Accession Number:

AD0392716

Title:

SECONDARY COMBUSTION OF PENTABORANE-HYDRAZINE EXHAUST IN AIR

Descriptive Note:

Final rept. 1 May 1967-30 Apr 1968

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA RESEARCH AND TECHNOLOGY DEPT

Report Date:

1968-06-01

Pagination or Media Count:

125.0

Abstract:

The C characteristic velocity performance of the air-augmentation stage was determined in two flight simulation regimes. In the sea levelMach 2. 5 regime 200 psia chamber pressure800 F air-temperature, the c performance efficiencies were 96-99 of theoretical at air-to-propellant ratios of 81, 161, and 501. Chemical analysis indicated complete combustion of all primary exhaust products, including boron nitride and elemental boron. In the 40,000 ftMach 4.0 regime 50 psia chamber pressure1500 F air-temperature, the c performance was 91-92 of theoretical at air-to-propellant ratios of 81 and 161. Chemical analysis indicated high boron nitride combustion efficiency but very low elemental boron combustion efficiency. Low chamber pressure and low residence time were concluded to be major contributing factors to the low elemental boron combustion efficiency and reduced c performance efficiency. A high water concentration in the secondary chamber, resulting from secondary hydrogen combustion, appears to contribute significantly to the high combustion efficiency of the boron and boron nitride. A model describing the secondary combustion process has been developed. The model reflects the importance of water vapor and high chamber pressure in promoting high combustion efficiency and high performance efficiency of boron-containing propellants.

Subject Categories:

  • Combustion and Ignition
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE