The prediction of future space travel in the next millennium starts by examining the past and extrapolating into the far future. Goals for the 21st century include expanded space travel and establishment of permanent manned outposts, and representation of Lunar and Mars outposts as the most immediate future in space. Nuclear stage design/program considerations; launch considerations for manned Mars missions; and far future propulsion schemes are outlined

Boehmer, C.

Haloulakos, V. E.

English

NASA Technical Reports Server

r ,
":1
I
N91-22155 .,.
21ST CENTURY PROPULS!ON
V. E. (Bill) Haloulakos
C. Boehmer
McDonnellDouglasSpace SystemsCompany
HuntingtonBeach,California
NASA Symposium
"Vision 21"
SpaceTravel for the NextMillenium
NASALewisReseercltCenter,Cleveland,Ohio
3-4 April1990
VJy_ k I II/UL
SPACE TRAVEL INTHE NEXT MILLENIUM?
El How do we predict the future?
• We do so by examining the past
--- We predict the noar future by examining the
immediate past and extrapolate into the far future
by studying the more distant past
• We aiso use a lot of imagination
El Constraint: In the use of our imagination, we are
constrained to obey the "known" laws of physics
228
Ira,
...................... 199'1012826...... n nlnnl
https://ntrs.nasa.gov/search.jsp?R=19910012842 2020-03-19T18:56:06+00:00Z
0 Ray of hope: The laws of physics are known to
have been through many evolutionary
and revolutionary changes. In fact,
they are in a continuous state of flux
O Example: For many centuries physics was taught
with the atom being exactly what the
word means, INDIVISIBLE. Now, of
course, atom is just a name and its
splitting is history.
f
I
__1- GOALS FOR THE 21ST CENTURY
_3 Expanded space travel and establishment of
permanent manned outposts
{3 Lunar and Mars outposts represent the most
immediate future in space trave: and both have
history from the very recent past
229
1991012826-229
-J]
VJY4_'_ I MISAA
LUNAR OUTPOSTS
ZI Tw_&Apollo program was successfully conductedchemmal propulsion
• It was necessary to advance from the liquid
oxygen/alcohol propellants of the V-2 to liquid
oxygen/liquid hydrogen of the Saturn V upper
stages in 15 years
vJy4_o MI
APOLLO 16 MISSION PROFILE
"..... o,,_pj .... _
,=_I/--:-.,--(2_-_._' ,Z_ _,_. _,___
• I -.r,-, , , 4..... L.----.'_C.__-"_ e_---- _ -'--
.......--- .--- ....
• "L "........ _ .....--" _.k _-.-_'_-_ .........., --,.,.. -,-.-_-_.,. :Z,-_-.--
,:-=.=_\ \ .. _....... .-....==.. ._-- -- - .............. -- ..__
.,-..,, --_._':_"/ _...... I,II_ ........i-_, =_/_?/_-}_-_-
_--__._._ _,_.-,,,----_ -,, _.._ _--- _..,._.:J',.......
