Accession Number:

AD0384281

Title:

OZONE FEASIBILITY STUDY.

Descriptive Note:

Final rept. 1 Dec 65-31 Mar 67,

Corporate Author:

AIR REDUCTION CO INC MURRAY HILL N J RESEARCH AND ENGINEERING DEPT

Report Date:

1967-09-01

Pagination or Media Count:

150.0

Abstract:

The goal of the work done under these contracts was to determine the feasibility of using ozone as a propellant for a rocket motor system. The first phase of the work was the determination of the quantity of solubilizer required to completely solubilize O3-O2 solutions and to establish adiabatic U-tube shock values and critical diameters for the homogeneous solutions. These data were then used to determine the maximum concentration of ozone which could be safely handled in flow tests. The calculations are presented for various rocket motor and flow parameters used in the design of these tests. Flow and burner studies have been successfully completed using a solubilized ozone solution in a simulated rocket motor system. It was concluded that an ozone, oxygen and fluorine solution containing about 30 weight percent ozone and at least 14 fluorine, when handled under carefully controlled conditions, is a feasible rocket-propellant oxidizer. Author

Subject Categories:

  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE