Download - Modeling of Propellant Tank Pressurization
![Page 1: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/1.jpg)
MODELING OF PROPELLANT TANK PRESSURIZATIONBy:Amr hassan ahmed darwish
![Page 2: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/2.jpg)
LAYOUT
![Page 3: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/3.jpg)
SELF PRESSURIZED SYSTEMS The advantages:
•Simple design with low parts count
•Inexpensive vehicle production
•Selectable tank pressures ranging up to 7Mpa
•Very few failure modes leading to superior reliability
![Page 4: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/4.jpg)
INTRODUCTION
![Page 5: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/5.jpg)
What is the major advantage of modeling the Propellant tank pressurization ?
Propellant tank pressurization is an essential element of the prediction of rocket performance. This is the case even more so for hybrid rockets that use a self-pressurizing oxidizer because the thrust produced by the motor is dependent on oxidizer tank pressure.
![Page 6: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/6.jpg)
What is the Objective ?Developing a model of a propellant feed system that can be readily incorporated into a rocket design computer program. The model developed is general and should work well for propellant tanks that are pressure fed with an inert gas and also for self-pressurizing systems.
![Page 7: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/7.jpg)
THE MODELING ANALYSISAssumptions• Open system• Real gas• Two-phase (liquid-vapor) homogenous
Nitrous oxide
• The saturation layer is a thin layer • Regular geometry shape of storage Tank
(cylinder shape)• Frictionless flow in the tank• Tank is in vertical position• No chemical reactions• No mechanical work• Neglect change in potential energy
![Page 8: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/8.jpg)
GOVERNING EQUATIONS
The first law of thermodynamics
![Page 9: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/9.jpg)
FOR LIQUID CONTROL VOLUME
For gas control volume
![Page 10: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/10.jpg)
![Page 11: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/11.jpg)
Evaluation of Thermodynamic Properties
The Soave-Benedict-Webb Rubin Equation of State equation
Peng –Robinson Equation of state (PR EOS)
![Page 12: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/12.jpg)
EVALUATION OF ENTHALPY AND INTERNAL ENERGY
![Page 13: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/13.jpg)
EVALUATING THE RATE OF MASSESThe rate of condensed vapor
The rate of evaporated liquid
The rate of change of gas mass Equation
The mass flow rate through the propellant Feed system
![Page 14: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/14.jpg)
The rate of change of Liquid mass Equation
EVALUATING THE RATE OF MASSES
![Page 15: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/15.jpg)
EVALUATING THE RATE OF VOLUME CHANGE
The rate of change of bulk Liquid volume:-
The rate of change of gas volume
![Page 16: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/16.jpg)
HEAT TRANSFERDuring the period of time when liquid is being expelled from the tank, vaporization takes place at the liquid -vapor mixture interface or possibly within the bulk liquid in the form of boiling
The free convection heat transfer between liquid and liquid surface layer is
![Page 17: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/17.jpg)
THE SOLUTION METHODOLOGY
Initial condition: The capacity of the oxidizer tank is 0.0354 m^3
with Tmperature surround the tank and mass are well known. The injector area is 0.0001219352 m^2 in this model.
Calculate the saturation pressure from the surround temperature and use The Soave-Benedict-Webb Rubin Equation of State to get the density of gas and Liquid then evaluate the mass of liquid and vapor from mass balanced equation .
a) Integrate numerically with time using the modified Euler method 𝑇ሶ𝐿 , 𝑇ሶ𝑇𝐺 , 𝑉ሶ𝑇𝐺 , 𝑉ሶ𝐿 , 𝑚ሶ𝐿 and 𝑚ሶ𝑇𝐺 to obtain 𝑇𝐿, 𝑇𝑇𝐺,𝑃𝑇𝐺 ,𝑉𝑇𝐺, 𝑉𝐿, 𝑚𝑇𝐺, 𝑚𝐿
Assume initially 𝜌𝐿ሶ , 𝑃𝑇𝐺ሶ and 𝜌𝑇𝐺ሶ are all set to be zero.
![Page 18: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/18.jpg)
![Page 19: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/19.jpg)
RESULTS
![Page 20: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/20.jpg)
TEST 1 ,
Comparison of measured and ullage pressure.
![Page 21: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/21.jpg)
TEST 1 ,
Variation temperature time history.
![Page 22: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/22.jpg)
TEST 1 ,
The variation of Propellant mass
![Page 23: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/23.jpg)
TEST 2 , ,
Variation of tank pressure with time
,
![Page 24: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/24.jpg)
TEST 2 , ,
The variation of Propellant mass
![Page 25: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/25.jpg)
TEST 3 , , ,
Variation of tank pressure with time
![Page 26: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/26.jpg)
TEST 3 , , ,
The variation of Propellant mass
![Page 27: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/27.jpg)
TEST 4 , , , ,
Variation of tank pressure with time
![Page 28: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/28.jpg)
TEST 4 , , , ,
The variation of Propellant mass
![Page 29: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/29.jpg)
CONCLUSION •A computer program of a propellant tank pressurization system has been developed.• This model is used to predict the self-pressurizing oxidizer system of a moderate size hybrid rocket.• The model does not assume thermo or phase equilibrium (although the liquid surface is set equal to the saturated vapor temperature) and is applicable to propellants that exhibit real-fluid behavior.• The results obtained are in good agreement with the published and experimental data
![Page 30: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/30.jpg)
REFERENCES•M. Arif Karabeyoglu ," Modeling of Propellant Tank Pressurization",AIAA 2005-3549, 41th AIAA/ASME/ASEE Joint Propulsion Conference, Tucson, Az, July 2005.•V.A. Zakirov, L. Li ," 1-D, Homogenous Liquefied Gas Self –Pressurization Model", Tsinghua University, Beijing, P.R. China, European conference Aerospace sciences (EUCASS).•.Claus K. Zéberg-Mikkelsen," Viscosity Study of Hydrocarbon Fluids at Reservoir Conditions Modeling and Measurements ", Department of Chemical Engineering, June 2001.•Alok Majumdar and Todd Steadman," Numerical Modeling of Pressurization of a Propellant Tank ", Sverdrup Technology, Huntsville, AI.•Don W.Green and Robert H.Perry ,Perry's Chemical Engineers' Handbook, 8thEd, McGraw-Hill , Inc.,New York ,NY,2008.•Rick Newlands," The physics of Nitrous Oxide", aspirespace, 2006.•http://www.tsinghua.edu.cn/docsn/lxx/mainpage/a/Web/index.htm•Margaret Mary Fernandez," Propellant Tank Pressurization Modeling for a Hybrid Rocket", Department of Mechanical Engineering,Kate Gleason College of Engineering,Rochester Institute of Technology,Rochester, NY 14623, August 2009.•Zakia Nasri and Housam Binous," Applications of the Peng-Robinson Equation of State using MATLAB", National Institute of Applied Sciences and Technology.•Matías A. Monsalvo," Phase Behavior and Viscosity Modeling of Refrigerant-Lubricant Mixtures", Ph. D. Thesis, Technical University of Denmark, Center for Phase Equilibrium and Separation Process.
![Page 31: Modeling of Propellant Tank Pressurization](https://reader036.vdocument.in/reader036/viewer/2022081721/58a1f2251a28ab531e8b7027/html5/thumbnails/31.jpg)
Thank you for listening