Preliminary analysis of liquid equilibrium configurations and disturbances of a vehicle motion due to liquid sloshing in space.
Liquid equilibrium configurations and disturbances of vehicle motion due to liquid sloshing in space
LIQUID SLOSHING↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Some studies of nonlinear lateral sloshing in rigid containers.
Nonlinear lateral sloshing in rigid tanks of various geometries, noting frequency-amplitude response
CYLINDRICAL TANK↗
A comparison of flexible and rigid ring baffles for slosh suppression.
Damping coefficients for rigid and flexible ring baffles for slosh suppression
LIQUID SLOSHING↗
Experimental and theoretical studies of liquid sloshing at simulated low gravity.
Liquid sloshing at simulated low gravity in rigid cylindrical tank, noting analytical model and experimental results
CYLINDRICAL TANK↗
Mechanical model for longitudinally excited sloshing motion.
Translational excitation mechanical model applied to space vehicle longitudinal excitation, examining sloshing phenomena
LIQUID SLOSHING↗
On liquid sloshing in a cylindrical tank with a flexible bottom.
Liquid sloshing cylindrical tank with elastic bottom for investigating surface tension effect at liquid gas interface of partly filled container
LIQUID SLOSHING↗
Simulation and scaling of low-gravity slosh frequencies and damping.
Low gravity slosh simulation parameters and scaling law used to extrapolate data to full scale spacecraft systems
SPACECRAFT STRUCTURE↗
Results of Microgravity Fluid Dynamics Captured With the Spheres-Slosh Experiment
This paper provides an overview of the SPHERES-Slosh Experiment (SSE) aboard the International Space Station (ISS) and presents on-orbit results with data analysis. In order to predict the location of the liquid propellant during all times of a spacecraft mission, engineers and mission analysts utilize Computational Fluid Dynamics (CFD). These state-of-the-art computer programs numerically solve the fluid flow equations to predict the location of the fluid at any point in time during different spacecraft maneuvers. The models and equations used by these programs have been extensively validated on the ground, but long duration data has never been acquired in a microgravity environment. The SSE aboard the ISS is designed to acquire this type of data, used by engineers on earth to validate and improve the CFD prediction models, improving the design of the next generation of space vehicles as well as the safety of current missions. The experiment makes use of two Synchronized Position Hold, Engage, Reorient Experimental Satellites (SPHERES) connected by a frame. In the center of the frame there is a plastic, pill shaped tank that is partially filled with green-colored water. A pair of high resolution cameras records the movement of the liquid inside the tank as the experiment maneuvers within the Japanese Experimental Module test volume. Inertial measurement units record the accelerations and rotations of the tank, making the combination of stereo imaging and inertial data the inputs for CFD model validation.
slosh↗
Results of Microgravity Fluid Dynamics Captured with the Spheres-Slosh Experiment
This paper provides an overview of the SPHERES-Slosh Experiment (SSE) aboard the International Space Station (ISS) and presents on-orbit results with data analysis. In order to predict the location of the liquid propellant during all times of a spacecraft mission, engineers and mission analysts utilize Computational Fluid Dynamics (CFD). These state-of-the-art computer programs numerically solve the fluid flow equations to predict the location of the fluid at any point in time during different spacecraft maneuvers. The models and equations used by these programs have been extensively validated on the ground, but long duration data has never been acquired in a microgravity environment. The SSE aboard the ISS is designed to acquire this type of data, used by engineers on earth to validate and improve the CFD prediction models, improving the design of the next generation of space vehicles as well as the safety of current missions. The experiment makes use of two Synchronized Position Hold, Engage, Reorient Experimental Satellites (SPHERES) connected by a frame. In the center of the frame there is a plastic, pill shaped tank that is partially filled with green-colored water. A pair of high resolution cameras records the movement of the liquid inside the tank as the experiment maneuvers within the Japanese Experimental Module test volume. Inertial measurement units record the accelerations and rotations of the tank, making the combination of stereo imaging and inertial data the inputs for CFD model validation.
slosh↗
Result of Microgravity Fluid Dynamics Captured with the SPHERES-Slosh Experiment
This paper provides an overview of the SPHERES-Slosh Experiment (SSE) aboard the International Space Station (ISS) and presents on-orbit results with data analysis. In order to predict the location of the liquid propellant during all times of a spacecraft mission, engineers and mission analysts utilize Computational Fluid Dynamics (CFD). These state-of-the-art computer programs numerically solve the fluid flow equations to predict the location of the fluid at any point in time during different spacecraft maneuvers. The models and equations used by these programs have been extensively validated on the ground, but long duration data has never been acquired in a microgravity environment. The SSE aboard the ISS is designed to acquire this type of data, used by engineers on earth to validate and improve the CFD prediction models, improving the design of the next generation of space vehicles as well as the safety of current missions. The experiment makes use of two Synchronized Position Hold, Engage, Reorient Experimental Satellites (SPHERES) connected by a frame. In the center of the frame there is a plastic, pill shaped tank that is partially filled with green-colored water. A pair of high resolution cameras records the movement of the liquid inside the tank as the experiment maneuvers within the Japanese Experimental Module test volume. Inertial measurement units record the accelerations and rotations of the tank, making the combination of stereo imaging and inertial data the inputs for CFD model validation.
