A mathematical model for flexible response of uprated Saturn I to inflight winds.
Motion equations for planar simulation of flexible Saturn 1B launch vehicles under in-flight winds using Appell equation, noting sloshing mode
Mitchell, H. P.↗
SEARCH · Search NASA
Results for “slosh”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
On the dynamics of liquids in a cylindrical tank with a flexible bottom.
Liquid dynamics and hydroelastic sloshing in partially filled right cylindrical tank with rigid side walls and flexible bottom of stretched membrane
Chang, S.-C.↗
Evaluation and application of data from low-gravity orbital experiment Quarterly progress report, 20 May - 20 Aug. 1968
Analytical evaluation of repressurization, thermal energy, tank pressure rise, liquid level rise, and sloshing data derived from low gravity earth orbital flight of S-4B stage /AS-203/
Source record↗
Pressure effect of a sound wave on a cryogenic fluid
Sound wave pressure for preventing cryogenic propellant sloshing during space flight
Kramer, F.↗
Guidance and control
Wind effects on rigid launch vehicle guidance and control system design, using model incorporating structural bending and fuel sloshing
Blair, J. C.↗
Instrument for measuring the dynamic behavior of liquids Patent
Pressure sensor network for measuring liquid dynamic response in flight including fuel tank acceleration, liquid slosh amplitude, and fuel depth monitoring
Powell, C. A., Jr.↗
Response analyzers for sensors Patent
Response analyzing apparatus for liquid vapor interface sensor of sloshing rocket propellant
Bynum, B. G.↗
Propellant dynamics in an aircraft-type launch vehicle
Liquid propellant sloshing in tilted axisymmetric cylindrical tanks for space shuttle applications
Dodge, F. T.↗
Free-surface vibrations of a magnetic liquid
Magnetic fluid sloshing in solenoidal magnetic field, describing fluid free surface waves similarity to ordinary liquid waves in reduced gravity field
Dodge, F. T.↗
Introduction to passive nutation dampers
Coning motion can prevent photographic and TV cameras and other oriented spacecraft experiments from maintaining a steady scan, and it can introduce a ripple in the high-gain communication system. Nutation dampers are used to remove this type of spacecraft instability. The first nutation damper flown in a missile for the stabilization of the gyroscope consisted of a hollow ring that was partially filled with mercury, and the sloshing of the mercury dissipated the nutational energy. A similar mercury-ring damper was used in the Pioneer 1 lunar probe in 1958 and became the first nutation damper to be used in space. Since then many types of nutation dampers have been designed for spin-stabilized spacecraft ranging in size from small scientific satellites to large space stations.
Herzl, G. C.↗
Mission definition study for Stanford relativity satellite. Volume 2: Engineering flight test program
The need is examined for orbital flight tests of gyroscope, dewar, and other components, in order to reduce the technical and financial risk in performing the relativity experiment. A program is described that would generate engineering data to permit prediction of final performance. Two flight tests are recommended. The first flight would test a dewar smaller than that required for the final flight, but of size and form sufficient to allow extrapolation to the final design. The second flight would use the same dewar design to carry a set of three gyroscopes, which would be evaluated for spinup and drift characteristics for a period of a month or more. A proportional gas control system using boiloff helium gas from the dewar, and having the ability to prevent sloshing of liquid helium, would also be tested.
Source record↗
Space shuttle ascent flight turbulence response
A totally reusable space shuttle configuration has been analyzed during ascent flight to determine its response to atmospheric turbulence. Responses in the form of booster and orbiter body accelerations and booster wing root shear, bending moment and turque were obtained due to random and quasi-square-wave discrete turbulence. The configuration was also analyzed with booster aerodynamic surfaces removed to simulate an expendable booster. Symmetric and antisymmetric analyses were performed. Propellant sloshing, gust penetration, and automatic control system effects were included. It was found that the symmetric responses were generally higher than the antisymmetric ones. The stability augmentation system tended to lower the booster accelerations in the symmetric case, while increasing the orbiter accelerations.
