The topics are presented in viewgraph form and include the following: an overview of the synthesis report; specific architecture 4 implementations; and specific power systems/environment issues

Graham, Scott R.

English

NASA Technical Reports Server

N93-26895
REPRESENTATIVE SYSTEMS FOR SPACE EXPLORATION
Scott R. Graham
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135
OUTLINE
- OVERVIEW OF THE SYNTHESIS REPORT
- SPECIFIC ARCHITECTURE IV IMPLEMENTATIONS
- SPECIFIC POWER SYSTEM/ENVIRONMENT ISSUES
BACKGROUND
Synthesis Group was created in June 1990 to evaluate Outreach
results and to establish a politically viable foundation
-- Architectures
-- Technology priorities
-- Early milestones
Synthesis Report architectures are an excellent basis from which to
proceed (appropriate framing parameters and range)
-- Associated priority technologies appear appropriate; assessment underway
PRE6EDIING P.alGE BLANK NOT FILMED
https://ntrs.nasa.gov/search.jsp?R=19930017206 2020-03-17T05:41:54+00:00Z
RECOMMENDATIONS
(1)
(2)
(3)
(4)
(s)
(6)
(7)
(8)
(9)
(!.0)
Establish within NASA a long range strategic plan for the nation's civil
space program, with the Space Exploration Initiative as its centerpiece.
Establish a National Program Office by Executive Order.
Appoint NASA's Associate Administrator for Exploration as the
Program Director for the National Program Office.
Establish a new, aggressive acquisition strategy for the Space
Exploration Initiative.
Incorporate Space Exploration Initiative requirements into the joint
NASA-Department of Defense Heavy Lift Program.
Initiate a nuclear thermal rocket technology development program.
Initiate a space nuclear power technology development program based
on the Space Exploration Initiative requirements.
Conduct focused life sciences experiments.
Establish education as a principal theme of the Space Exploration
Initiative.
Continue and expand the Outreach Program.
PRIORITY TECHNOLOGIES
• Heavy lift launch with a minimum capability of 150 metric tons
with designed growth to 250 metric tons
• Nuclear thermal propulsion
• Nuclear electric surface power to megawatt levels
• Extravehicular activity suit
• Cryogenic transfer and long-term storage
• Automated rendezvous and docking of large masses
• Zero gravity countermeasures
• Radiation effects and shielding
• Telerobotics
• Closed loop life sLipport systems
• Human factors for long duration space missions
• Light weight structural materials and fabrication
• Nuclear electric propulsion for follow-on cargo misslons
• In situ resource evaluation and processing
56
t_:
SYNTHESIS REPORT OVERVIEW OF ARCHITECTURES:
I - MARS EXPLORATION
II - SCIENCE EMPHASES FOR THE MOON AND MARS
III - MOON TO STAY AND MARS EXPLORATION
IV - SPACE RESOURCE UTILIZATION
MARS EXPLORATION
The major objective of this architecture Is to explore Mars and provide scientific return.
The emphasis of activities performed on the Moon is primarily as a preparation for the
Mars mission, to test Mars equipment, systems and operations. This permits meaningful
scientific return from the Moon ......
Precursors
6 crew
Lunar IOC 14 days
2006
Lunar
NOC-1
Lunar
NOC-2
Mars IOC
Mars NOC
Number of crow
6 crew
45-60 days
2007
6 crew
30 days
2009
6 Grew
30-100 days
2014
6 crew
600 days
2016
Moon: None
Mars: Scout territory before committing to landing site
Return safely to Moon, check equipment with second mission
Demonstrate extended operations through lunar night using Mars
prototype equipment
Perform complete dress rehearsal for Mars; extended stay time
in lunar orbit; obtain significant life sciences data
Arrive at Mars and accomplish scientific exploration
Achieve long surface stay to perform extensive field exploration,
including addressing difficult and complex scientific problems;
ISRU demonstrations
surface slay lime, launch date
The dates are notional and depend upon available resources and technological development. (16)
57
SCIENCE EMPHASIS FOR THE MOON AND MARS
Balanced scientific retum from the Moon and Mars. Emphasized throughout are exploration end
scientific activities, Including complementary human and robotic missions required to ensure
optimum return.
