Information is given in viewgraph form on space power technologies. Energy conversion, the role of nuclear power in space, lunar and Mars bases, and the Pathfinder program are covered

Sovie, Ronald J.

German

NASA Technical Reports Server

SPACE POWER TECHNOLOGIES
_O BY
RONALD J. SOVIE
DEPUTY CHIEF, POWER TECHNOLOGY DIVISION
NASA LeRC
,2
00
!
AIAA/OAST CONFERENCE ON
CSTI AND PATHFINDER
9/13/88
RJS.9-13.001 "_ l
https://ntrs.nasa.gov/search.jsp?R=19890002399 2020-03-20T05:57:05+00:00Z
WHAT WILL BE DISCUSSED
• OAST BASE RESEARCH AND TECHNOLOGY POWER PROGRAM
PATHFINDER
-- ROVER POWER
-- SURFACE POWER
--SPACE NUCLEAR POWER (SP-IO0)
CSTI
- HIGH CAPACITY POWER
RJS.9-13.002
©__
t,.-'
OAST
BASE R & T
POWER PROGRAM
RJS.9-13.oo8
SPACE ENERGY CONVERSION R&T BASE
PROJECT ELEMENTS
• PHOTOVOLTAICS
CELLS, BLANKETS, MODULES
LeRC,
D. FLOOD
JPL
P.STELLA
Oh
Q ELECTROCHEMISTRY
BATTERIES, FUEL CELLS
O THERMAL ENERGY CONVERSION
ADVANCED SOLAR DYNAMICS,
• POWER MANAGEMENT
FAULT TOLERANT, 20 kHz, SPACE
ELECTROPHYSICS
• THERMAL MANAGEMENT
ADVANCED RADIATORS, LOW TEMP.
AMTEC
ENVIRON.
HEAT PUMPS,
LeRC,
L THALLER
LeRC,
M. WARSHAY
LeRC,
R. BERCAW
LeRC,
O-G
M. WARSHAY
JPL
G. HALPRIN
JPL
P. BANKSTON
JPL
J. KLEIN
GSFC, JSC
T. SWANSON W. ELLIS
RJS.9-13.006
LO
",,3
PATHFINDER POWER SYSTEMS - MISSIONS
° ROVER POWER
" LUNAR/MARS EXPLORATION
" ROBOTIC EXPLORATIONAND SAMPLE RETURN
" LUNAR/MARSBASES
• SURFACE POWER
" LUNAR/MARS OUTPOSTS
" PILOTED MARS EXPEDITION
" SPACECRAFT POWER
- EARTH ORBIT
• OBSERVERS
- TRANSFER
• OTHERS
• SPACE NUCLEAR POWER (SP-IO0)
- LUNAR/MARS BASES
- MANNEDMARS EXPEDITION
- ADVANCED EARTH ORBIT OPERATIONS
- OUTER PLANETARY EXPLORATION
RJS.9-13.o15
NASA
C-87o11751
SP-IO0
II II
ROLEOF NUCLEARPOWERIN SPACE
LUNARBASE MANNEDMARS MISSION
DAU CmTRALUTla,H'Y_
HUCtX.AnSPACE_ peSl}
COMMUNICA'IlONSATIH,UTE PO1nflHI
PLANETm
lU_E CF.N1NU.U11UTYPOWER
liST CAImOVEHICLE
MAmeEOVBgCtJSNql
colmumCAllONS MTBJLITEPOWER
PLANETARYEXPLORATION
;or"
,o"o
co-onlimm rt.ATFOnM UTIUTY POWER NIT PJ_TIOII _ co._-Nmo
EVOLUTIONARY POWER REQUIREMENTS FOR
SURFACE BASE OPERATIONS
UNMANNED
PRECURSOR
2 kWe
MANNED INTERIM SUSTAINED
OUTPOST/CAMP BASE BASE
- 25-100kWe 500 kWe 2000 kWe
• ORBITER
• ROVER
• SAMPLE RETURN
• FARSIDE
COMSAT
• HABITAT(6 CREW)
• LABORATORY
• SCIENCEEXPTS
• LOX PILOTPLANT
• SITEPREP
• ROVERS/TRAILERS
• LANDER/ASCENT
VEHICLE
• HABITAT(15CREW)
• ADD'L LABS
• EXTENDEDSCIENCE
• IN-SITU RESOURCES
PLANT
• CELSSRESEARCH
• SURFACESURVEYS
• MINING
• LOX PRODUCTION
• MATL'S PILOTPLANT
