DUMBO Nucelar Rcoket
File Description
Investigation Of A Tricarbide Grooved Ring Fuel Element For A Nuclear Thermal Rocket Brian Taylor’s 2017 paper on Grooved Ring Element Nuclear Rockets.

Forward

Propulsion systems that derive their power from nuclear reactions have been conceptualized for many decades. Serious efforts to develop this technology were made in both the United States and the Soviet Union. The most well known program was that of the Nuclear Engine for Rocket Vehicle Application (NERVA) that was a joint effort of the U.S. Atomic Energy Commission and NASA. Several engines were built and tested under this program in order to develop this technology for a manned mission to Mars.

Presentation Slides Brian Taylor’s Presentation Slides from the July 11th, 2017 presentation.
Metal Dumbo Rocket Reactor The 1957 technical paper by B. W. Knight Jr., B. B. Mclnteer, R. M. Potter, and E. S. Robinson on the design work for the Dumbo Nuclear rocket engine.

Introduction

It has been obvious for many years that, because of the great energy release in nuclear reactions as compared with chemical reactions, nuclear power has potential advantages in rocket propulsion. Many proposals for nuclear powered rockets have been made. A complete bibliography and of historical background has been prepared by R.W,Bussard of LASL.

Dumbo Pachydermal Rocket Motor Bill Kirk’s 1955 summary of the Dumbo work.

Since ROVER/NERVA technology has been ably the intention of this workshop was to cast a rather wide net, I thought it might be useful to tell you a little bit about a lesser known chapter of nuclear rocket history for a couple of reasons. First, perhaps we might learn something from that history, and second, under certain circumstances it might provide an alternative that would be useful in helping to develop a higher performance nuclear rocket engine.

Nuclear Rockets April 26, 1955 paper by H.F. York and A.T. Biehl.

ABSTRACT

A systems analysis is made of a class of nuclear-propelled rockets in combination with chemical boosters. Various missions are considered including the delivery of 5000-1b payload 5500 nautical miles, the placement of a satellite in an orbit about the earth and the delivery of a payload to escape velocity.
The reactors considered are of the heterogeneous type utilizing graphite fuel elements ni a matrix of Be or hydrogenous moderator.
Liquid hydrogen and ammonia are considered as propellants. Graphical results are presented which show the characteristics and performance of the nuclear rockets as the design parameters are varied.
It should be emphasized that this report is not in any sense intended as a handbook of rocket parameters; it is intended only as a guide for determining areas of interest.
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