DESIGN, DEVELOPMENT, AND TESTING OF A LIQUID HYDROGEN SHUTOFF VALVE
Abstract
Research concerns the development of a liquid hydrogen shutoff valve for use in a rocket propulsion system of a missile or space vehicle. A study was made of the physical properties of liquid hydrogen and the properties of materials at liquid hydrogen temperatures. The prime design objectives for this component were reliability of operation, minimum weight, and low leakage. The validity of the valve concept as a liquid hydrogen shutoff device was well established by development testing of the elements of the final unit. The program has resulted in a valve design with essentially zero leakage at the specified operating temperatures. The valve seat configuration that produced this result was a spherically lapped metal poppet and seat with relatively high unit seat loading. Satisfactory operation of a hydraulically formed bellows for use as a high pressure actuator was demonstrated. Development testing of components was accomplished with liquid hydrogen. Relatively simple and economical test equipment was used. This was adequate for conducting small scale tests with liquid hydrogen. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1960
- Accession Number
- AD0259087
Entities
People
- P.r. Hughes
- R.l. Baisley