arthur n. guest, aguest@mit wilfried k. hofstetter, [email protected]
DESCRIPTION
Interplanetary Transfer Vehicle Concepts for Near-Term Human Exploration Missions beyond Low Earth Orbit. Arthur N. Guest, [email protected] Wilfried K. Hofstetter, [email protected] Paul D. Wooster, [email protected] DevelopSpace Initiative Inc. Presentation at AIAA Space 2010 - PowerPoint PPT PresentationTRANSCRIPT
August 30, 2010 [email protected]
Interplanetary Transfer Vehicle Concepts for Near-Term Human Exploration Missions
beyond Low Earth Orbit
Arthur N. Guest, [email protected]
Wilfried K. Hofstetter, [email protected]
Paul D. Wooster, [email protected]
DevelopSpace Initiative Inc.
Presentation at AIAA Space 2010
Anaheim, August 30, 2010
August 30, 2010 [email protected]
Overview⢠This paper analyzes candidate minimalist system designs for potential âflexible-
pathâ destinations, including the following mission types: â Lunar fly-byâ Lunar orbit â Sun-Earth L2 libration pointâ Geo-synchronous orbitâ Near-Earth objects
⢠The analysis is based on the use of existing in-space propulsion stages (EELV upper stages), along with a heavy-lift launch vehicle, crew entry capsule (such as the Orion vehicle), and small habitation module (along the lines of the Altair crew compartment)
⢠Overall goal is to identify options for conducting these types of missions with minimum additional development effort
⢠This project is being undertaken as part of DevelopSpaceâs open-source space development activities
â All models, analyses, and supporting documentation is available through http://wiki.developspace.net/ITV and http://svn.developspace.net/svn/itv/
â Material is provided to serve as a basis for further development of these concepts
August 30, 2010 [email protected]
Agenda
⢠Motivation for human deep space missions
⢠Mission assumptions and requirements
⢠Architecture-level analysis
⢠Detailed discussion of mission designs
⢠Conclusions and future work
August 30, 2010 [email protected]
Motivation for Human Deep Space Missions
⢠Human deep space missions to destinations such as a Near Earth Object (NEO) could serve as near-term (this decade) stepping stones to human Mars exploration
⢠Human deep space missions do not require development of capabilities for Mars entry, descent & landing (EDL) and planetary landing, and are therefore easier to achieve than lunar surface missions
⢠NEO missions in particular offer deep space operational experience relevant to human Mars missions while also providing significant science return (e.g. samples)
August 30, 2010 [email protected]
Agenda
⢠Motivation for human deep space missions
⢠Mission assumptions and requirements
⢠Architecture-level analysis
⢠Detailed discussion of mission designs
⢠Conclusions and future work
August 30, 2010 [email protected]
Mission Assumptions and Requirements
⢠Basic requirements for the different mission types
⢠The lunar missions are carried outusing only an entry capsule such asthe Orion Crew Module for habitation
⢠For the SE-L2, GEO, and NEO missions,an additional habitation module similar tothe ESAS LSAM ascent crew module usused (no propulsion system)
MissionTotal missionduration [d]
Crewsize [-]
InjectionÎv [m/s]
Destination capture
Îv [m/s]
Destinationdeparture
Îv [m/s]
Lunar flyby 7 (3.5/0/3.5) 4 3200 20 (MCC) 20 (MCC)
Lunar orbit 9 (3.5/2/3.5) 4 3200 835 + 20 (MCC) 835 + 20 (MCC)
SE-L2 visit 80 (35/10/35) 4 3200 400 + 50 (MCC) 400 + 50 (MCC)
GEO visit 10.5 (0.25/10/0.25) 4 24302100 (incl. 28.5° plane change)
1470
NEO visit 138 (111/16/11) 3 3291 2193 1746
Orioncrew module
LSAMcrew module
August 30, 2010 [email protected]
Agenda
