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fuel-sloshing
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On the Flutter of Swept Taper Wing in Subsonic Compressible Flow Considering Effect of Fuel Sloshing in External Stores
, M.Sc. Thesis Sharif University of Technology ; Dehghani Firoozabadi, R (Supervisor)
Abstract
In the present work, the aeroelastic stability analysis for the swept taper wing and external fuel tank combination system in subsonic compressible flow are represented. The wing structure is modeled by using the Euler-Bernoulli beam theory. Fuel sloshing is modeled by using an equivalent mechanical mass-spring-damper model. Modal analysis technique is used to drive the structural equations of motion of the system. Aeorodynamic of wing is modeled by using index aerodynamic that has been dived by Marzocca and a slender body aerodynamic theory for the external fuel tank are used. For stability analysis, k-method redrived for a case that structural damping there is. The effects of the external...
A FEM-BEM Model for Investigation of Fuel SlushingEffect on the Supersonic Wing Aeroelasticity
, M.Sc. Thesis Sharif University of Technology ; Haddadpour, Hassan (Supervisor)
Abstract
In the present work the stability analysis for the coupled aeroelasticity and fuel sloshing in supersonic wings is represented. The wing and store structure is modeled using the finite element method. The supersonic wing aerodynamic is modeled by the linear piston theory and store aerodynamic is modeled by the semi-stable slender body piston theory. Fuel sloshing in the store with desired geometry is modeled by the boundary element method. The coupled structure, aerodynamic and sloshing governing equations are drawn by using the Galerkin method and reduce order modeling teqnique for them and an effective numerical model was developed that is capable to analyze the stability for...
3D Modeling and nonlinear Control of a Satellite with 3D Fuel Slosh Dynamics
, M.Sc. Thesis Sharif University of Technology ; Fathi, Mohsen (Supervisor)
Abstract
The thrust vector control problem is studied for a Satellite with fuel slosh dynamics. The sloshing propellant is modeled as a 3D pendulum. The coupled equations of motion of the satellite and the fuel are expressed in terms of the three dimensional satellite translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A nonlinear feedback control law with the idea of backstepping integrator is proposed to control the translational velocity vector and the attitude of the satellite, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law
Translational and Rotational Dynamics and Control Of an All-Thruster Satellite Considering Fuel Slosh
, M.Sc. Thesis Sharif University of Technology ; Assadian, Nima (Supervisor)
Abstract
The purpose of the present study is to model and control a 6DOF satellite dynamics with a rigid body in the Earth’s orbit including the fuel slosh. The satellite manages and controls its attitude and position by twelve ON-OFF thrusters installed alongside the principal body axes. Moreover, due to using the liquid fuel to feed these thrusters, fuel slosh may have a strong dynamical effect on the satellite translational and rotational dynamics and control. The thrusters’ activation may result in fuel slosh and the impact of their frequent switching ON-OFF on fuel is considered in this study. The thrusters force magnitude, switching intervals, and their frequencies can affect the magnitude of...
Multidisciplinary Design Optimization of an Air Launch Satellite Launch Vehicle by Considering the Coupled Slosh–vehicle Dynamics
, M.Sc. Thesis Sharif University of Technology ; Fathi, Mohsen (Supervisor)
Abstract
In this thesis, the multidisciplinary design of liquid propellant satellite launch vehicle has been done by taking into consideration the effects of fuel sloshing. At first, the theory of multidisciplinary design and one-level architecture with the label of multidisciplinary feasibility have been used. In the following, Gravitational Search Algorithm (GSA) and Particle swarm optimization (PSO) have been developed. Then, the multidisciplinary design cycle began with the design of the liquid propellant system. In the propulsion section, the selection of the optimal fuel, the design of the nozzle, motor and the selection of the optimal engine cycle considering the geometric and mass...
