Computer program for the analysis of a single propellant tank pressurization system includes many pertinent physical phenomena previously ignored in other mathematical models. This program can be used for analysis, simulation, and design of propellant pressurization systems

Epstein, M.

English

NASA Technical Reports Server

December 1967	 Brief 67-10625 
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. 
Propellant Tank Pressurization Analysis Program 
The problem: 
To produce a mathematical model of a tank pres-
surization system which includes many pertinent phys-
ical phenomena previously ignored in other models. 
The solution: 
A program for the analysis of a single propellant 
tank pressurization system. 
How it's done: 
To predict pressurization performance adequately 
the following phenomena have been considered. 
Propellant Tank 
1. Heat transfer between the gas and the walls, be-
tween the liquid and the walls, between the 
liquid and the gas, between the walls and the 
insulation, and between the insulation and the 
ambient. 
2. Mass transfer within the gas space and at the 
gas—liquid interface. 
3. Circulation within the gas and liquid spaces. 
4. Venting of gas from the propellant tank. 
5. Propellant tanks of circular or annular cross sec-
tion, with radius an arbitrary function of axial 
distance. 
6. Variation of gas density with temperature and 
pressure. 
7. Variation of gas, liquid, wall, and insulation ther-
modynamic and transport properties with tem-
perature and/or pressure. 
Gas Storage Tank 
1. Heat transfer between the gas and the wall and 
between the walls and ambient. 
2. Variation of gas density with temperature and 
pressure. 
3. Variation of gas and wall thermodynamic proper-
ties with temperature and/or pressure. 
Pressure Regulator 
The regulator set (or sense) pressure is a function 
of the regulator position; i.e., the pressure regUlator 
is nonisochrnnoiis
Ambient 
The ambient heat transfer coefficient and tempera-
ture are functions of time and axial position for the 
propellant tank, and are functions of time only for 
the gas storage tank. 
The propellant tank gas and liquid space, including 
walls and insulation are divided into nodes. A differ-
ence technique is used to perform the heat and mass 
transfer calculations which involves computation of 
evaporation or condensation rates, gas space mole 
fraction and temperature distributions. The propellant 
tank pressure and the pressurant temperature and 
flowrate are computed from the propellant tank re-
quirements and the characteristics of the gas storage 
bottle (if any) and heat exchanger (if any), subject 
to limitations imposed by the maximum and minimum 
effective areas of the pressure regulator and the char-
acteristics of the gas lines. 
Notes: 
I. This program is written in Fortran IV and MAP 
for use on the IBM 7094 computer. 
2. This program can be used for analysis, simula-
tion, and design of propellant pressurization sys-
tems. 
3. Inquiries concerning this program may be made 
to:
COSMIC 
Computer Center 
University of Georgia 
Athens, Georgia 30601 
Reference: B67-10625 
Patent status: 
No patent action is contemplated by NASA. 
Source: M. Epstein 
of North American Aviation 
under contract to 
Marshall Space Flight Center 
(M FS- 1506) 
Category 06 
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=19670000624 2020-03-11T21:35:24+00:00Z


Propellant tank pressurization analysis program

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