Proportional pulsed pilot valve using conventional efficient solenoid valve for pilot stage provides proportional thrust control for cold gas thrusters with zero leakage of main stage

Rusk, S. J.

English

NASA Technical Reports Server

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- Main Flow
From 
Supply 
- Pilot Flow 
Valve Mount 
and Port 
Module 
Decembec1971	 Brief 71-10468 
S	 NASA TECH BRIEF 
Ames Research Center 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a aubscription basis from the National Technical Information 
Service, Springfield, Virginia 22151. Requests for individual copies or questions relating to the. Tech Brief program may 
be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Proportional Pulsed Pilot Valve 
The problem:	 opposite the solenoid; the solenoid assembly is

To provide proportional thrust control for cold- not exposed to the pressure. The push action of the 
gas thrusters.	
-	 solenoid spindle unseats the pilot plunger and 
The solution:	 allows the pilot flow to enter the command pressure 
A proportional pulsed pilot valve which uses a 	 chamber. The pilot flow causes the pressure in the 
conventional, efficient solenoid valve for the pilot 	 command chamber to rise to a level dictated by the 
stage. Proportional control of the main stage, with 
zero leakage, is accomplished. 
How it's done: 
The valve is mounted in a block containing ap-
propriate input and output orifices. Pressure is 
supplied to the chamber on the right, at the end
solenoid duty cycle, supply pressure, and the size of 
the bleed orifice in the main piston. 
The pressure in the command pressure chamber 
forces the main piston to the right, opening the main 
orifice and permitting the main flow to proceed from 
the pressure source to the output orifice. As the 
(continued overical) 
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 docuñient, 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=19710000465 2020-03-17T02:25:37+00:00Z
main orifice opens and the main flow is established, 
pressure is applied to the main piston face on the 
side opposite the command pressure chamber, 
which tends to reduce the main flow. Thus, a bal-
ance is established between the command pressure 
and the resultant output pressure and flow, and an 
output proportional to input is produced. 
Notes: 
1. A prototype model of the valve has been built 
and tested. 
2. No additional information is available. Specific 
questions, however, may be directed to: 
Technology Utilization Officer 
Ames Research Center 
Moffett Field, California 94035 
Reference: B71-10468
Patent status:. 
No patent action is contemplated by NASA. 
Source: S. J. Rusk of 
Lockheed Missiles & Space Co. 
under contract to 
Ames Research Center 
-	 (ARC-10228) 
Brief 71-10468	 Category 07


Proportional pulsed pilot valve

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