Equivalent mechanical model of liquid sloshing in multi-baffled containers
, Article Engineering Analysis with Boundary Elements ; Vol. 47, issue. 1 , Octobe , 2014 , p. 82-95 ; Noorian, M. A ; Haddadpour, H ; Sharif University of Technology
Abstract
This study presents a method to determine an equivalent mechanical model (EMM) for multi-baffled containers with arbitrary geometries. The method is implemented for 2D and axisymmetric containers. The Laplace equation and Green's theorem are used to develop the fluid model and the boundary element method (BEM) is used to solve the fluid field governing equation. Moreover, a zoning method is utilized to model arbitrary arrangements of baffles in multi-baffled containers and a reduced order model is developed to model the free-surface sloshing. The exerted hydrodynamic pressure distribution, forces and moments on the walls of the container are determined based on the Bernoulli equation and a...
Sloshing analysis of flowing liquid in 3D tank using boundary elements method
, Article Journal of Pressure Vessel Technology, Transactions of the ASME ; Volume 135, Issue 2 , 2013 ; 00949930 (ISSN) ; Borhan Panah, M. R ; Sharif University of Technology
2013
Abstract
A numerical model based on the boundary element method is proposed for the sloshing of a flowing liquid in a three-dimensional tank. Assuming a mean flow in the tank in addition to a perturbation flow, the nonlinear boundary conditions of the liquid free-surface are linearized. Using the boundary element method along with the modal analysis technique a reduced order model is obtained which is used to calculate the fundamental sloshing frequencies and modes in the tank with an inlet and outlet. The obtained results for a test case are compared with the literature data to validate the proposed model. The results are in a very good agreement with analytical results and show an acceptable...
Satellite Attitude Control with Consideration of the Fuel Sloshing Dynamics
, M.Sc. Thesis Sharif University of Technology ; Salarieh, Hassan (Supervisor) ; Nejat Pishkenari, Hossein (Supervisor)
Abstract
Modeling and Controlling of a satellites fuel slosh is considered a vital problem in the field of satellite attitude control. In this paper modeling and control of the attitude of a satellite carrying a partially filled spherical fuel tank, which uses the diaphragm as a propellant management device (PMD), has been studied. The fuel slosh dynamics is modeled using a spherical pendulum with two degrees of freedom and a rigid arm, which represents the first mode of sloshing. The effects of the diaphragm that surround the fuel surface, are considered as torsional springs and dampers attached to the satellite body. The combined dynamics equations of the satellite rigid motion and the fuel slosh...
A reduced order model for liquid sloshing in tanks with flexible baffles using boundary element method
, Article International Journal for Numerical Methods in Engineering ; Volume 89, Issue 13 , 2012 , Pages 1652-1664 ; 00295981 (ISSN) ; Firouz Abadi, R. D ; Haddadpour, H ; Sharif University of Technology
2012
Abstract
In order to study the interaction of sloshing and structural vibrations of baffled tanks, a reduced order model based on modal analysis of structure model and boundary element method for fluids motion is developed. For this purpose, the governing equations of elastic structure and incompressible flow are used to derive simple models to simulate both fields. Using the modal analysis technique, the structural motions are applied to the fluid model and on the other hand by using boundary element method, the fluid loads are applied to the structural model. Based on this formulation, a code is developed which is applicable to an arbitrary elastic tank with arbitrary arrangement of baffles. The...
Stability analysis of elastic launch vehicles with fuel sloshing in planar flight using a BEM-FEM model
, Article Aerospace Science and Technology ; Volume 53 , 2016 , Pages 74-84 ; 12709638 (ISSN) ; Haddadpour, H ; Ebrahimian, M ; Sharif University of Technology
Elsevier Masson SAS
2016
Abstract
A numerical model is developed for investigation of coupled dynamics of fuel contained elastic launch vehicles in planar atmospheric flight. Finite element method along with the linear quasi-steady piston aerodynamic theory is used for developing an aeroelastic model. A reduced order boundary element model is used for modeling the liquid sloshing in tanks. The interaction of sloshing and aeroelasticity is studied using stability analysis of the coupled system. Results show that the slosh-aeroelastic coupling in an elastic launch vehicle occurs for low tank filling ratios and may lead to decreasing the system damping. Due to more interactions between the slosh and rigid body modes, larger...
