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Rocket-Induced Magnetohydrodynamic Ejector : A Single-Stage-to-Orbit Advanced Propulsion Concept

Author
Cole, John
Published
Sep. 1995.
Physical Description
1 electronic document
Additional Creators
Robertson, Anthony and Campbell, Jonathan
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
During the atmospheric boost phase of a rocket trajectory, magnetohydrodynamic (MHD) principles can be utilized to augment the thrust by several hundred percent without the input of additional energy. The concept is an MHD implementation of a thermodynamic ejector. Some ejector history is described and some test data showing the impressive thrust augmentation capabilities of thermodynamic ejectors are provided. A momentum and energy balance is used to derive the equations to predict the MHD ejector performance. Results of these equations are compared with the test data and then applied to a specific performance example. The rocket-induced MHD ejector (RIME) engine is described and a status of the technology and availability of the engine components is provided. A top level vehicle sizing analysis is performed by scaling existing MHD designs to the required flight vehicle levels. The vehicle can achieve orbit using conservative technology. Modest improvements are suggested using recently developed technologies, such as superconducting magnets, which can improve predicted performance well beyond those expected for current single-stage-to-orbit (SSTO) designs.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19960021025.
Accession ID: 96N24517.
NAS 1.15:111435.
NASA-TM-111435.
AIAA Paper 95-4079.
AIAA 1995 Space Programs and Technologies Conference; 26-28 Sep. 1995; Huntsville, AL; United States.
Terms of Use and Reproduction
Copyright, Distribution under U.S. Government purpose rights.
View MARC record | catkey: 15650941