Buoyant anti-slosh system Patent
Submerged fuel tank baffles to prevent sloshing in liquid propellant rocket flight
Evensen, D. A.↗
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Slosh alleviator Patent
Slosh and swirl alleviator for liquid propellant tanks during transport and flight
Nelson, W. J.↗
Lateral sloshing in oblate spheroidal tanks under reduced- and normal-gravity conditions
Natural lateral sloshing frequency of liquids in oblate spheroidal tanks in reduced- and normal- gravity conditions
Coney, T. A.↗
Engineering study of flexible baffles for slosh suppression
Analysis of aluminum and nonmetallic baffles for use with oxygen containers to prevent sloshing
Dodge, F. T.↗
Investigation of slosh anomaly in Apollo lunar module propellant gage
Analysis of propellant sloshing in lunar module during Apollo 14 flight and resultant erroneous indication of low level of propellant
Scholl, H. F.↗
On the change of natural frequencies of a sloshing liquid by movable devices
Sloshing liquid natural frequencies change in cylindrical shell by movable devices, considering immersed thin elastic plate effect
Chang, S.-C.↗
Viking thrust vector control dynamics using hybrid coordinates to model vehicle flexibility and propellant slosh
Viking vehicle structural flexibility and propellant sloshing effects on thrust vector control dynamics, obtaining computer simulated responses for hybrid and discrete coordinate models
Fleischer, G. E.↗
Finite element analysis of Mercury slosh in the solar electric propulsion stage
The static equilibrium shapes of the neoprene bladder have been established corresponding to various ullage and gravity configurations under specified boundary conditions. The hemispherical bladder is taken to be attached at the diametral plane of the sphere with zero relative slope. With these shapes, the spherical tank with bladder and mercury has been modeled as an assemblage of finite elements. The properties of these elements have then been calculated using a linear displacement field. The dynamic characteristics were obtained to be used to define a mechanical analog which will reproduce the sloshing phenomenon of the system.
Singh, J. N.↗
Slosh dynamics of a spin-stabilized spacecraft comprising off-axis tanks filled partially with liquid propellant
The fundamental nonlinear equations of motion were derived and the specialized to a steady-state rotation of the vehicle about a given axis of rotation. A thrust about the spin axis was introduced. A perturbation solution was derived which linearizes the problem. The effect of the centrifugal and coriolis accelerations together with vorticity are implicitly taken into consideration in the formulation. A variational formulation of the associated boundary conditions is presented. For practical cases it is shown that the simple classical pendulum representation for slosh is not very appealing for a spinning spacecraft unless severe restrictions are allowed.
Fontenot, L. L.↗
An analytical tool for simulating Large AMplitude Propellant Slosh
The development of a multiple-mass, nonlinear, finite-element analytical model - the Large AMplitude Propellant Slosh model (LAMPS) in two- and three-dimensional versions, is described. The model is used in predicting the forces on the Space Shuttle external tank caused by large amplitude motion of propellant fluid. Comparisons between measured propellant reorientation forces and those predicted by the LAMPS models are presented, and it is concluded that the model provides a cost effective, experimentally verified approach to a complicated nonlinear problem.
Berry, R. L.↗
Inconsistency of the homogeneous vortex model for liquid slosh in spinning spherical tanks
The problem of liquid slosh in spinning containers represents an important factor in an analytical assessment of the destabilizing energy dissipation in dual spin spacecraft. The solution of the governing equations in this problem is involved due to the occurrence of the Coriolis term. Pfeiffer (1974) introduced the concept of homogeneous vorticity. Although the assumption is valid for completely filled ellipsoidal cavities, it is only an approximation for a partially filled cavity. On the basis of the results of a stability analysis, it appears that the assumption of homogeneous vorticity may be true for filling volumes more than 55%, while for lesser volumes this assumption cannot possibly be true, even approximately. Great care should then be taken in using Pfeiffer's model in flow problems involving intrinsic resonances.