Evaluation of the seismic response of liquid storage tanks
, Article 10th International Conference on Civil, Structural and Environmental Engineering Computing, Civil-Comp 2005, Rome, 30 August 2005 through 2 September 2005 ; 2005 ; 1905088000 (ISBN); 9781905088003 (ISBN) ; Rofooei, F. R ; Bozorgnia, Y ; Sharif University of Technology
2005
Abstract
In this paper, the dynamic response of the anchored and unanchored flexible on-grade storage tanks under near-fault input ground motions has been investigated. For numerical analysis, an oil storage tank with its content has been modeled with the displacement-based elements using a general-purpose finite elements program. The fluid-structure interaction has been taken into account using the constraint equations. Non-linear behavior caused by the base uplift in unanchored tanks has been considered by implementing the gap elements between the tank base and the ground level. The results indicate that the non-linear behavior caused by the base uplift, leads to remarkable changes in most of the...
Development and verification of a flexible tethered satellite system model considering the fuel slosh
, Article Multibody System Dynamics ; Volume 56, Issue 3 , 2022 , Pages 289-312 ; 13845640 (ISSN) ; Vatankhah, R ; Eghtesad, M ; Assadian, N ; Sharif University of Technology
Springer Science and Business Media B.V
2022
Abstract
Removing space debris of various sizes, configurations, and properties from Earth’s orbits is one of the main missions of world space agencies. The existence of deactivated bodies within the path of other spacecraft increases the risk of collision. Althgough towing a satellite through a tether and taking it out of orbit may be a definite solution for space debris removal, most deactivated satellites have some fuel remaining in their fuel tank. This remaining liquid slosh within the tank directly affects satellite motion. To improve the mathematical modeling, the existence of unburned fuel is considered. More specifically, this research focuses on dynamic modeling and control of a selected...
Satellite attitude PDE-based controller design considering fluid fuel sloshing in planar maneuver
, Article Aerospace Science and Technology ; Volume 122 , 2022 ; 12709638 (ISSN) ; Salarieh, H ; Nejat Pishkenari, H ; Sharif University of Technology
Elsevier Masson s.r.l
2022
Abstract
Due to significance of high-accuracy attitude control, the fuel sloshing effects on the satellite attitude should be considered, more precisely. This work deals with the attitude control of a liquid propellant-filled satellite considering the incompressible fuel sloshing in the planar maneuver. The satellite consists of a rigid body, a partially-filled tank and a flexible diaphragm. Hamilton's principle is employed to derive nonlinear coupled PDEs-ODEs governing the coupled satellite-diaphragm propellant tank system. Afterwards, to dispense with the spillover instability, a PDE-based controller is designed to realize the satellite attitude control while tracking a desired pitch angle and...
Nonlinear vibrations and chaos in floating roofs
, Article Journal of Computational and Nonlinear Dynamics ; Volume 7, Issue 2 , January , 2012 ; 15551415 (ISSN) ; Tariverdilo, S ; Salarieh, H ; Sharif University of Technology
2012
Abstract
Variational principle is used to derive the nonlinear response of the floating roof of cylindrical liquid storage tanks due to harmonic base excitations. The formulation accounts for nonlinearity due to large deflections of the floating roof. The derived nonlinear governing equation for the sloshing response of the floating roof has a cubic nonlinear stiffness term similar to the well known Duffing equation. It is shown that accounting for large deflections could substantially reduce the wave elevation for near resonance harmonic excitations. Evaluating the response of the nonlinear model for increasing amplitudes of near resonance harmonic excitations gives rise to the appearance of sub and...