⢠Motivation for human deep space missions
⢠Mission assumptions and requirements
⢠Architecture-level analysis
⢠Detailed discussion of mission designs
⢠Conclusions and future work
August 30, 2010 [email protected]
CEV SM + 1 Centaur V1
CEV SM + 2 Centaur V1
CEV SM + 3 Centaur V1
CEV SM + 4 Centaur V1
CEV SM + 5 Centaur V1
2 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [4 SSME +2 x 5-Segment SRB,
Inline]
2 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
1 x [3 SSME +2 x 4-Segment SRB,
Inline]
1 x [4 SSME +2 x 5-Segment SRB,
In-line]
1 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
Lunar Orbit
SE-L2
Lunar Flyby
GEO
NEO
1 x [4 SSME +2 x 5-Segment SRB,
In-line]
Centaur V1 Architecture Analysis
August 30, 2010 [email protected]
CEV SM + 1 Delta 4 Heavy Upper Stage
CEV SM + 2 Delta 4 Heavy Upper Stage
CEV SM + 3 Delta 4 Heavy Upper Stage
CEV SM + 4 Delta 4 Heavy Upper Stage
CEV SM + 5 Delta 4 Heavy Upper Stage
Lunar Orbit
SE-L2
Lunar Flyby
GEO
NEO
1 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [4 SSME +2 x 5-Segment SRB,
Inline]
1 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
1 x [4 SSME +2 x 5-Segment SRB,
In-line]
2 x [3 SSME +2 x 4-Segment SRB,
Inline]
2 x [3 SSME +2 x 4-Segment SRB,
Side-Mount]
Delta IV Upper Stage Architecture Analysis
August 30, 2010 [email protected]
Agenda
⢠Motivation for human deep space missions
⢠Mission assumptions and requirements
⢠Architecture-level analysis
⢠Detailed discussion of mission designs
⢠Conclusions and future work
August 30, 2010 [email protected]
4 Centaur V1 stages3 Centaur V1 stages
2 Centaur V1 stages
1 Centaur V
1 stage
Numerical Earth Departure Analysis
August 30, 2010 [email protected]
Lunar Flyby Mission Storyboard
Earth
Lunarorbit
LEO
Earthâsmoon
Centaur V1 stages discarded
Launch 1
Trans-lunar coast Trans-Earth coast
Earth entry
Earth landing
Lunar flyby
August 30, 2010 [email protected]
Lunar Orbit Mission Storyboard
Earth
Lunarorbit
LEO
Earthâsmoon
Centaur V1 stages discarded
Launch 1
Trans-lunar coast Trans-Earth coast
Earth entry
Earth landing
Lunar orbit operations
Science package remains in lunar orbit
Low lunar orbit capture Low lunar orbit departure
August 30, 2010 [email protected]
SE-L2 Mission Storyboard
Earth
SE-L2halo orbit
LEO
SE-L2asset
Centaur V1 stages discarded
Launch 1
Trans-SE-L2 coast Trans-Earth coast
SE-L2 captureSE-L2 departure
SE-L2operations
Earth entry
Earth landing
Servicing payload left atthe observation asset
August 30, 2010 [email protected]
GEO Mission Storyboard
Earth
GEO
LEO
Centaur V1 stages discarded
Launch 1 Launch 2
Trans-GEO coast Trans-Earth coast
GEO capture
GEO departure
GEO operations
Earth entry
Earth landing
GEOasset
Mission module and sciencepayload remains with asset or is discarded
Capture stage discarded
August 30, 2010 [email protected]
NEO Mission Storyboard
Earth
NEOvicinity
LEO
NEO
Centaur V1 stages discarded
Launch 1 Launch 2
Trans-NEO coast Trans-Earth coast
NEO capture
NEO departure
NEO exploration
Earth entry
Earth landing
Capture stage discarded
Mission module and sciencepayload remains at destination
Consumables for trans-NEO coast discarded
August 30, 2010 [email protected]
Agenda
⢠Motivation for human deep space missions
⢠Mission assumptions and requirements
⢠Architecture-level analysis
⢠Detailed discussion of mission designs
⢠Conclusions and future work
August 30, 2010 [email protected]
Conclusions⢠ITV designs based on NASAâs Orion and adapted EELV upper stages
enable near-term human deep space missions
⢠With a single launch of a heavy-lift launch vehicle (such as a side-mount or in-line shuttle-derived vehicle) lunar flyby, orbit, and SE-L2 missions can be carried out
