Accession Number:

AD0875081

Title:

Long-Term Storability of Propellant Tankage and Components

Descriptive Note:

Interim rept. no. 1, Mar 1969-Feb 1970

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDSAFB CA

Personal Author(s):

Report Date:

1970-05-01

Pagination or Media Count:

213.0

Abstract:

A program was initiated to investigate the storability of liquid system components and tankage under extreme conditions of relative humidity and temperature. A variety of system components and tankage materials are being evaluated for long-term storability with storable liquid rocket fuels and oxidizers. Storage conditions are 85 degrees F temperature and 85 relative humidity for oxidizer systems and 70 to 150 degrees F temperature for fuel systems. The propellants under test are N204, ClF5, and MHF-5. Tankage materials under test are various alloys of aluminum, steel and titanium. The results of almost 3 years of testing on a representative number of tankage materials have indicated that leakage of propellant can occur as a result of improper weld joint design, inadequate quality control in fabrication and inadequate acceptance leakage testing. Factors which can contribute to the development of oxidizer leakage are a high ambient relative humidity greater than 30 and stress corrosion cracking susceptibility of the tank material in combination with the propellant and trace quantities of foreign compoundselements in the propellant.

Subject Categories:

  • Surface-Launched Guided Missiles
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE