Accession Number:

AD0270941

Title:

Exploratory Research on High Energy Propellant Systems

Descriptive Note:

[Technical Report, Final Report]

Corporate Author:

TEMPLE UNIV PHILADELPHIA PA

Personal Author(s):

Report Date:

1961-01-01

Pagination or Media Count:

72

Abstract:

A versatile liquid propellant evaluation system was perfected which is suitable for use with laboratory quantities 50 to 200 ml of regular or cryogenic fuels and oxidizers. Tests with the RP-1-LOX system provided values for specific impulse on the order of 90 of theoretical. Data from a test of the pentaborane-fluorine system yielded a specific impulse which was 83 of theoretical. A dilute solution 0.05 of O3F2 in liquid O was used as an oxidizer in the apparatus and proved to hypergolic with gaseous H2, UDMH, UDMH-DETA, E OH, C3H8, n-hexane, JP-4, and mixtures of JP-4 and UDMH. Compatibility tests by simple contact showed that dilute O3F2 -LOX solutions do not react hypergolically with most materials commonly used in LOX systems.

Descriptors:

Subject Categories:

  • Liquid Propellant Rocket Engines

Distribution Statement:

[A, Approved For Public Release]