Future Propellant Management Device Concepts for Restartable Cryogenic Upper Stages

Behruzi, Philipp; Dodd, Charles; Netter, G.

doi:10.2514/6.2007-5498

Cited by 21 publications

(6 citation statements)

References 2 publications

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“…The surface tension coefficient of the propellant is 69.8 dyn/cm. The relocation time can be calculated by equation (5). The relocation time t m for the drop tower test is 0.5 s.…”

Section: Resultsmentioning

confidence: 99%

“…The flow rate of the liquid depends on the width of the vane and the distance between the vane and the tank wall. The second type of vane is perpendicular to the tank wall, and it transports liquid through the rectangular area between the vane and the wall [5,6]. Vanes are particularly beneficial in satellite systems requiring periodic station-keeping maneuvers because satellites only require occasional access to the propellant over the course of a long-duration mission [7].…”

Section: Introductionmentioning

confidence: 99%

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Testing Liquid Distribution in a Vane-Type Propellant Tank under Conditions of Microgravity Using a Drop Tower Test

Liu¹,

Li²,

Wen³

et al. 2020

International Journal of Aerospace Engineering

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Propellant management devices (PMDs) are a key component used to manage liquid propellant in a propellant tank under zero gravity conditions. A microgravity drop tower test system was established to investigate the performance of a PMD. A single module was used for the experiments, and the microgravity level was less than 3 × 10 − 3 g . Anhydrous ethanol was used as the simulate liquid. Different volume fractions of liquid were used to study the influence of the PMD on performance management. Experiments were conducted with the position of the container oriented in different directions. Changes in the gas-liquid interface were studied during the test. This kind of vane transports liquid through the rectangular area between the vane and the wall. The velocity flows along the vane of different liquid volume fractions in the tank were different at the beginning ( t < 0.8 s ) compared with the end of the test. The liquid relocation time was less than 0.8 s while the liquid volume fraction was larger than 25%. The liquid relocation time was prolonged when the liquid volume fraction was less than 25%. The liquid climbing height along the vane under microgravity increased as the volume fraction of liquid reduced. The climbing velocity of the liquid is half reduction when the liquid volume fraction is small. The time for the liquid transferred from the top of the tank to the liquid outlet can be obtained by climbing velocity. It shows that the maneuverability of the satellite decreases at the end of its life. The above results are applicable to all propellant tank with vertical vanes. These results provide a favorable reference for further optimized design of vertical vane-type propellant tanks.

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“…The surface tension coefficient of the propellant is 69.8 dyn/cm. The relocation time can be calculated by equation (5). The relocation time t m for the drop tower test is 0.5 s.…”

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Testing Liquid Distribution in a Vane-Type Propellant Tank under Conditions of Microgravity Using a Drop Tower Test

Liu¹,

Li²,

Wen³

et al. 2020

International Journal of Aerospace Engineering

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“…PMDs were born out of the desire to perform engine restarts in a low-g environment [2,3]. PMDs must be designed and implemented to ensure that there is always communication between the PMD and liquid anywhere within the tank, and to ensure that the tank outlet is sufficiently covered with liquid during any phase of the mission.…”

Section: Figure 2 -Generic Supply and Receiver System Where The Downsmentioning

confidence: 99%

A Detailed Historical Review of Propellant Management Devices for Low Gravity Propellant Acquisition

Hartwig

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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This paper presents a comprehensive background and historical review of Propellant Management Devices (PMDs) used throughout spaceflight history. The purpose of a PMD is to separate liquid and gas phases within a propellant tank and to transfer vapor-free propellant from a storage tank to a transfer line en route to either an engine or receiver depot tank, in any gravitational or thermal environment. The design concept, basic flow physics, and principle of operation are presented for each type of PMD. The three primary capillary driven PMD types of vanes, sponges, and screen channel liquid acquisition devices are compared and contrasted. For each PMD type, a detailed review of previous applications using storable propellants is given, which include space experiments as well as space missions and vehicles. Examples of previous cryogenic propellant management are also presented.

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“…A large number of different experiment sequences were carried out during the 6 minutes of ballistic flight with the goal to demonstrate the capability of the tested concepts in a 0g environment. The experiments are linked to the verification of two Propellant Management Device concepts usable for cryogenic upper stages [1][2][3][4][5][6][7] . Both PMDs represent partial retention devices, containing liquid in a reservoir 8 which is significantly smaller than the tank volume.…”

Section: Introductionmentioning

confidence: 99%

Cryogenic Propellant Management Sounding Rocket Experiments on TEXUS 48

Behruzi¹,

Klatte²,

Fries³

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The TEXUS48 sounding rocket was successfully launched on November 27th 2011 containing two experiment modules with cryogenic liquids. The two experiment modules are experiments dealing with the propellant management of cryogenic liquids in µg using LN2 as test liquid. Main focus of the experiments is to validate two Propellant Management Device (PMD) concepts usable for cryogenic upper stages. In this context a number of different test sequences were carried out, i.e. draining, refilling, heating and depressurization phases. Tank draining concerned the liquid expulsion from the test tank which includes the draining of the PMDs inside the test tank. The PMDs refilled after being depleted with capillary means. Additional heating phases were included simulating the heat soakback via the feed line. In case of upper stages the heat is coming from the hot engine after engine cut-off. Different subcooling states were tested. The present paper discusses the test setup of the two modules. Furthermore a presentation of the different flight regimes and a discussion of the flight results is given. The tests show that the two PMD concepts are able to fulfill the anticipated goals. An overview concerning the two PMD modules and a rough description of the sounding rocket flight were presented in 2012 at the AIAA Joint Propulsion Conference 7 . Nomenclature LOX = Liquid Oxygen LH2 = Liquid Hydrogen LN2 = Liquid Nitrogen L = Length scale PMD = Propellant Management Device PRR = Propellant Refillable Reservoir c R = Capillary radius  = Surface tension  = Density

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Future Propellant Management Device Concepts for Restartable Cryogenic Upper Stages

Cited by 21 publications

References 2 publications

Testing Liquid Distribution in a Vane-Type Propellant Tank under Conditions of Microgravity Using a Drop Tower Test

Testing Liquid Distribution in a Vane-Type Propellant Tank under Conditions of Microgravity Using a Drop Tower Test

A Detailed Historical Review of Propellant Management Devices for Low Gravity Propellant Acquisition

Cryogenic Propellant Management Sounding Rocket Experiments on TEXUS 48

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