Precursors
6 crew *
Lunar IOC 14 days
2003
6 crew
Lunar 90 days
NOC-1 2006
6 crew
Lunar 180 days
NOC-2 2007
6 CreW
Lunar 30 days
NOC-3 2008
18 crew
Lunar extended
NOC-4 2O,l,O
-- 6 crew
Mars 30-100 days Arrive at Mars and accomplish sdentlflc explorstlon (same as Architecture I)
IOC 2014
6 crew
Mars 600 days Expand capability to conduct human field work
NOC-1 2016= 2018
12 crew
Mars 600 days Establish permanent base; emphasize exploration and science
NOC-2 2020
6 crew
Asteroid 10-100 days Science Includes mapping, sampling, emplaclng; ISRU experiments
Option (open)
• Number of crew, surface stay tbllet bunch (IMo
• The dates are notional and depend upon available resources and technological development. (16)
MOON TO STAY AND MARS EXPLORATION
Permanent presence on the Moon and Mars exploration. Long term human habitation and
exploration In space end on planetary surfaces provide terrestrial splnoffs to Improve our
life on Earth and Increase knowledge of solar system and ourselves.
Moon: Landing site selection; surface site characterization
Precursors Mars: Global reconnaissance; site selection
6 crew * Establish creW-t-endedsite end conduct survey work for el
Lunar IOC 14 days
2004 future permanent habitat; detailed site charactedzation
6 crew
Lunar 40 days Remain for complete day/night cycle; establish Infrastructure
NOC-1 2005 for permanent habitat
12 crew
Lunar 90 days
NOC-2 2006
Lunar 18 crew
NOC-3 360 days
2007
18 crew
30 days
2009
Mars IOC
Moon: Global reconnaissance; lending site selection
Mars: Global reconnaissance; geophysical end environmental measurements;
site selection
Demonstrate safe return with significant exploration capability;
explore three complex sites; emplaca experiments
Extend length of human presence; permanent crew- tended outpost;
begin construction of lunar observatory
Longer Maya; surface exploration; increase capability of obsarvator(/;
experiment wlth life support system closure
Dress rehearsal for Mars mission; 200 day lunar orbit May time
(same as Architecture I)
Expand surface exploration end observatory capability
Mars
NOC
Emplace multiple habitats, accumulate life science data;
demonstrate resource use, food production, recycle waste
Permanent presence; food production and life support system closure;
in sltu gas production; regular resupply and crew rotation
Lunar Mars dress rehearsal (same as in Architecture I)
NOC-4
6 crew Arrive at Mars and accomplish scientific exploration
30-100 days (same as Architecture I)
2014
6 crew Achieve long surface stay to perform extensive field exploration,
600 days including addressing difficult and complex scientific problems;
2016 ISRU demonstrations (same as Architecture I)
Number ol crew, surface stay time, launchdate
• The dates ere notion-,! end depend upon available resources and technological development, (16)
58
SPACE RESOURCE UTILIZATION
Make maximum use of available resources to support SEI missions. Seek to develop resources
for transportation, habitation, life sciences, energy production, construction, etc. Reduce costs
and approach self-sufficiency.
Precursors
Lunar IOC
Lunar
NOC-1
Lunar
NOC-2
Mars IOC
Mars NOC
Asteroid
Option
6 crew
14 days
2004
6 crew
45-180 days
2006-2010
6 crew
40 days
2011
6 crew
30-100 days
2016
6 crew
30-100 days
2018
6 crew
10-100 days
(open)
Moon: Landing site selection for resource potential
Mars: Site selection; surface characterization
Select a resource-rich site and demonstrate In sltu fuel productlon
for use In rover and ascent vehicle.