Source record↗
Study of propellant dynamics in a shuttle type launch vehicle
A method and an associated digital computer program for evaluating the vibrational characteristics of large liquid-filled rigid wall tanks of general shape are presented. A solution procedure was developed in which slosh modes and frequencies are computed for systems mathematically modeled as assemblages of liquid finite elements. To retain sparsity in the assembled system mass and stiffness matrices, a compressible liquid element formulation was incorporated in the program. The approach taken in the liquid finite element formulation is compatible with triangular and quadrilateral structural finite elements so that the analysis of liquid motion can be coupled with flexible tank wall motion at some future time. The liquid element repertoire developed during the course of this study consists of a two-dimensional triangular element and a three-dimensional tetrahedral element.
Jones, C. E.↗
Experimental investigation of liquid propellant dynamics in a double cylindrical tank
Experimental data are presented for verifying the computer program for computing propellant oscillation modes and frequencies for tanks of any shape, fill level, or orientation. The experimental apparatus including the tank, support and excitation system, and instrumentation is described along with the procedures. Results showing slosh forces and moments are tabulated for different fill heights. It was found that for the vertical tank excited along the long axis, the frequencies of the higher modes are significantly higher than with the tank tilted. Little difference was noted for excitation along the short axis.
Ransleben, G. F., Jr.↗
A method for determining the response of space shuttle to atmospheric turbulence. Volume 1: Space shuttle turbulence response
A computer program has been developed and demonstrated that can analyze the response of space shuttle to atmospheric turbulence. The method developed accounts for propellant slosh, gimballed engine, and stability augmentation system (SAS) coupling with the elastic vehicle. Statistical outputs are generated that relate vehicle loads and accelerations to level of random turbulence. For discrete turbulence descriptions, response time-histories are computed. Preliminary turbulence response analyses of space shuttle were conducted for one ascent and one booster flyback subsonic flight condition. The ascent case considered both symmetric and antisymmetric boundary conditions, while only the symmetric analysis was conducted for booster flyback. The three conditions were analyzed with SAS active and inactive, but apparent instabilities with SAS active (arising from improper gains) invalidated the results. Load and acceleration responses in all cases, however, were well within vehicle design limits.
Source record↗
Space Shuttle response to atmospheric turbulence.
A fully reusable Space Shuttle configuration has been analyzed during ascent flight to determine its response to atmospheric turbulence. Propellant sloshing, gust penetration, and automatic control system effects were included. The steady-state aerodynamic method of Woodward was used to derive the generalized aerodynamic forces, using the standard quasi-steady assumption. Aerodynamic interference effects between adjacent wings and bodies were found to be significant, with symmetric responses generally higher than antisymmetric. The stability augmentation system tended to lower booster response while increasing orbiter response. Loads due to 9 m/s quasi-square-wave gusts were considerably higher than the 3 sigma random turbulence loads. The elastic portion of the response accounted for about 15% of the total wing load in the discrete gust analysis, while in the random case the elastic effect was small.
Huntington, R. G.↗
Fluid dynamics test method
Test method and apparatus determine fluid effective mass and damping in frequency range where effective mass may be considered as total mass less sum of slosh masses. Apparatus is designed so test tank and its mounting yoke are supported from structural test wall by series of flexures.
Gayman, W. H.↗
Effect of throttling on interface behavior and liquid residuals in weightlessness
An experimental investigation was conducted to study liquid-vapor interface behavior and subsequent vapor ingestion in a flat-bottomed cylindrical tank following a single-step throttling in outflow rate in a weightless environment. A throttling process in which the final Weber number was one-tenth of the initial Weber number tended to excite large-amplitude symmetric slosh, with the amplitude generally increasing as initial Weber number increased. As expected, liquid residuals were lower than those obtained without throttling and, for moderate values of initial Weber number, could be adequately predicted by assuming that all draining took place at the final Weber number. At large values of Weber number, residuals tended to be lower than this predicted value.
Symons, E. P.↗