Test device using a mandrel with a collapsible linkage assembly enables a fluid flow sensor to be properly positioned in a restricted passage by external manipulation. This device is applicable to the combustion chamber of a rocket motor

Fitzgerald, J. J.

Oberschmidt, M.

Rosenbaum, B. J.

English

NASA Technical Reports Server

Oxidizer 
April 1967	 Brief 67-10074 
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. 
Flow-Test Device Fits Into Restricted Access Passages 
The problem: 
To design a test device that will enable a fluid flow 
sensor to be properly positioned with respect to fluid 
(propellant and oxidizer) injector orifices, or ports, 
located at the end of a restricted passage in the com-
bustion chamber of a rocket motor. 
The solution: 
A device incorporating a mandrel with a collapsi-
ble linkage assembly which can be inserted through a 
restricted passage (combustion chamber throat) and 
externally manipulated to position a fluid flow sensor 
(e.g., resistance thermometer) in proper relation to 
the flow port to be checked. 
How it's done: 
The collapsible linkage assembly, at the forward 
end of the hollow mandrel, carries three expandable 
support fingers which are uniformly spaced about the 
periphery of the mandrel. One of these fingers carries 
the flow sensor; the other fingers serve as support and
positioning means. The mandrel, which is threaded to 
the inner circumference of the sleeve, can be rotated 
(by holding the sleeve knob with one hand and rotat-
ing the mandrel knob with the other hand) to expand 
the linkage after it has been inserted through the 
throat of the motor to position the sensor over one of 
the flow ports. Once the flow in a particular port has 
been checked, the entire device can be rotated to align 
the sensor with each of the other ports in sequence. 
To remove the device, the mandrel is rotated in the 
opposite direction with respect to the sleeve to col-
lapse the linkage, and the device is easily withdrawn 
through the throat. 
Note: 
Inquiries concerning this invention may be di-
rected to:
Technology Utilization Officer 
Manned Spacecraft Center 
Houston, Texas 77058 
Reference: B67-10074
cuB! inued uierIc.uI 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
https://ntrs.nasa.gov/search.jsp?R=19670000074 2020-03-11T20:44:38+00:00Z
Patent status: 
Inquiries about obtaining rights for the commercial 
use of this invention may be made to NASA, Code 
GP, Washington, D.C. 20546. 
Source: B. J. Rosenbaum,
M. Oberschmidt,
and J. J. Fitzgerald
(MSC-1078) 
Brief 67-10074	 Category 01


Flow-test device fits into restricted access passages

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