NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A Combined Solar Electric and Storable Chemical Propulsion Vehicle for Piloted Mars MissionsThe Mars Design Reference Architecture (DRA) 5.0 explored a piloted Mars mission in the 2030 timeframe, focusing on architecture and technology choices. The DRA 5.0 focused on nuclear thermal and cryogenic chemical propulsion system options for the mission. Follow-on work explored both nuclear and solar electric options. One enticing option that was found in a NASA Collaborative Modeling for Parametric Assessment of Space Systems (COMPASS) design study used a combination of a 1-MW-class solar electric propulsion (SEP) system combined with storable chemical systems derived from the planned Orion crew vehicle. It was found that by using each propulsion system at the appropriate phase of the mission, the entire SEP stage and habitat could be placed into orbit with just two planned Space Launch System (SLS) heavy lift launch vehicles assuming the crew would meet up at the Earth-Moon (E-M) L2 point on a separate heavy-lift launch. These appropriate phases use high-thrust chemical propulsion only in gravity wells when the vehicle is piloted and solar electric propulsion for every other phase. Thus the SEP system performs the spiral of the unmanned vehicle from low Earth orbit (LEO) to E-M L2 where the vehicle meets up with the multi-purpose crew vehicle. From here SEP is used to place the vehicle on a trajectory to Mars. With SEP providing a large portion of the required capture and departure changes in velocity (delta V) at Mars, the delta V provided by the chemical propulsion is reduced by a factor of five from what would be needed with chemical propulsion alone at Mars. This trajectory also allows the SEP and habitat vehicle to arrive in the highly elliptic 1-sol parking orbit compatible with envisioned Mars landing concepts. This paper explores mission options using between SEP and chemical propulsion, the design of the SEP system including the solar array and electric propulsion systems, and packaging in the SLS shroud. Design trades of stay time, power level, specific impulse and propellant type are discussed.
Document ID
20140002512
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Mercer, Carolyn R.
(NASA Glenn Research Center Cleveland, OH, United States)
Oleson, Steven R.
(NASA Glenn Research Center Cleveland, OH, United States)
Drake, Bret
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
March 31, 2014
Publication Date
September 10, 2013
Subject Category
Spacecraft Design, Testing And Performance
Spacecraft Propulsion And Power
Report/Patent Number
E-18772
Meeting Information
Meeting: AIAA SPACE 2013 Conference
Location: San Diego, CA
Country: United States
Start Date: September 10, 2013
End Date: September 12, 2013
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 272725.04.01.01.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available