Propellant Management Device studies, computational methods and neutral buoyancy tests

Ducret, E.; Moullec, L. Le; Spencer, B.; Balaam, P.

doi:10.2514/6.1992-3611

Cited by 10 publications

(9 citation statements)

References 1 publication

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“…We also observe that the order of magnitude of the ow rates computed in Table VII agree with the estimate of 0:4 cm 3 =s given by Ducret et al [9], although these authors do not give the details of their calculations.…”

Section: Comparison With Data Of Dreyer Et Al In References [11; 12]supporting

confidence: 79%

“…If one attempts to take care of the complexity of the geometry by ignoring the entry and exit regions, then the problem would be to accurately estimate the entry and exit conditions in a straight section of the vane. The author is not aware of direct numerical simulation results for a zero-g PMD published in the open or patent literature; estimates of drainage times are available ( [6][7][8][9]). In particular, Ducret et al [9] estimate a vane ow rate of 0:4cm 3 =s 'for the worst case situation of the input parameters', although the details of their method are not given.…”

Section: Introductionmentioning

confidence: 99%

“…The author is not aware of direct numerical simulation results for a zero-g PMD published in the open or patent literature; estimates of drainage times are available ( [6][7][8][9]). In particular, Ducret et al [9] estimate a vane ow rate of 0:4cm 3 =s 'for the worst case situation of the input parameters', although the details of their method are not given. A more detailed discussion of the di culties associated with a full-edged numerical simulation, versus the advantages of the present approach, is given in Section 5.…”

Section: Introductionmentioning

confidence: 99%

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Estimating zero‐g flow rates in open channels having capillary pumping vanes

Srinivasan

2003

Numerical Methods in Fluids

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SUMMARYIn vane-type surface tension propellant management devices (PMD) commonly used in satellite fuel tanks, the propellant is transported along guiding vanes from a reservoir at the inlet of the device to a sump at the outlet from where it is pumped to the satellite engine. The pressure gradient driving this free-surface ow under zero-gravity (zero-g) conditions is generated by surface tension and is related to the di erential curvatures of the propellant-gas interface at the inlet and outlet of the PMD. A new semianalytical procedure is prescribed for accurately calculating the extremely small fuel ow rates under reasonably idealized conditions. Convergence of the algorithm is demonstrated by detailed numerical calculations. Owing to the substantial cost and the technical hurdles involved in accurately estimating these minuscule ow rates by either direct numerical simulation or by experimental methods which simulate zero-g conditions in the lab, it is expected that the proposed method will be an indispensable tool in the design and operation of satellite fuel tanks.

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Section: Comparison With Data Of Dreyer Et Al In References [11; 12]supporting

confidence: 79%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Estimating zero‐g flow rates in open channels having capillary pumping vanes

Srinivasan

2003

Numerical Methods in Fluids

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“…Space stage propellant tanks, in some cases, are containers of a complex spatial configuration with thin and smooth walls, which are under pressurization gas pressure [e.g., 4,5,8]. The complex and unpredictable features of liquid propellant motion in propellant tanks in microgravity conditions define the increased level of requirements for the design and functional characteristics of PMD (as a rule, well-proven capillary accumulators and mesh phase separators are used as such devices [8,10,13]).…”

Section: Introductionmentioning

confidence: 99%

“…This dynamic system describes the motion of fluid and gas in the tank during various LV program flight motions in microgravity conditions. The processes occurring in this dynamic system are the subject of many-sided experimental and theoretical investigations [e.g., 1,2,4,6,8,20].…”

Section: Introductionmentioning

confidence: 99%

The approach to numerical simulation of the spatial movement of fluid with forming free gas inclusions in propellant tank at space flight conditions

Pylypenko¹,

SMOLENSKYY²,

Nikolayev³

et al. 2022

Kosm. nauka tehnol.

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The space propulsion systems ensure se veral start-ups and shutdowns of main liquid-propellant rocket engines under microgravity conditions for the spacecraft program movements and reorientation control. During the passive flight of the space stage (after its main engine shutdown), the liquid propellant in the tanks continues to move by inertia in microgravity away from the propellant management device as much as possible. In this case, the pressurization gas is displaced to the propellant management device, which creates the potential danger of gas entering the engine inlet in quantities unacceptable for the reliable engine restart. In this regard, determining the parameters of fluid movement in propellant tanks in microgravity conditions is an urgent problem that needs to be solved in the design period of liquid propulsion systems. We have developed an approach to the theoretical computation of the parameters of the motion of the ‘gas — fluid’ system in the propellant tanks of modern space stages in microgravity conditions. The approach is based on the use of the finite element method, the Volume of Fluid method and modern computer tools for finite-element analysis (Computer Aided Engineering — CAE systems). For the passive leg of the launch vehicle space flight, we performed mathematical modeling of the spatial movement of liquid propellant and forming free gas inclusions and determined the parameters of movement and shape of the free surface of the liquid in the tank as well as the location of gas inclusions. The numerical simulation of the fluid movement in an experimental sample of a spherical shape tank was performed with regard to the movement conditions in the SE Yuzhnoye Design Bureau ‘Drop tower’ for studying space object s in microgravity. The motion parameters of the ‘gas — fluid’ interface obtained as a result of mathematical modeling are in satisfactory agreement with the experimental data obtained. The use of the developed approach will significantly reduce the amount of experimental testing of the designed space stages.

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Determination of the parameters of motion of the gas–liquid interface in the fuel tanks of launch vehicle space stages in passive portions of the flight

Nikolayev¹,

Bashliy²,

Sviridenko³

et al. 2017

Teh. Meh.

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To execute program motions, the space stages of liquid-propellant launch vehicles are equipped with restartable propulsion engines. On the shutdown of the propulsion engine of a space stage, the liquid propellant in the tank in microgravity conditions moves by inertia upwards as far as possible away from the intake. This results in the potential possibility of the pressurizing gas penetrating into the engine inlet in quantities that make an engine restart impossible. Because of this, motion parameter determination for a liquid moving in propellant tanks in microgravity conditions is a topical problem to be solved in the designing of liquid-propellant rocket engines. This paper presents a technique for the calculation of the parameters of motion of the gas-liquid interface in the propellant tanks of modern liquid-propellant launch vehicle space stages in microgravity conditions (between a start and a shutdown of their propulsion engines) taking into account the design features of in-tank propellant management devices. The technique is based on the use of the finite-element method, the volume-of-fluid method, and modern finite-element CAE systems. It allows one to determine the parameters of motion and the shape of the free liquid surface in the tank, the parameters of free gas inclusions formed in the liquid, and the efficiency of the in-tank propellant management devices in the passive portion of the launch vehicle flight for the normal operation of the propulsion system. For the conditions of motion of a prototype propellant tank with a liquid in a drop tower, which simulates microgravity, the motion of a liquid in a cylindrical tank was simulated numerically accounting for the deformation of its free surface. The computed motion parameters of the liquid and the gas-liquid interface agree with the experimental data. The technique developed will allow one to reduce the extent of testing of newly developed and upgraded launch vehicle space stages.

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Propellant Management Device studies, computational methods and neutral buoyancy tests

Cited by 10 publications

References 1 publication

Estimating zero‐g flow rates in open channels having capillary pumping vanes

Estimating zero‐g flow rates in open channels having capillary pumping vanes

The approach to numerical simulation of the spatial movement of fluid with forming free gas inclusions in propellant tank at space flight conditions

Determination of the parameters of motion of the gas–liquid interface in the fuel tanks of launch vehicle space stages in passive portions of the flight

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