• REUSABLELEM
CARGOVEHICLE
• HABITAT(24 CREW)
• RESEARCHFACILITIES
• SUSTAINEDSCIENCE
• INCREASEDLOX
PRODUCTION
• METALS PRODUCTION
• MANUFACTURING
• CERAMICS PRODUCTION
• FOOD PRODUCTION
• PRODUCT EXPORT
• MASS DRIVER
RJS.9-13.027
LUNAR POWER SYSTEM MASS
AND
MARS BASES
100 kWe
SOA ADV NUCLEAR
SOLAR SOLAR 4]-[
NUCLEAR
SURFACE
0
0
LUNAR 3,300,000 33,000 11,900 4000
MARS 120,000 12,500 11,900 4000
500 kWe
LUNAR 165,000 20,700 12,000
MARS 62,500 20,700 12,000
FUS.9-13.O30
MASS SAVINGS IN LEO FOR
LUNAR AND MARS OPERATIONS
NUCLEAR (4 PI SHIELD TRANSPORTED FROM EARTH)
VERSUS ADVANCED SOLAR
t"O
10s- -
-r.
..=.
_ _1o_
z
Igl
105-
LUNAR OPS
5.0 LEO/LUNAR
PAYLOAD RATIO
MARS OPS6.5 LEO/LUNAR
PAYLOAD RATIO
105,500
- i2HLLV'S _
MANNED OUTPOST
100 kWe
721,500
11 HLLV'S
271,700
INTERIM BASE
500 kWe
3,125,000
46 HLLV'S J
1,398,150
SUSTAINED BASE
2000 kWe
RJS.9-13.031
MARS/LUNAR BASE
POWER SYSTEM PHILOSOPHY
• SPACECRAFT, INITIAL CAMP BASED ON ADVANCED
POWER SYSTEMS (10 - 25 kWe MODULES)
SOLAR
0
• SURFACE PREPARATION FOR NUCLEAR POWER
• EVOLUTION TO NUCLEAR
TO THOUSANDS OF kWe
POWER PROVIDES HUNDREDS
• PATHFINDER SOLAR POWER
SP-100 GES SUPPORT
• CSTI - HIGH CAPACITY POWER (NUCLEAR)
RJS.9-13.014
NASAC-411-NN4
O
/
O0
-n;:O
"0_
O_
0_,
;:or-
¢/)
TECHNOLOGY GOALS
• EARTH ORBITAL, SPACECRAFT, OTHER APPLICATIONS
SOLAR 3-6 W/kg
SOA
%,
=! 16-20 W/kg
%
NUCLEAR #_ 15-40 W/kg
RJS.9-13.032
©__
O
PATHFINDER
RJS.9-13.009
SURFACE POWER SYSTEMS
GOAL: DEMONSTRATE FEASIBILITY OF CRITICAL
TECHNOLOGIES NECESSARY FOR INITIAL
CAMPS, SPACECRAFT POWER SYSTEMS
COMPONENT
LUNAR/MARS
t_3
O
cr_
REQUIREMENTS: ~ 3 We/kg - LUNAR CAMP
~ 8 We/kg - MARS CAMP
14 DAYS D/N
12 HR D/N
CYCLE
CYCLE
ENERGY CONVERSION 4 0_300 W/kg
ENERGY STORAGE 4 0--_500-1000 Whr/kg
- MISSIONDEPENDENT
POTENTIAL FOR SUCCESSFUL OPERATION ON MARS,
LUNAR SURFACES
RJS.9-13.020
SURFACE POWER SYSTEMS
PROJECT ELEMENTS
• MISSIONS AND SYSTEMS ANALYSIS
• H2-02 REGENERATIVE FUEL CELL
• PHOTOVOLTAIC POWER
0
"-,.3 - AMORPHOUS SILICON CELLS/BLANKETS
- ADVANCED ARRAY STRUCTURES
• ADVANCED SOLAR DYNAMICS
- CONCEPTUAL DESIGN STUDY
• POWER CONDITIONING/CONTROL
• ENVIRONMENTAL COMPATIBILITY
RJS.9-13.021
SURFACE POWER SYSTEMS
MAJOR DELIVERABLES
FY'93
t_
O
CO
• DEMONSTRATE 2000 HR OPERATION ON 65%
• 300F, 200 PSI
- HIGH PRESSURE ELECTROLYZER(3000 PSI)
- BUILDING BLOCK STACK
REGENERATIVE FUEL CELL
• 1 kWe DEMONSTRATION
• 2000 W/kg
• CONCEPTUAL
- .46 kg/m2
• CONCEPTUAL
DESIGN
- ELECTRICAL,THERMAL
• POWER
AMORPHOUS SILICON ON KAPTON
REDUCED-G ARRAY STRUCTURE