slosh↗
Europa Clipper Preliminary Design Review Propellant Slosh Analysis
This presentation outlines the preliminary design review (PDR) propellant slosh analysis done for the Europa Clipper Mission. It provides sample results for both high acceleration pendulum-damper models and low acceleration pendulum-spring-damper models. The high acceleration pendulum-damper models were derived from STAR-CCM+ computational fluid dynamic (CFD) simulations and the low acceleration pendulum-spring-damper models were derived from Surface Evolver models.
slosh↗
Treatment of Launch Vehicle Flight Control Stability Margin Reductions for Crewed Missions with Emphasis on Slosh Dynamics
NESC’s perspective for crewed spaceflight: Acceptance of flight control gain/phase stability margin reductions from industry standards should be accompanied by an adequately extensive technical treatment, including: •Analyzing the fundamental physics involved, with applicable simulation tool verification (particularly if results are dissimilar among rules of thumb, linear tools, nonlinear analysis, and flight data) •Conducting sensitivity studies in time and frequency domains to analyze effects of possible parameter and system variations •Studying the effects of the consequence of instability associated with offending modes by running stressing cases in time domain •Assessing alternative flight control designs to demonstrate that present design appropriately balances overall vehicle risk (i.e., quantitatively delineate chosen tradeoffs between various stability margins and vehicle performance in the context of risk/consequence) Work presented here represents an example summary of expected engineering work to flight-certify crewed missions with unstable slosh modes and reduced stability margins
Launch Vehicle Flight Control↗
New Perspective on Slosh Dynamics in High-Gravity Regimes for Lunar Missions
Slosh dynamics particularly in high gravity regime is of high interest to the NASA Human Landing Systems program, which aims to return humans to the Moon. This paper reexamines the commonly accepted equivalence between pendulum and massspring-damper mechanical analogies, demonstrating the differences through simulations and their impact on design and analysis. This study re-derives equations of motion for these mechanical models including mass-spring-damper (MSD) and pendulum by relaxing simplifying assumptions that had been typically applied to large launch vehicles and may be violated for lunar and planetary landing applications. The newly-derived equations uncover potential modeling gaps when applying the pendulum and MSD models, and the need for additional considerations in their application. Finally, the newly-derived equations are validated using MathWorks® Simscape™ Multibody™ dynamics toolbox simulation.
Pendulum↗
New Perspective On Slosh Dynamics in High-Gravity Regimes for Lunar Missions
Slosh dynamics particularly in high gravity regime is of high interest to the NASA Human Landing Systems program, which aims to return humans to the Moon. This paper reexamines the commonly accepted equivalence between pendulum and mass-spring-damper mechanical analogies, demonstrating the differences through simulations and their impact on design and analysis. This study re-derives equations of motion for these mechanical models including mass-spring-damper (MSD) and pendulum by relaxing simplifying assumptions that had been typically applied to large launch vehicles and may be violated for lunar and planetary landing applications. The newly derived equations uncovers potential modeling gaps when applying the pendulum and MSD models, and the need for additional considerations in their application. Finally, the newly derived equations are validated using MathWorks® Simscape™ Multibody™ dynamics toolbox simulation.
Slosh↗
A simple method for determining the bending moment equation that includes vehicle elastic and sloshing modes and a numerical example
Bending moment of vehicle in terms of control parameters - vehicle elastic and sloshing modes
FLIGHT VEHICLE↗
Study made of large amplitude fuel sloshing
Study of resonant oscillations of an ideal fluid in a cylindrical tank is used to obtain a better understanding of fuel sloshing in large liquid booster. More realistic structural design criteria may be formulated when the dynamic response of the liquid in a cylindrical tank can be predicted analytically.
Di Maggio, O. D.↗
Flexible ring baffles for damping liquid slosh
Slosh damping, obtained through the use of small, less massive, flexible baffles, provides a relatively lightweight system for damping the motions of liquid propellants in launch vehicles, missiles, and other tankage systems.
Brooks, G. W.↗
Improved technique for digital simulation of bending and slosh phenomena
Mathematical model representation of bending and slosh phenomena in the Saturn vehicle results in linear second order differential equations. Improved technique was developed to provide a real-time digital solution of the equations. The technique may also be applied to nonreal time digital simultations, resulting in savings of digital computer time.
Stauffer, N. E.↗