Computer program predicts performance of fluorine-hydrogen main tank injection pressurization system for full range of liquid-hydrogen-fueled space vehicles. Analytical model includes provisions for heat transfer, injectant jet penetration, and ullage gas mixing. Analysis predicts GF2 usage, ullage gas and tank wall temperatures, and LH2 evaporation

Cady, E. C.

Kendle, D. W.

English

NASA Technical Reports Server

December 1972 B72-10069 
NASA TECH BRIEF 
Lewis 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 subscription 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. 
Main Tank Injection Pressurization Program 
.
The problem: 
For cryogenic vehicles, particularly those that require 
multi-burn operations, the tank pressurization system 
can contribute significantly to the weight, complexity, 
and cost of the propulsion feed system. 
The solution: 
A computer program has been developed that pre-
dicts the performance of a fluorine-hydrogen Main Tank 
Injection (MTI) pressurization system for the full range 
of liquid-hydrogen-fueled space vehicles. MTI is a tech-
nique in which a hypergolic reactant is injected into a 
full-scale propellant tank, and the resultant heat release 
pressurizes the tank. 
How it's done: 
The analytical model includes provisions for heat 
transfer, injectant jet penetration, and ullage gas mixing. 
A large scale M-TI control system was designed, fabri-
cated, and tested in a flight-weight LH 2
 tank. Seventeen 
tests were performed at various ullage volumes with both 
straight-pipe and diffuser-type injectors, and at varied 
LH2 and GF2
 injection flow-rates. Pre-pressurization, 
constant-pressure hold, and LH 2
 expulsion at controlled 
tank pressures were demonstrated. The analysis accu-
rately predicted GF2
 usage, ullage gas and tank wall 
temperatures, and LH 2
 quantities evaporated. The analy-
sis was used to predict the performance of an MTI pres-
sure control system for a Centaur vehicle configuration 
and mission specified by NASA. The study reveals that 
MTI can be effectively applied to a space vehicle and 
that substantial pressurization system performance bene-
fits could be realized. 
Notes: 
1. This program was written in FORTRAN IV for use 
on the IBM-7094 computer. 
2. Inquiries concerning this program should be directed 
to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: LEW-1 1368 
Patent status: 
No patent action is contemplated by NASA. 
Source: E. C. Cady and D. W. Kendle of

McDonnell Douglas Corporation

under contract to

Lewis Research Center

(LEW-1 1368) 
Category 09 
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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Main tank injection pressurization program

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