DESIGN OF SOLAR DYNAMIC LUNAR/MARS
3- 8 W/kg
CONDITIONING CONTROL DESIGN/ENVIRONMENTAL
300 W/kg
POWER SYSTEMS
COMPATIBILITY
FUS.9-13.022
SURFACE POWER SYSTEMS
, MAJOR LABORATORIES
C
LD
. LeRC- LEAD CENTER
. TECHNICALSUPPORT FROM JPL, LANL
° CONTACT - J. BOZEK, LeRC
RJS.9-13.023
SPACE NUCLEAR POWER SP-IO0
• PROVIDES NASA SUPPORT TO TRI-AGENCY, DOE/NASA/DOD,
SP-IO0 GROUND ENGINEERING SYSTEM (GES) DEVELOPMENT
PROGRAM
O
- ENSURES REACTORAVAILABLE FOR NASA APPLICATIONS
• REQUIREMENTS
- 100 kWe
- 7- 10 YEARS LIFE
• > .95 RELIABILITY
- 30 W/kg
" 1/3 SHUTTLE BAY
RJS.9-13.024
bo
O0
O_Z
O_
SPACE NUCLEAR POWER SP-100
MAJOR DELIVERABLES
= 2.5 MWT REACTOR TEST - FY'92
• SPACE SUBSYSTEM TEST - 15 kWe FY'94
MAJOR LABORATORIES
DOE " PGM. DIR.- E. WAHLQUIST
JPL " PROJECT MGMT. - V. TRUSCELLO
LeRC o NASA GES SUPPORT - H. BLOOMFIELD
RJS.9-13.025
bO
GO HIGH
CSTI
CAPACITY
POWER
RJS.9-13.033
CSTI HIGH CAPACITY POWER
• PROVIDES FOR INCREASED POWER, RELIABILITY AND
t_O
k--=
¢=.
LIFETIME FOR NUCLEAR SPACE POWER SYSTEMS
THE SP-IO0 REACTOR WITH EITHER DYNAMIC OR
USING
STATIC
CONVERSION SYSTEMS.
FUS,9-13.011
CST/
HIGH CAPACITYNUCLEARPOWER
, FOCUSEDTECHNOLOGYDEVELOP-
MENTTOENHANCECAPABILITYOF
SPACEPOWERSYSTEMSUSING
GESREACTOR
25 -•" 80 W/kg
100 _ 800 kWe
• ADVANCEDENERGYCONVERSION
- FREEPISTONSTIRLINGENGINES
- ADVANCEDTHERMOELECTRICS
• ADVANCEDRADIATORS
• POWERCONDmONING& CONTROL
• REFRACTORY& COMPOSITE
MATERIALS
SPECIFIC
POWER,
Wlkg
,°°m
80
CSTI
GOAL
6O
4O
GES
POWER,kWe
t_
CSTI HIGH CAPACITY POWER
MAJOR MILESTONES
FY92
• DEMONSTRATE TECH. READINESS :_1300 k FPSE
- 1050 k (25%, <6kg/kWe, 25kWe/pl, TR=2.0)
- 1 YEAR ENDURANCE
" COMPONENT PERF. W/REFRACTORY METALS
• Z = 1.2 Si Ge GaP "n" LEG TECH. AVAIL. FOR
- OA Z = 0.85
- DEMONSTRATEPOT. FOR Z = 1.2 COUPLE
GES
• 850k, 550k HT PIPE DEMO., E >0.85, <5kg/m 2
- ADV. RADIATORDEMO. ~ 5kg/m2
• 108 RAD. HARD, 400C INVERTER DEMO.
• COMPLETE REFRACTORY COMPOSITE CHARACTERIZATIONS
• POTENTIAL FOR 10 YEAR LIFE
RJS88-OO7.16
CSTI
HIGH CAPACITY POWER
, NASA CENTERS
LeRC - PROJECT MANAGEMENT - J. WINTER
- ALL PROGRAM ELEMENTS
JPL " ADVANCED THERMOELECTRICS - C. WOOD
RJS.9-13.016
CONCLUDING REMARKS
• COMPREHENSIVE SPACE POWER PROGRAM
" BASE R&T,CSTI, PATHFINDER
" SIGNIFICANT ACCOMPLISHMENTS
O0
• WELL CO-ORDINATED
- SDIO, USAF, DOE
• LEVERAGEAT NATIONALLEVEL
• POWER SYSTEM CAPABILITY
- ENABLE BOLD NEW MISSIONS
" RESTORE NATIONALTECHNICAL LEADERSHIP
• WE HOPE YOU CAN PARTICIPATE
RJS.9-13.019


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