⢠With two launches, missions to GEO as well as missions to certain NEOs (similar to the NEO 1999 AO10 2025/26 opportunity) can be carried out
⢠For lunar flyby and lunar orbit options, only an Orion-like vehicle (possibly also commercially developed), adapted Centaur V1 upper stages, and a heavy-lift launch vehicle are required
⢠For SE-L2, GEO, and NEO missions, an additional habitation module similar in size to the ESAS LSAM crew module is required for additional pressurized volume and airlock functionality
⢠With the Orion crew module, the human-rated heavy-lift launch vehicle, and possibly also the habitation module, the minimalist architecture would provide important elements extensible to future human Mars missions
August 30, 2010 [email protected]
Suggestions for Future Work
⢠Further detailed analysis of the mission designs outlined⢠Including more detailed definition of science payloads, inflatable
structures for the habitat module, and an in-depth analysis of hydrogen (and possibly also oxygen) boil-off
⢠Detailed analysis of concepts based on a Delta IV Heavy upper stage design adapted for extended use
⢠Extension of the NEO mission analysis to more NEOs⢠Analysis of alternative designs for the entry capsule (for
example designs based on commercial crew systems)⢠Possible entry vehicle mass reductions which may lead to cost
reductions and increased mass margin (or possibly fewer launches)
⢠The DevelopSpace platform can support these types of follow-on activities â http://www.developspace.net
August 30, 2010 [email protected]
Background: DevelopSpace⢠DevelopSpace Initiative, Inc. is a not-for-profit, tax-exempt organization
dedicated to advancing human space activities
⢠We aim to apply open-source principles and development methodologies towards space endeavors
⢠Our intent is to foster a community actively engaged in advancing knowledge, tools, and systems relevant to expanding humanity into space, and openly sharing the associated information resources to broaden adoption and speed development
⢠The DevelopSpace platform at http://www.developspace.net/ provides a space-related knowledge base and project hosting infrastructure such as file repositories, wikis, mailing lists, etc., for open-source, space-related projects
⢠We are open to contributions from all those interested in engaging in the open development space systems and exchange of knowledge related thereto
August 30, 2010 [email protected]
Backup Slides
August 30, 2010 [email protected]
Science Payloads
August 30, 2010 [email protected]
Launch vehicle data
Option Solid Rocket Boosters Core Stage LEO Payload [kg] Source
12 x 4-Segment Solid Rocket
Boosters3 x SSME, Side-Mounted 72000
Presentation to the Augustine Committee
22 x 4-Segment Solid Rocket
Boosters3 x SSME, Inline 74000 ESAS Report
32 x 5-Segment Solid Rocket
Boosters4 x SSME, Inline 97000 ESAS Report
August 30, 2010 [email protected]
Mission payloads
Mission CEV Block IIUpgraded CEV
Block IILSAM crew
compartmentAdditional
consumablesScience payload Total payload
Lunar flyby 10797 kg - - - 1650 kg 12847 kg
Lunar orbit 10797 kg - - - 1650 kg 12847 kg
SE-L2 visit - 11379 kg 2455 kg 1301 kg 4196 kg 19731 kg
GEO visit - 11379 kg 2455 kg 0 kg 4196 kg 18430 kg
NEO visit - 11379 kg 2455 kg 2175 kg 1476 kg 17685 kg
August 30, 2010 [email protected]
Consumables data
August 30, 2010 [email protected]
Launch vehicle shroud volume
August 30, 2010 [email protected]
SE-L2 Earth departure
August 30, 2010 [email protected]
GEO Mission GEO insertion
August 30, 2010 [email protected]
NEO Mission â NEO Insertion