An Integrated Vehicle Propulsion and Power System for Long Duration Cryogenic Spaceflight

Zegler, Frank

doi:10.2514/6.2011-7355

Cited by 10 publications

(8 citation statements)

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“…Today's Centaur has a propellant mass fraction (f P ) of 0.90 and has demonstrated 2% per day boil-off rate. 12 With 199 flights spanning 5 decades and 99 consecutive successes, including the November 2011 launch of the Mars Science Laboratory, Centaur provides the demonstrated reliability that will be critical to ensuring that astronauts are delivered safely into Mars orbit by successfully executing the critical Mars Orbit Insertion burn.…”

Section: A Design Of Mars Transfer Stage (Mts)mentioning

confidence: 98%

“…By integrating the MTS and Mars mission module avionics and power one can avoid duplication, further reducing the MTS mass. 12 Such integration allows removal of Centaur's battery, flight computer and communications antenna.…”

Section: A Design Of Mars Transfer Stage (Mts)mentioning

confidence: 99%

“…This will enable the crew to conduct extensive and detailed scientific explorations of Mars. (12) In-situ resource utilization processing equipment, which would significantly reduce the mass of consumables needed to be transported from Earth to Mars and increase the scientific payload capability of the mission.…”

Section: Enabling Technologiesmentioning

confidence: 99%

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Modular Space Vehicle Architecture for Human Exploration of Mars Using Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Benton

Kutter

Bamford

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper presents a conceptual Mars Exploration Vehicle (MEV) architecture, which includes two unmanned Mars Lander Transfer Vehicles (MLTVs) and a Mars Crew Transfer Vehicle (MCTV) with a crew of four. The MLTVs and MCTV are assembled in low Earth orbit (LEO) from modules launched by four Space Launch System (SLS) and five Delta IV Heavy rockets. The MLTVs and MCTV individually escape from LEO, transit to Mars, brake into Mars orbit using propulsion and aerobraking, and rendezvous and dock in low Mars orbit (LMO). Each MLTV includes an Earth Departure stage (EDS), Mars Transfer Stage (MTS), Lander Service Module (LSM), and two landers: A Mars Personnel Lander (MPL) provides two-way crew transportation between LMO and the surface. Three unmanned Mars Cargo Landers (MCLs) provide one-way cargo transportation and the functionalities of habitats (MCL-H) (2) and rover (MCL-R). The landers rendezvous and assemble on the surface to form a base. The MCTV includes two EDS, two MTS, and the following: (1) The Multi-Purpose Crew Vehicle (MPCV) transports the crew from Earth to LEO, provides propulsion, and returns the crew to Earth after nominal mission completion or in aborts. (2) Three Deep Space Vehicles (DSVs) provide life support consumables, passive biological radiation shielding, crew habitation space, and propulsion. The DSV design was derived from the MCL-H. (3) An Artificial Gravity Module (AGM) allows the MCTV to rotate and generate artificial gravity for the crew and provides photo-voltaic power generation and deep space communications. A miniature magnetosphere (Mini-Mag), a potential key enabler for human interplanetary exploration, is electromagnetically generated on the AGM and provides active crew biological radiation shielding. The MEV architecture is based on many existing or near-term technologies. It incorporates significant modularity and could provide an economical approach to achieve progressively more ambitious stepping stone missions along a flexible path for human solar system exploration: starting with test flights in Earth and lunar orbit and progressing through missions to nearEarth asteroids and the moons of Mars, and culminating in the Mars landing mission.

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Section: A Design Of Mars Transfer Stage (Mts)mentioning

confidence: 98%

Section: A Design Of Mars Transfer Stage (Mts)mentioning

confidence: 99%

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Modular Space Vehicle Architecture for Human Exploration of Mars Using Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Benton

Kutter

Bamford

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…22. 19,20 The IVF utilizes Boil-off GH 2 , including TVS flow, and gaseous oxygen (GO 2 ) to provide RCS, pressurization and limited power. The IVF will use electrically driven, cryogenic piston pumps to pressurize the GH 2 and GO 2 to several thousand kPa.…”

Section: A Design Of Mars Transfer Stage (Mts)mentioning

confidence: 99%

Conceptual Space Vehicle Architecture for Human Exploration of Mars, with Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Benton

