Project Title:

Metalized-Cryogen for Advanced Hybrid Engines

92-1-11.06-1992B                                                    NASW-4789
Metalized-Cryogen for Advanced Hybrid Engines
Orbital Technologies Corporation
402 Gammon Place, Suite 10
Madison, WI  53719
Eric E. Rice                                         (608-833-1992)

Abstract:

     An innovative, metalized, hybrid solid rocket motor will be
developed. While many approaches to solid propellant delivery to a
combustion chamber have been investigated, in general, these
devices are complex, heavy, and expensive. This project will
couple two areas of propellant enhancement: propellant
metalization and cryogen solidification. Because the performance
enhancement capability of metalized propellants has received much
study since the 1960s, the system simplifications associated with
solid cryogens are both promising and attractive. Phase I will
demonstrate the basic metalized-cryogen solidification process.
Phase II will build and fire a small motor in the 100-200 lb
thrust range.

Potential Commercial Application:

Potential Commercial Applications:  The hybrid engine may be
adaptable to thrust ranges from 20 lb to 20,000 lb or higher and
may operate at chamber pressures of 200 to 400 psia. Smaller sizes
may operate as pulse thrusters for attitude and velocity trim.
Larger sizes would be suited to upper-stage applications and space
tug uses. The engine's major strengths are its simplicity, long-
term space storage, and low-cost reliability without complex
metalized propellant delivery systems.

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