSTO) vehicle, which improves economics vastly.  However, providing material to LEO is not always the most economical solution for permanent space-based habitation.  In-situ resource utilization (ISRU) has been proposed as a method for avoiding the Earth’s gravity well for space-based construction with solutions proposed using Lunar, Martian as well as other resources.  

One attractive resource is water ice, with uses as both reaction mass for propellant in liquid form and as structure in solid form.  Nuclear Thermal rockets in particular are well-suited to in-space propulsion as they can add enthalpy to a variety of propellants for thrust without requiring processing plants to achieve chemically active reactants, thus saving on mission payload mass.  A mission is proposed that leverages the NTTR vehicle as well as ISRU to construct an orbital habitat of Lunar water ice with a single terrestrial launch (Single Stage to Orbital Habitat – SSTOH).  

This analysis describes an 11m diameter robotic vehicle with a 6,000-megawatt nuclear thermal rocket in a NTTR arrangement.  The SSTOH mission places a 21m minor and 214m major diameter toroidal habitat in space, capable of full terrestrial gravity simulation by spinning at 3 rpm.  The habitat begins as two thin films defining the interior and exterior surfaces of the torus, which is then inflated with lunar-sourced water in a 1m thick shell and allowed to freeze.  

The lunar water ice is extracted from permanently shadowed regolith on the Lunar south pole, where the NTTR vehicle propulsively lands and places 54 tons of payload.  The lunar payload is comprised of a small 30 MWth nuclear reactor and associated mechanisms able to extract sub-surface ice.  

The NTTR vehicle fills its propellant tank with 720 tons of lunar water, and using the water as a propellant delivers 400 tons of water to the habitat in LLO before returning to the Lunar water extraction plant.  The reusable NTTR vehicle makes 100 trips to inflate the 40,000-ton habitat, with approximately one trip per 24 hours.  Subsequently, the lunar water extraction reactor can be transported to the habitat as a power supply and the NTTR vehicle can push the habitat to a Lagrange point.  

In such a fashion, a single vehicle of low investment can produce a 199,000m^3 habitat within 5 months of launch.