Small base, capable of expansion; demonstrates production of fuel,
power beaming, etc.; build infrastructure
Dress rehearsal for Mars mission: extended lunar orbit stay time
(500 days)
Arrive at Mars and accomplish scientific exploration and ISRU
experiments (same as Architecture I)
Achieve long surface stay to perform tests and demonstrations
of In situ resource use to support long term human presence
Emphasis on characterlstlcs and examination of asteroid as a source
of valuable, useful material
• Number of crew, surface May lime, launch dale
• The dates are notional and depend upon available resouroes and technological development. (16)
SPECIFIC ARCHITECTURE IV IMPEMENTATIONS
• PRECURSORS "
• TRANSPORTATION SYSTEMS
• SURFACE SYSTEMS
59
Space Resource Utilization Architecture- Objective and Strategy- i
nil
IMa _CHITECTURE OBJECTIVE ]
ke maximum use of available resources to support |
the space exploratton missions directly.
STRATEGY
'The goal is _ to reduce the direct expense of going to the
Moon and Mars, then to build toward self-su_iciency of
long-duration space bases, and eventuall_ to return energy
and resources to Earth." •
ISpace Resource Utilization Architecture i
- Lunar Precursors and Robotics: Mission Strategy-
IIIII III I I
Strategy:
"...the location and quantities of resources on the Moon ... must be
assessed. Some of this characterization is done remotely from
Earth, but the general plan is to conduct robotic missions to map
the Moon ... emphasizing resource location and quantification."
CY 19
96 197198 199
SPACE
RESOURCE
UTILIZATION
I I t
i I t
I I t
I I
20
O0 101 102 103 104 105 t()6 107 1()8" t09 110 Ill I_'_ 113114 115 116t17118 I 19
I fr...._ Ir--t Ir-,.,q_ I_,.,,_,./_ I
I I I I I I _, , I I I | I ! ,, | ,=, i I I _ I
Reconnaissance orbiter (2)
quantify mineralogy and chemistry
surface topography (stereo visual imagery)
regolith structure (electromagnetic sounder)
electromagnetic noise background
Telerobotlc rover (I)
locate resource deposits
chemical and evolved gas analysis
physicalproperties
6O
Space Resource Utilization Architecture |
- Mars Precursors and Robotics: Mission Strategy- !
II II ii
Strategy:
'The overall approach is to achieve knowledge of Mars from robotic
missions and then to follow Up with detailed field science by humans.
...robotic precursor missions are used to scout the territory before
committing to a landing site .... A minimum set of precursors is
flown to gather the data necessary for selecting Mars landing sites.
i = t = = J j i i i = = t = _ I _ j_SPACE I I I I I I I I I I I I I i I I ir='=ll
RESOURCE
UTILIZATION I I I I I I
, i IF_"_ ir_l i i i i i i I t i i i i i
Reconnaissance orbiter/Comm orbiter (2 each)
image 12 candidate landing sites for certification
- identify and map hazards
chemical and physical properties
strategic science and resource data to aid
site selection
Automated rover (2)
- test for toxicity
- chemical and mineral analysis
- image surface and subsurface
Mars Transportation System (MTS)
Assumptions & Approach
• Mission Concept is a Split-Sprint Type
. Piloted Rights in 2016 & 2018
- Cargo-Only Flights in 2014 & 2016
• Earth.to-Orbit (ETO) Launch Capability is 250t Class
. Cargo-Only MTS Flights Sized for Single ETO (Multiple Cargo Flights/Mission)
• Piloted MTS Flights Utilize Multiple ETO's
• MTS Comprised of Transfer Vehicle (MTV) & Lander Vehicle (MEW)
- MTV Uses Nuclear Thermal Propulsion Osp = 925s)
• MEV Uses Lox/Methane Propellant ODescenffAscent Stages) & Descent
Aerobrake
- MEV Sized to Land 45t onMars Surface
• MTS is Zero-g Vehicle
• MTS Elements are Expended on Each Mission. Except MEV is Reusable
O
MTS Crew Modules Sized for Crew of 6
. Ballistic Crew Recovery at Earth
. Separate Transfer & Lander Crew Modules
- Crew Launched By Shuttle
61
Space Resource Utilization Architecture
Split Sprint Mission Profile
2014/2016 First Mars Mission
2014
Unmanned [ "_
One-way [ ]
Cargo Vehicle_ }