Kutter

Bamford

et al. 2012

AIAA SPACE 2012 Conference &Amp; Exposition

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This paper presents a conceptual Mars Exploration Vehicle (MEV) architecture, which includes a Mars Crew Transfer Vehicle (MCTV) with a crew of four, and two unmanned Mars Lander Transfer Vehicles (MLTVs). The MCTV and MLTVs are assembled in low Earth orbit (LEO) from modules launched by six Space Launch System (SLS) rockets. The MCTV and MLTVs individually escape from LEO, transit to Mars, brake into Mars orbit using propulsion (MCTV and MLTVs) and aerobraking (MLTVs only). The MLTVs deliver landers to the MCTV in low Mars orbit (LMO). Each MLTV includes an EarthDeparture stage (EDS), Mars Transfer Stage (MTS), MEV Service Module (MSM), and two landers: A Mars Personnel Lander (MPL) provides two-way transport of the four crewmembers between LMO and the surface. Three unmanned Mars Cargo Landers (MCLs) provide oneway cargo transportation and the functionalities of habitat and rover. The four landers are assembled on the surface to form a base. The MCTV includes three EDS, two MTS, and the following: (1) The Multi-Purpose Crew Vehicle (MPCV) transports the crew from Earth to LEO, provides propulsion, and returns the crew to Earth after completion of a nominal mission or in aborts. (2) Three Deep Space Vehicles (DSVs) provide life support consumables, passive biological radiation shielding, crew habitation space, and propulsion. The DSVs are modified MCL habitat landers. (3) An Artificial Gravity Module (AGM) allows the MCTV to rotate and generate artificial gravity for the crew and provides photovoltaic power generation and deep space communications. A miniature magnetosphere (Mini-Mag), a potential key enabler for human interplanetary exploration, is electromagnetically generated on the AGM and provides active crew biological radiation shielding. The MEV architecture incorporates significant modularity and could provide an economical approach to achieve progressively more ambitious "stepping stone" missions along a "flexible path" for human exploration of the solar system: starting with test flights in Earth and lunar orbit and progressing through missions to near-Earth asteroids and the moons of Mars, and culminating in the Mars landing mission. Nomenclature AGM = Artificial Gravity Module MCTV = Mars Crew Transfer Vehicle BAS = BRV Adaptor Structure (DSV2 to BRV1) MLA = MTS Launch Adaptor BRV = Booster Refueling Vehicle MLTV = Mars Lander Transfer Vehicle DSV = Deep Space Vehicle (DSV1, 2, 3) MOLA = Mars Orbiter Laser Altimeter EAS = EDS Adaptor Structure (EDS1,5-DSV2,3) MPCV = Multi-Purpose Crew Vehicle EDA = EDS Docking Assembly (EDS1, 5 Fwd.) MPL = Mars Personnel Lander EDS = Earth Departure Stage (EDS1, 2, 3, 4, 5) MRA =

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“…For the past several years, United Launch Alliance (ULA) has been developing a propulsion system called Integrated Vehicle Fluids (IVF) [1] to improve the functional and reliability limits of upper stages for long duration space missions. The intent of IVF is to replace the helium storage system and hypergolic thrusters in order to reduce system weight and enhance reliability.…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling of an Integrated Vehicle Fluids System Loop for Pressurizing a Cryogenic Tank

LeClair

Hedayat²,

Majumdar³

2017

53rd AIAA/SAE/ASEE Joint Propulsion Conference

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This paper presents a numerical model of the pressurization loop of the Integrated Vehicle Fluids (IVF) system using the Generalized Fluid System Simulation Program (GFSSP). The IVF propulsion system, being developed by United Launch Alliance to reduce system weight and enhance reliability, uses boiloff propellants to drive thrusters for the reaction control system as well as to run internal combustion engines to develop power and drive compressors to pressurize propellant tanks. NASA Marshall Space Flight Center (MSFC) conducted tests to verify the functioning of the IVF system using a flight-like tank. GFSSP, a finite volume based flow network analysis software developed at MSFC, has been used to support the test program. This paper presents the simulation of three different test series, comparison of numerical prediction and test data and a novel method of presenting data in a dimensionless form. The paper also presents a methodology of implementing a compressor map in a system level code.

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An Integrated Vehicle Propulsion and Power System for Long Duration Cryogenic Spaceflight

Cited by 10 publications

References 0 publications

Modular Space Vehicle Architecture for Human Exploration of Mars Using Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Modular Space Vehicle Architecture for Human Exploration of Mars Using Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Conceptual Space Vehicle Architecture for Human Exploration of Mars, with Artificial Gravity and Mini-Magnetosphere Crew Radiation Shield

Numerical Modeling of an Integrated Vehicle Fluids System Loop for Pressurizing a Cryogenic Tank

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