Exploratory Research on High Energy Propellant Systems

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.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1961
Accession Number
AD0270941

Entities

People

  • A.v. Grosse
  • T.r. Flint

Organizations

  • Temple University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boiling Point
  • Chemistry
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Decomposition
  • Heat Energy
  • Hypergolic Ignition
  • Ignition
  • Liquid Oxygen
  • Materials Laboratories
  • Materials Science
  • Measurement
  • Partial Pressure
  • Propellants
  • Rocket Engines
  • Rocket Propellants

Fields of Study

  • Physics

Readers

  • Organic Chemistry
  • Rocket Propulsion.