Single bum _u'tn IJcp
Ciurgo
Veh capturu &
remains in orbit
2016
FastTransfer
Opposition
Piloted Vehicle
CRV re4um, V
50 d Surf Stay Piloted
Dep Jet,son _ MOC Tanks
TMI Tankl
Space Resource Utilization Architecture
2014 & 2016 One Way Cargo Mars Transfer Vehicles
Single MEV delivery
Cargo
M_v N q
r i
/
,F
75K
Nuclear
-,80m
Element Mass (kg) 2014 2016
MEV 78900 78900
CRV 0 0
MTV crew habitat system 0 0
Truss strongback,struts& RCS
Reactor/enginemass
Radiationshadowshieldmass
Navigationpackmass
EOC propellant
TEI propellant
MOC propellant
TMI propellant
TMI/MOC common tank (1_
Aft tank total mass
5521
3_2
0
2000
0
0
22925
79236
17797
119958
209781
x2
419562
IMLEO
62
* 2018 manned long my conjunction requires 3 cargo MEVs,
2016 cargo: 3 NTR vehicles canylng I MEV each
5521
3_2
0
2000
0
0
22630
75514
17235
115379
205202
x3
615606
Space Resource Utilization Architecture
2016 Opposition & 2018 Conjunction Piloted Mars Transfer Vehicles
2016 - 425 d transfer time, 50 d stay 2018 - 188 d transfer, 678 day stay
Piloted
MEV
MOC
Tinks
TMI
Tanks (2)
TEI/EOC
Tank
~100m
Element Mass (kg) 2016 2018
MEV 78900 78900
CRV 5808 5808
MTV crew habitat system 58000 58000
Truss strongback, struts & RCS
Reactor/engine mass
Radiation shadow shield mass
5521 5521
6804 6804
5598 5598
EOC propellant
TEI propellant
TEIZEOO common tank (1)
Aft tank total mass
0 0
95281 80090
16873 14705
112154 94795
MOC propellant
MOC tanks (2)
MOC tankset total mass
155260 116030
25002 20103
175620 136133
TMI propellant
TMI tanks (2)
TMI tankset total mass
314870 353880
49035 54360
363905 408240
75K
Engine (2)
IMLEO 816943 796799
Space Resource Utilization Architecture
Methane Lander Characteristics
Propellent Type: Cryogens, liquid oxygen, liquid methane
Rated Thrust: 30,000 lbf each
Number of descent engines: 5
Number of ascent engines: 3
Specific Impulse (vacuum): 380 sec
Total Loaded Mass: 78.9 metric tonnes
Landed Payload Capability: 45 metric tonnes
63
ISpace Resource Utilization- Mars IOC]
Synthesis Group]
• Similar to Mars IOC of Mars Exploration
Architecture
• Arrive at Mars and successfully accompllsh
scientific exploration of its surface.
Prcdeployment of much of the needed
equipment on the Martian surface
and remote testing prior to crew launch
• 30 - 100 day surface stay
• Specified implementation utilizing:
• habitat (same design as the one tested on
the lunar surface)
• pressurized rover
• nuclear power system
• minima] photovoltalc emergency backup
• unloader/mover
• scientific exploration equipment
• communications equipment
• Addition of resource utilization experiments
on the Martian surface
• Methane
• Oxygen
* Specified implementation utilizing:
• pressurized rover
• habitat
• atmosphere reduction plant
PSS Implementation 1
• PSS Objective
Mars IOC establishes the infrastructure to support
a crew of 6 on the Martian surface for up to 90 days.
• Major Elements Delivered
Offioading/Construction Equipment
Habitat Modules/Airlock
Interconnect Node
100 kW Power Module
PVA/RFC Backup Power System
Pressurized Rover
CH4/O2 Unpressurized Rover
ISRU Demonstration Unit
Science
• Capabilities Provided
• Habitat for a Mars surface crew of 6 for up to
90 days
• Continuous power of 100 kW, with PVA backup
• Prcssurlzcd transport on the surface with 100 km
range "
• Payloadunloading
• Sltepreparation
* Localunprcssm-lzedtransportationcapableof
usinglocallyproducedfuel
• Warning systemforsolarflares
• Production of small quantlUes of CH4, H20, 02
• Issues
Required habitat mass
The required habitat mass exceeds payload constraints
of Space Transportation, so habitat is delivered in
multiple modules
Delivery of elements 2 years prior to crew arrival
Elements required to sit on the surface of Mars for
2 years before crew arrives
64
I_wllf I/4d&_ laekW
1
Nuclear Reactor
//
_T
/ I \
\
o
Space Resource Utilization Architecture
Mars IOC
Not to Beak,,
Cartoon--not based on any specific system's study.
