Cryogenic pressure transducer utilizes a diaphragm which is electron beam welded to a fitting. This assembly is then heliarc welded to the main body of the transducer. The transducer requires no damping oil and thus is capable of operating at both cryogenic and high temperatures

Hendrix, J. M.

English

NASA Technical Reports Server

Heliarc Weld 
Element Assembh 
Wiper Assembly 
Flex Pivots 
Heliarc Weld 
First Stage Strut —
Diaphragm
Stage Strut 
Bracket 
hlining 
Beam Weld 
Weld 
The transducer described in this Tech Brief utilizes 
a diaphragm which is electron beam-welded to a fit-
ting. This assembly is then heliarc welded to the main 
body of the transducer. The diaphragm pressure de-
November 1969	 Brief 69-10601 
•	 NASA TECH BRIEF• 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Cryogenic Pressure Transducer 
flection, about .003 to .005 inch, is transmitted to a 
first stage amplifier through a strut wire brazed at 
both amplifier and sensor ends. The amplifier multi-
plies sensor travel by a factor of 4.5 to 6 and feeds 
this motion to the wiper assembly through a second 
stage strut wire (see Figure). 
The second amplifier arm further multiplies motion 
to produce .150 inch wiper travel at the potentiometer. 
The transducer requires no damping oil, and thus is 
capable of operating at both cryogenic and high tem-
peratures. The flex pivots provide frictionless bear-
ings, high lateral stiffness, and low torsional stiff-
ness. 
Notes: 
1. The information contained in this Tech Brief may 
be of interest to designers and users of process 
control instrumentation and cryogenic equipment. 
2. No further documentation is available. Technical 
questions may be directed to: 
Technology Utilization Officer 
Manned Space Flight Center 
Huntsville, Alabama 35812 
Reference: B69-10601 
Patent status: 
No patent action is contemplated by NASA. 
Source: J. M. Hendrix of 
Bourns Inc. 
under contract to 
Marshall Space Flight Center 
(MFS- 14909) 
Category 01 
This document was prepared under the sponsorship of the National	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States	 information contained in this document, or warrants that such use 
Government nor any person acting on behalf of the United States	 will be free from privately owned rights.
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Cryogenic pressure transducer

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