Accession Number:

AD0259086

Title:

DESIGN, DEVELOPMENT, AND TESTING OF A LIQUID HYDROGEN TANK VENT AND RELIEF VALVE

Descriptive Note:

Corporate Author:

PARKE THOMPSON ORDNANCE SECTION ATLAS POWDER CO ST LOUIS MO

Personal Author(s):

Report Date:

1960-12-01

Pagination or Media Count:

1.0

Abstract:

A summary is presented of the design and development of a liquid H propellant tank vent and relief valve for use in rocket propulsion systems, missiles, and space vehicles. A study was made of the physical properties of liquid H and the properties of materials at liquid H temperatures. Materials were chosen to ensure the reliability, minimum weight, and low leakage of this component. The validity of the valve concept as a pressure control device was well established A valve was developed with a high degree of steady state accuracy, adequate response characteristics, and consistent crack and reseat characteristics within the specified operating temperature range. An adequate and simple means of thermal compensation of an absolute pressure reference device was developed. Satisfactory operation at -420 F of a valve seat with low seating force and of mylar diaphragms was demonstrated. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE