Fluid state vortex valve secondary injection control system shows considerable promise for future application to solid propellant rocket engine thrust vector control. The single axis injection system tested would be capable of providing secondary injection thrust vector control using 2000 deg F gas

Holt, W. D.

Rivard, J. G.

English

NASA Technical Reports Server

December 1966	 Brief 66-10524 
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. 
Study of Vortex Valve for Medium Temperature Solid Propellants 
The fluid state vortex valve secondary injection con-
trol system shows considerable promise for future 
application to solid propellant rocket engine thrust 
vector control. The single axis injection system tested 
would be capable of providing secondary injection 
thrust vector control using 2000° F gas. 
The following summarizes the program's activities: 
Six hot-gas firings were made. The gas generator 
supplied a flow of 1.0 lb/sec for 30 seconds. This 
system incorporated two vortex valves in parallel, 
functioning together as a flow divider circuit. One of 
the vortex valves utilizes active control, the other 
acting essentially as a pressure regulator maintaining 
the supply pressure constant by effectively bypassing 
flow when the power valve is throttled. This system 
demonstrated a flow modulation capability in excess 
of 4 to 1. The particular system concept selected, 
using active control on only one vortex valve, does 
not produce the desired total system performance. 
A better system approach would be to use active 
control on both vortex valves and operate essentially 
in a push—pull mode. The system dynamic response 
was evaluated with sinusoidal and transient inputs. 
At 30 cps the amplitude attenuation was —4db and 
the phase lag was 28 degrees. The frequency response 
of the basic vortex valve is fast enough so that the 
system dynamics are dominated by the associated 
manifold volume compressibility time constants. 
The control system components and associated 
hardware functioned as desired. The performance of 
the vortex valve did not change during a 30-second 
hot-gas test, indicating insensitivity to thermal expan-
sion. A composite structure of high density graphite
backed with asbestos-phenolic eliminated erosion in 
the supply manifold. 
Cold gas testing of a one-sixth scale model vortex 
valve was conducted to optimize the configuration 
and performance of the vortex power valve and vortex 
regulator valve for the selected system. The normal-
ized performance, with regard to gains and flow 
modulation range, was practically identical for hot-
and cold-gas tests. The two vortex valves required 
complementary characteristics, achieved by variation 
in the vortex valve geometry. This parameter variation 
experience resulted in further insight into the basic 
knowledge of vortex valve technology and control 
system performance. 
The logical extension of this program is to develop 
a fluid state control system using high temperature 
(6000°F) aluminized solid propellant gases. Eventu-
ally, a direct engine bleed, fluid state, secondary in-
jection thrust vector control system should provide a 
lightweight system with inherent simplicity and high 
reliability. 
Note: 
Additional information is contained in: "Research 
Study of the Vortex Valve for Medium-Temperature 
Solid Propellants," by W. P. Holt and J. G. Rivard, 
The Bendix Corporation, August 1965, Report No. 
N66-21695, which may be obtained from: 
Technology Utilization Officer 
Langley Research Center 
Langley Station 
Hampton, Virginia 23365 
Reference: B66-10524
(continued overicaf) 
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.
https://ntrs.nasa.gov/search.jsp?R=19660000522 2020-03-11T17:43:53+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: W. D. Holt and J. G. Rivard 
of The Bendix Corporation 
under contract to
Langley Research Center
(Langley-204)
. 
40' 
Brief 66-10524	 Category 01


Study of vortex valve for medium temperature solid propellants

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