........,_,,,._..._ ,:,_._,-_..,_,--_...... _._ "_'--..,_,.-_-.=
....... :_.-- . i.-.-_.._.'_-'---
ORIGINAL PAGE IS
OFPOORqIJ/U.RY
230
"-- .... - ........ '* .... Wl I n -- I I I ....... ------ -- ....... ' --
1991012826-230
VJy4._I _MISkA
MARS OUTPOSTS
_1Trips to Marswere plannedand vehicles were
designedfor landingsand returns
• Unmanned 1984
• Manned 1988
C] Tradestudiescomparedchemicalcryogenics
(O2/H2) with direct nuclear thermal propulsion
using the,NERVAengine
The followingchartssummarize,the trades and
vehicledesignsconductedbetween1965
and 1973
HISTORY
Nuclear Engine
O KIWI - A (Los Alamos) 1957-1960
Q KIWI - B (Los Alamos) 1961-1964
ON TO MARS (REVISITED) • KIWI-B4E Aug 1964
- 940MW, 10-rain,restart
_1Phoebus (Los Alamos) 1965-1968
- 4106 MW, 30-min
c 10=..s. ElNRX (Aerojet/Westinghouse)1964-1967
_,,,m,_= Q XE-1 (Aeroj_t/Westinghouse)1969
.J_J_..._,_= _ Nuclear Stage
m SoWSyWmSxW,ws1_onpmmdet_
=2-2,_ im _ Dougias Aircraft 1965-1969
Q McDonnell Douglas 1969-1973
• NuclearFlight DefinitionStudy
- Saturn derivative
- Shuttle
/vU)onne_Oougl=,_Sym_=C_=ny • NuclearStage System DefinitionStudy
- Propulsionmodule
_=po_NsM. =,OUOLA=' • Reusable NuclearShuttle(RNS)
- Lunar
- LEO-GEO
- Earth - Mars
2'31
1991012826-231
VHW= _._2.24 m. y Tlmk
Dim .._
Tank Valve ""----L.---"__/_.__J_
enginm/Tmnk "_ 'LL__o.=
''"'_ " "_ ._ I o.u.,
EnglneSea0.00' -_-
NERVAFLIGHTENGINE _'
1.34 _0.bCONFIGURATION o_ m
llant
/ ' _- Nozzle
t-,- 2.97 m 01=--t _ : 100:1
FULL SCALE MOCKUP
OF NR-1 FLIGHTENGINE,
RATED AT 1500 MW t
AND 75,000 LB THRUST
232
/
1991012826-232
VJ0075,3 1_2BZ .i!J
.=._,___NUCLEAR ROCKET REACTOR TESTINGLASL (LANL)
Power Run Time
Date Level (MW) (rain)
KiWi - A July , 959 70 5
KIWI- A' July 1960 85 6
KIWI - A3 Oct 1960 100 5
KIWI - BIA Dec 1961 32,5 1
KIWI - B1B Sept ! q62 900 1
KiWI - B4A Nov ;962 500 0
KIWI - B4D May 1964 1020 1
KIWI - B4E Aug 1964 940 10
TNT Jan 1965 -- m
Phoebus - 1A June 1965 1090 11
Phoebus - 1B Feb 1967 1500 30
Phoebus - 2A June 1968 4100 13
Pee Wee - 1 Dec 1968 500 40
NF- 1 June 1972 434 108
12
VJO076 2 M28Z
NUCLEAR ROCKET REACTOR/ENGINETESTING
J_l- WESTINGHOUSE/AEROJET
Power Run Time
Date Level (MW) (min)
NRX - _.2 Sept 1964 1100 5
NRX - A3 April 1965 1100 17
NRX - EST March 1966 1100 28
NRX - A5 June 1966 1100 30
NRX - A6 Dec 1967 1100 60
XE Mar 1969 1100 10
233
1991012826-233
CLASS 3 MULTI-MODULE RNS
_,J
Commendand Control Module (6 It) -_r ThermalandMeteoroid -'_ Integra:WaffleProtection \
\ / _-"Spray Nozzle .._.-"_'_
IntermoduleStructure _ \ / \ Refill __,--"_\ /oo.,,..,\
FeedSystem_ _.t_P_--:<_ -- APS Nnzzlee_,,.,J
__ Propellant Modules*
,-,_'_/_ _-x__ (240ft)
\
\, \_ _.--_ Individual Modules
\' _"_-- _r,, ,---_- PropulsionModule (50ft) 15 ft in Diameterby
"-- ._n.l-, 60 ft Long
__ VJVB73 1
CLASS 1 SINGLE-MODULE HYBRID RNS
Command and Control Module (6 ft) -'7
Forward Umbilical /
Slosh _ /
Baffle_ J
IntegralWaffle
Tunnel
Intermodule Structure ._-
OockingInterface--_
Liquid Le_,elSensors \
PS Nozzles
"- Spray Nozzle
Refill
--- Propellant Module
(103.4 P)
Propellent and Meteoroid
Feed System Protection\ PropulsionModule (60 It)
NERVA
234
........ ..... ....._..,,m_i _ ,_.._)
1 QQt f_d ")Q")_ ,'_,')A
NUCLEAR STAGE DESIGN/PROGRAMCONSIDERATIONS
VJX042 M1CV
f/
Q Structure
Q Propulsion
• Auxiliary
• Nuclear
(..3Electrical
• Power
• Guidance/H,wigation
• Control
• Communications
Q Thermal Control
Q Radiation Protection
• Configuration
• Shioldinq
Propellant Control
• Pressurization
• Chilldown
235
II I I I ......... IIII I I .................... i i
1991012826-235
-JI
NUCLEAR STAGE DESIGN/PROGRAM CONSIDERATIONS -'
(Continued)
VJX042 MICV
(3 Weight/Mass Control
Q Ground/Orbital Operations
• As3embly
• Maintenance
(3 Safety
El Reliability
El Manufacturing
• El Test Plan
• Component
• Systems
• Battleship
_. Q Program Schedule
Costs
VJV877 1
J_ 1988 MARS LANDING PROFILE
&V = 11000 fps
30 Days &V = 5500 fps
// Mars "- _. -_'_-...