65
I Space Resource Utilization- Mars NOC I
]Synthesis Group]
• Emphasizes tests and demonstrations of
in sltu resource use on the Martian surface
to support long term human presence
• Return to original site of Mars IOC
• Specified implementation utilizing:
• resource plant expansion
• small greenhouse
PSS Implementation[
• PSS Objective
Mars IOC objective is to carry out a 600 day crew
stay at the site of the Mars IOC mission.
• Major Elements Delivered
Hab/Lab/Storage Module
Airlock
100 kW Power Module
Greenhouse
Mars Atmosphere Processing Plant
Integrated Mining Vehicle
Fueling Pallet
Unpressurizcd Rover
Consumables
Science
• Capabilities Provided
• Habitat for a Mars surface crew of 6 for 600+ days
• Continuous power of 200 kW. with PVA backup
• Mining
• Food production
• Increased CH4 production
• Issues
Consumables
The mass of the consumables needed (plus pallet)
exceeds the allowable down mass for piloted flights.
Consumables must have a "shelf-life" of 2 yrs.
66
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Spooe Resource Utlllzmllon Archllecture
1_4am NO(; 1
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SPECIFIC POWER SYSTEM/ENVIRONMENT ISSUES
WHAT SHOULD WE CONSIDER TO BE OUR MAXIMUM OPERATING VOLTAGES FOR
SURFACE AND ORBITING POWER SYSTEMS? WHAT INCREASE IN VOLTAGE CAN BE
ACHIEVED WITH INSULATION OF EXPOSED PARTS?
WHAT CONCERNS ARE THERE WITH COPPER OR ALUMINUM CONDUCTORS, ON THE
SURFACE?- OR IN ORBIT? (PROBABLY UPPER BOUNDED BY AREOSYNCHRONOUS
ORBIT).
WE ARE AWARE OF COSA_ _FRAC'rORY METALS IN_0_ATABILITY, WHAT
OTHER MATERIALS MAY EXPERIENCE EITHER CHEMICAL OR ELECTROCHEMICAL
DECOMPOSITION?
WILL A.C. (AS COMPARED TO D.C.) POWER TRANSMISSION R_DUCE POSSIBLE
STATIC BUILD UP AND SUBSEQUENT DUST BR_ING ON EXPOSED POWER SYSTEM
COMPONENTS SUCH AS, ARRAYS, CABLES, CONNECTORS OR INSULATORS? (MOON)
WHAT SPECIAL GROUNDING TECHNIQUES MAY BE REQUIRED FOR SURFACE
PO_ SYSTEMS? (MOON)
CLOSING REMARKS
CONCEPTUAL DESIGNS ARE CURRENTLY BEING DEVELOPED FOR
LUNAR AND MARS POWER SYSTEMS.
BOTH SOLAR AN'D NUCLEAR BASED SYSTEMS ARE VIABLE CANDIDATES PREDI-
CATED PRIMARILY ON POWER LEVEL AND APPLICATION.
SPECIFIC DESIGN DETAILS ARE SO.WHAT LACKING BECAUSE ONLY TOP LEVEL
INFORMA_ON IS AVAILABLE ON EACH ARCHITECTURE AT THIS TIME.
A SYSTEMS APPROACH TO DESIGNING POWER SYSTEMS HAS BEEN ADOPTED AND
WE CONSIDER THE EFFECTS OF VARIOUS SPACE ENVIRONMENTS TO BE A KEY
FACTOR IN THAT APPROACH.
68


Representative systems for space exploration

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