Spaceship Discovery -Vehicle Architecture for Human Exploration of Moon, Mars, and Beyond

With the recently revived interest in space exploration, this design study was undertaken by the author in an attempt to design a vehicle architecture that could achieve the national vision of human travel "to the Moon, Mars, and beyond" in progressively more ambitious steps. This paper presents a conceptual architecture for human interplanetary travel in the not-to-distant future. The main flight vehicle resembles the spaceship Discovery depicted in the novel and film "2001 - A Space Odyssey." Like its namesake, this spaceship could one day transport a human expedition to explore the moons of Jupiter. This spaceship Discovery is a real engineering design that could be implemented using technologies that are currently near the state-of-the-art, including advanced, bi-modal nuclear thermal rocket (NTR) engines for main propulsion and electrical power. Spaceship Discovery is a modular design: Requirements, features, mass properties, and configuration layouts are presented for each module. Four types of lander designs are presented, including requirements, mission profiles, performance data, and configuration layouts: (1) A reentry module to return the crew to Earth at the conclusion of a mission or after aborts, (2) a crew exploration lander for Earth's Moon or Callisto that utilizes only vacuum propulsive braking, and (3 and 4) two types of Mars exploration landers that utilize both aerodynamic and propulsive braking. Four Design Reference Missions (DRMs) were used to develop design requirements: (1) A high-energy mission to the Moon, (2 and 3) low- and high-energy missions to Mars, and (4) A high-energy mission to Jupiter's moon Callisto. The Spaceship Discovery design includes dual, strap-on boosters that enable the high-energy Mars and Jupiter DRMs. Mission profiles, performance data, mass properties, and configuration layouts are presented for each DRM, and then compared side-to-side. Launch requirements, mass properties, and module launch configurations are presented. Spaceship Discovery offers many advantages for human exploration of the Solar System: (1) Nuclear propulsion enables propulsive capture and escape maneuvers at Earth and target planets, eliminating the need for risky aero-capture maneuvers. (2) Strap-on NTR boosters provide robust propulsive energy, enabling missions beyond Mars, and Mars missions with short transit times and free-return aborts. (3) A backup abort propulsion system enables crew aborts at multiple points in the mission. (4) Clustered NTR engines provide "engine out" redundancy. (5) The design provides efficient implementation of omnidirectional GCR shielding using main propellant LH2. (6) The design provides artificial gravity to mitigate crew physiological problems on long-duration missions. (7) The design is modular and can be launched using proposed upgrades to EELVs or Shuttle-derived launch vehicles. (8) High value parts of the vehicle are reusable for Mars and Lunar missions. (9) The design is flexible, with inherent growth capability, and will enable an in-family progression "to the Moon, Mars, and beyond."

[1]  Robert Zubrin Nuclear power and propulsion for missions to Mars and the outer solar system , 1993 .

[2]  Stanley K. Borowski,et al.  "2001: A Space Odyssey" Revisited—The Feasibility of 24 Hour Commuter Flights to the Moon Using NTR Propulsion with LUNOX Afterburners , 1997 .

[3]  P. F. Wercinski,et al.  Mars sample return - A direct and minimum-risk design , 1996 .

[4]  Theodore Rockwell,et al.  Reactor Shielding Design Manual , 1956 .

[5]  Stanley K. Borowski,et al.  Space vehicle design and operation for efficient use of Nuclear Thermal Propulsion , 1993 .

[6]  Michael G. Houts,et al.  Reactor and shielding design implications of clustering nuclear thermal rockets , 1992 .

[7]  J. Wilson,et al.  RADIATION PROTECTION : GALACTIC COSMIC RAYS , 2022 .

[8]  David W. Plachta,et al.  An Updated Zero Boil-Off Cryogenic Propellant Storage Analysis Applied to Upper Stages or Depots in a LEO Environment , 2002 .

[9]  John Matthews,et al.  A Closed Brayton Power Conversion Unit Concept for Nuclear Electric Propulsion for Deep Space Missions , 2003 .

[10]  Eric M. Queen,et al.  Mars science laboratory parachute simulation model , 2006 .

[11]  C. Russell Joyner,et al.  TRITON: A TRImodal capable, Thrust Optimized, Nuclear Propulsion and Power System for Advanced Space Missions , 2004 .

[12]  Stanley K. Borowski,et al.  “Bimodal” Nuclear Thermal Rocket (BNTR) Propulsion for an Artificial Gravity HOPE Mission to Callisto , 2003 .

[13]  G. Keating,et al.  Structure of the Mars Upper Atmosphere: MGS Aerobraking Data and Model Interpretation , 1999 .

[14]  William J. Emrich,et al.  Nuclear propulsion system options for Mars missions , 1992 .

[15]  Stanley K. Borowski,et al.  Nuclear Thermal Rocket/Vehicle Design Options for Future NASA Missions to the Moon and Mars , 1993 .

[16]  Bruce Cordell Manned Mars mission overview , 1989 .

[17]  Stan Gunn,et al.  Design of second-generation nuclear thermal rocket engines , 1990 .

[19]  Patrick A. Troutman,et al.  Revolutionary Concepts for Human Outer Planet Exploration (HOPE) , 2003 .

[20]  Juan R. Cruz,et al.  Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future , 2006 .

[22]  Regis D. Heitchue Space systems technology , 1968 .