f 196 Days / ,,._. _ _
// _ \\ 180 Days
, / f _ --. _._, \
__ _ _" AV = RNSs&V = 13000 fps
i 4900 fps
r_
236
........... i it i i, n . __ _1_
1991012826-236
; o
,._ MSFC MANNED MARS v_,,,,
f SPACECRAFT CONCEPT
Forward
Interstage_. --- 22 ft ---_.
Crew _ "_ _. t Weight
Compartment_ / ' l (lb)Aft \
Inter _. 55 It Mluion Module 82,900
stage_
Logistic _ Mars Excursion Module 95,290
Vehicle X
Tunnel \ _ _ _ Mars Probes
MEM _:_ _ _i i Venus Prol:ms 4,000
Interstage - Interstages 21,000Separatlon'_----l---- "_-- _ - ___.L Mars
-. i / _ t ExcursionI-'lane I / _. t/ / -- \ .oduie(..)
Probe / j \ _ Total Spacecra!t 239,190
Interstage .....---_-_--_-- ._-i- ,aEM
Separation [ _ [ / Interstage
P,ane L-J I'
33 It
PROPELLANT REQUIREMENTS- v,v.,,,_> BASELINE MODE
l e 262-nmi Departure Orbit ! _V Wp Wp(t000 (1000 (°/o)RNS {e 300,000-1bCapacity RNSJNumber fp_) Ib)
I _ Arrive ° Earth 4.9 36 2.513I _ -" *Mldcourse 0.7 10.2 0 3
4 I I "_- Leave - Mars 11.0 129.5 6.8 46
F"'T _*Orblt Trim 0.2 6.5 0 2
J J- _ Arrive- Mars (No. 2) 4.6 102.8 5.7 36
:"_-- Arrive - Mars (No. 1) 0.9 25.3 0 8
_ *Midcourse 0.4 21.0 0 7
3 _ Leave - Earth {No. 2) 6.3 242.7 11.0 85
.....