El-Raheb, M.↗
Fuel Gage for Sloshing Tanks
New gage accurately measures fuel remaining in moving, or sloshing, tank. Measures tank air (or other gas) pressure and time required for pressure to change from one preselected level to another. Time measurement directly proportional to volume of air. Data processor computes relative volumes of air and fuel in tank.
Garner, H. D.↗
Liquid oxygen sloshing in Space Shuttle External Tank
This paper describes a numerical simulation of the hydrodynamics within the liquid oxygen tank of the Space Shuttle External Tank during liftoff. Before liftoff, the tank is filled with liquid oxygen (LOX) to approximately 97 percent with the other 3 percent containing gaseous oxygen (GOX) and helium. During liftoff, LOX is drained from the bottom of the tank, and GOX is pumped into the tank's ullage volume. There is a delay of several seconds before the GOX reaches the tank which causes the ullage pressure to decrease for several seconds after liftoff; this pressure 'slump' is a common phenomenon in rocket propulsion. When four slosh baffles were removed from the tank, the ullage gas pressure dropped more rapidly than in all previous flights. The purpose of this analysis was to determine whether the removal of the baffles could have caused the increased pressure 'slump' by changing the LOX surface dynamics. The results show that the LOX surface undergoes very high vertical accelerations (up to 5 g) and, therefore, splashing almost certainly occurs. The number of baffles does not affect the surface if the structural motion is assumed; but, the number of baffles may affect the structural motion of the tank.
Kannapel, M. D.↗
Three-dimensional analysis of liquid oxygen sloshing in Space Shuttle external tank
A three-dimensional numerical simulation has been performed in order to investigate the hydrodynamics within the liquid oxygen tank of the Space Shuttle external tank after liftoff. The results indicate that the LOX surface undergoes very high vertical accelerations (up to 5 g) and that splashing almost certainly occurs. Although the number of slosh baffles is not found to affect the surface, it is noted that the number of baffles may affect the structural motion of the tank. Surface accelerations are similar to those observed in previous two-dimensional simulations.
Kannapel, M. D.↗
Slosh wave excitation in gravity Probe-B spacecraft experiment
The dynamical behavior of fluids, in particular the effect of surface tension on partially-filled fluids in a rotating dewar under microgravity environment have been investigated. Results show that there is a group of wave trains, both in longitudinal and transverse modes, with various frequencies and wavelengths of slosh waves generated by the restoring force field of gravity jitters and centrifugal forces in this study.
Hung, R. J.↗
A numerical and experimental study of three-dimensional liquid sloshing in a rotating spherical container
A numerical and experimental study of three dimensional liquid sloshing inside a partially-filled spherical container undergoing an orbital rotating motion is described. Solutions of the unsteady, three-dimensional Navier-Stokes equations for the case of a gradual spin-up from rest are compared with experimental data obtained using a rotating test rig fitted with two liquid-filled spherical tanks. Data gathered from several experiments are reduced in terms of a dimensionless free surface height for comparison with transient results from the numerical simulations. The numerical solutions are found to compare favorably with the experimental data.
Chen, Kuo-Huey↗
Slosh wave excitation in the gravity probe-B spacecraft propulsion system
The dynamical behavior of fluids in a Gravity Probe-B Spacecraft tank imposed by various frequencies of gravity jitters have been investigated. Fluid stress distribution also have been investigated. Results show that fluid stress distribution exerted on the outer and inner walls of rotating dewar are closely related to the characteristics of slosh waves excited on the liquid-vapor interface in the rotating dewar tank.
Hung, R. J.↗
Gravity jitters excited slosh waves in rotating propellant tank under microgravity environment
The dynamical behavior of fluids, in particular the effect of surface tension on partially-filled rotating fluids (cryogenic liquid helium and helium vapor) in a full-scale Gravity Probe-B Spacecraft propellant tank without probe imposed by various frequencies of gravity jitters have been investigated. Results disclose the conditions for the excitation of large amplitude slosh waves which shall be avoided in the design of cryogenic liquid propellant system.
Hung, R. J.↗