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

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)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1960
Accession Number
AD0259086

Entities

People

  • A.e. Neal
  • R.h. Warren

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Liquid Hydrogen
  • Materials
  • Physical Properties
  • Propellant Tanks
  • Propellants
  • Propulsion Systems
  • Reliability
  • Relief Valves
  • Rocket Propulsion
  • Spacecraft
  • Steady State
  • Tank Vents
  • Valves
  • Vents

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Software Engineering
  • Thermal Physics or Thermal Science.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster