Feasibility studies on an auxiliary propulsion system using MPD thrusters

The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author. It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines. Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.

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Feasibility analysis of liquid propellant settling in the tanks of a space propulsion system after flying in zero gravity using a separating turn maneuver of the orbital unit

Space engineering and technology ◽

10.33950/spacetech-2308-7625-2021-1-78-87 ◽

2021 ◽

pp. 78-87

Author(s):

Nikolay N. TUPITSYN

Keyword(s):

Attitude Control ◽

Feasibility Studies ◽

Propulsion System ◽

Zero Gravity ◽

Liquid Propellant ◽

Propulsion Systems ◽

Rocket Propulsion ◽

Liquid Rocket Propulsion ◽

Liquid Rocket ◽

Main Engine

The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author. It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines. Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.

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Analysis of Self-field MPD Thrusters for Designing a Megawatt-class In-space Propulsion System

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference ◽

10.2514/6.2014-3418 ◽

2014 ◽

Cited By ~ 2

Author(s):

Ikkoh Funaki ◽

Ken Kubota ◽

Akira Kawasaki ◽

Yoshihiro Okuno ◽

Kenji Miyazaki ◽

...

Keyword(s):

Propulsion System ◽

Space Propulsion ◽

Mpd Thrusters

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Rendez vous with Saturn's rings

International Astronomical Union Colloquium ◽

10.1017/s0252921100101885 ◽

1984 ◽

Vol 75 ◽

pp. 743-759 ◽

Cited By ~ 2

Author(s):

Kerry T. Nock

Keyword(s):

Solar Energy ◽

Electric Propulsion ◽

Power Source ◽

Propulsion System ◽

Low Thrust ◽

Ring Plane ◽

The Earth ◽

Total Impulse ◽

Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

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Feasibility Studies of Two-Stage Testing in Large-Scale Educational Assessment: Implications for NAEP

PsycEXTRA Dataset ◽

10.1037/e540612012-001 ◽

1998 ◽

Cited By ~ 1

Author(s):

R. Darrell Bock ◽

Michele F. Zimowski

Keyword(s):

Large Scale ◽

Feasibility Studies ◽

Educational Assessment ◽

Two Stage

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Dependence of Current Harmonics of Greenhouse Irradiators on Supply Voltage

Light & Engineering ◽

10.33383/2019-024 ◽

2020 ◽

pp. 85-88 ◽

Cited By ~ 1

Author(s):

Nadezhda P. Kondratieva

Keyword(s):

Mathematical Models ◽

Supply Voltage ◽

Harmonic Distortion ◽

Feasibility Studies ◽

Power Losses ◽

Voltage Level ◽

Supply Networks ◽

Current Harmonics ◽

Cable Lines ◽

Harmonic Composition

The article describes the results of the study concerning the effect of the voltage level on current harmonic composition in greenhouses irradiators. It is found that its change affects the level of current harmonics of all types of the studied greenhouse irradiators. With decrease of nominal supply voltage by 10 %, the total harmonic distortion THDi decreases by 9 % for emitters equipped with high pressure sodium lamps (HPSL), by 10 % for emitters with electrode-less lamps and by 3 % for LED based emitters. With increase of nominal supply voltage by 10 %, THDi increases by 23 % for lighting devices equipped with HPSL, by 10 % for irradiators with electrode-less lamps and by 3 % for LED based emitters. Therefore, changes of supply voltage cause the least effect on the level of current harmonics of LED based emitters and then the emitters with electrode-less lamps. Change of the level of supply voltage causes the greatest effect on the level of current harmonics of HPSL based irradiators. Mathematical models of dependence of THDi on the level of supply voltage for greenhouse emitters equipped with LED, electrode-less lamps and HPSL lamps were formulated. These mathematical models may be used for calculations of total current when selecting transformers and supply cable lines for greenhouse lighting devices, for design of new or reconstruction of existing irradiation systems of greenhouse facilities, and for calculation of power losses in power supply networks of greenhouse facilities during feasibility studies for energy saving and energy efficiency increasing projects.

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