Arthur N. Guest, aguest@mit Wilfried K. Hofstetter, [email protected]

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


Overview• This paper analyzes candidate minimalist system designs for potential “flexible-

path” destinations, including the following mission types: – Lunar fly-by– Lunar orbit – Sun-Earth L2 libration point– Geo-synchronous orbit– 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 DevelopSpace’s open-source space development activities

– All models, analyses, and supporting documentation is available through http://wiki.developspace.net/ITV and http://svn.developspace.net/svn/itv/

– Material is provided to serve as a basis for further development of these concepts


Agenda

• Motivation for human deep space missions

• Mission assumptions and requirements

• Architecture-level analysis

• Detailed discussion of mission designs

• Conclusions and future work


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)


Agenda







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 [-]

InjectionΔv [m/s]

Destination capture

Δv [m/s]

Destinationdeparture

Δv [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


Agenda







CEV SM + 1 Centaur V1





2 x [3 SSME +2 x 4-Segment SRB,

Inline]


Inline]


Side-Mount]


Inline]


In-line]


Side-Mount]

Lunar Orbit

SE-L2

Lunar Flyby

GEO

NEO


In-line]

Centaur V1 Architecture Analysis


CEV SM + 1 Delta 4 Heavy Upper Stage





Lunar Orbit

SE-L2

Lunar Flyby

GEO

NEO


Inline]


Inline]


Side-Mount]


In-line]


Inline]


Side-Mount]

Delta IV Upper Stage Architecture Analysis


Agenda







4 Centaur V1 stages3 Centaur V1 stages

2 Centaur V1 stages

1 Centaur V

1 stage

Numerical Earth Departure Analysis


Lunar Flyby Mission Storyboard

Earth

Lunarorbit

LEO

Earth’smoon

Centaur V1 stages discarded

Launch 1

Trans-lunar coast Trans-Earth coast

Earth entry

Earth landing

Lunar flyby


Lunar Orbit Mission Storyboard

Earth

Lunarorbit

LEO

Earth’smoon


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


SE-L2 Mission Storyboard

Earth

SE-L2halo orbit

LEO

SE-L2asset


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


GEO Mission Storyboard

Earth

GEO

LEO


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


NEO Mission Storyboard

Earth

NEOvicinity

LEO

NEO


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


Agenda







Conclusions• ITV designs based on NASA’s 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


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 – http://www.developspace.net


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


Backup Slides


Science Payloads


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


Boosters3 x SSME, Inline 74000 ESAS Report


Boosters4 x SSME, Inline 97000 ESAS Report


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


Consumables data


Launch vehicle shroud volume


SE-L2 Earth departure


GEO Mission GEO insertion


NEO Mission – NEO Insertion

Arthur N. Guest, aguest@mit Wilfried K. Hofstetter, [email protected]

Documents

Transcript of Arthur N. Guest, aguest@mit Wilfried K. Hofstetter, [email protected]