Retrieval (Per RNS) 6.7 26.4 40 10
Leave - Earth (No. 1, Per RNS) 6.7 208.5 10.0 73
1.2
_1_
SP= 450 sec
Total PropellantRequired = 1,097,800 Ib
237
_)
1991012826-237
...... . ..... --.4 ................. "-'_
_. VJ_. 33! M21BZ
LAUNCH../` CONSIDERATIONSFOR MANNED MARS
CAPTURE AND LANDING MISSION (1988)
Class 1
Ll 4 stages, 1,097,800 Ib LH2
Each stage weigh_ F;9,245!b dry
Assume ALS 180,000 Ib
Mission requires 8 ALS launches
• 4 launches of stage (70,000 Ib) + 110,000 Ib LH2
• 4 launches of '174,000Ib LH=(assume 6000-1btank)
Class 3
CI4 stages (1 propulsion, 8 propellant, 1 command
and control module)
• Assume 1,335,00GIb LH=
C)Each stage weighs 85,000 Ib dry
Requires: • 4 launches for propulsion (30,475 Ib) plus
command and control module (4615 Ib)
• 32 launches for propellant module (40,075 Ib)
(containing34,000 Ib LH2)
• 6 launches 42,000 Ib LH2
Total 42 launches (Space Shuttle/Titan IV)
_o NUCLEAR VERSUS CHEMICAL v.,_=,_,
, . J:_- PERFORMANCE COMPARISON
J_ (SAM -STAGETECHNOLOGY)
'_ Mluion II Number Number" I
(Elliptic [ of of
Caplure Launches OLV/ Launches
Orbits) OLV Booster Saturn V Mission Payload Booster Saturn V
"" Planetary Capture Missions' Planetary Flyby Missions-2
1978 Venus Advanced ChemiCal 5 1977 triple 220,000 Ib I S-IVC 4
capture Nuclear-restart 3 planet JAdvanced l 4"
I chemical
1980 Venus Advanced Chemlual 5 !
capture Nuclear restart 3 !Nuclear 2
INuclaar.
restart
1982 Mars Advanced Chemical - 1978 dual 200,000 Ib S-IVC 3
capture Nuclear restart 4 planel Advanced 3"
chemlca!
Nuclear 2
h :lear-
re=tart
1978 Mars Advanced Chemical 8 1976 dual 200,000 Ib I S-IVC 3
capture Nuclear restart 4 planet, Advanced -
powered chemical
Nuclear 2
Nuclear-
restart
' Requires _wo launches for payload
238
.......... ---'--' "' .... - 1991012826'238
VJI
V_f4m mW
,___ VISIONSOF THE FUTURE
_ Deep space travel requires energy and delta
velocity(AV)in particular
_ Propulsion systems with Is > 1500 sec
areneeded
VJK1/0
-=.____PROPULSIONSYSTEM _V CAPABILITIES
W 0 - Gsoss _¢_v¢_ we,,_4
40 i Wp -- Pr0J_liNIn! WOlff| IS -- 3000 IlK
WST ' $1i_f$ WetQrl(
wo,w,_/_!./} • Chemical propulsion can barely
$0 t$= 2S00 sic
.... 20 achieve earth escape with a
.... ,o ////_/ ,_.o,., single-stagevehicle
" /._/'/_/I .s-:ooo..¢ • Higher is propulsion systemssubstantially increase payload
i /,__,_j/., /.' delivery capabilities ;
20 -- ,.
/_// • Hew exotic propulsion systems
_"// I need to be developed and made
j ,s-,o_..¢ economical to produce, store
- E*rm 4 _" Ihuct*ln•.=-. . and use
io - ..31" I"
,I
/ fs- s(X)==¢
_* Ce.mmvt
.I I I _ l
4, 0.$ 011 0.7 011 011 O
ProINdllm Meal lSrKmm Ikp _"WpIWsT)
U4SI FliACTIOI EIIFICI"I ill AV ¢APAIILITli|
! )
1991012826-239
1
°4
1
V_,lO .-'1
SPECIFIC IMPULSES OF ROCKET FUELS
Antimatter
*Project Forecast II "'_=_',;_.._ (PT-42*)
• " vl=wt=llVlVI I I V_I II |lb_llllP_l_l_ll a, _. "
." •,
----." 1000 to ?sec
Nuclear
"__PT-02*)
._.#,;;_6330 sec
Metastable
Molecular Matter (PT-O 1")
Matter __3
i_ 150 sec500 sec
26
240
...... IIII I ..... Ill IIIIIIIIIIql nil ......... w..... ,, _,,
]99]0]2826-240
- !
SPACE TRANSFERVEHICLECOMPARATIVE DESIGN DATA
,,_ LEO - GEO - LEO Mission,..Mpl= 36,000 kg ; Del V = 9 Ion/s;
Burn Time - 3675s (Constant) ,o,_,,.,,cx
I Chemical Huclur,. Fusion,
I cryogenic, 4 Alpha 2's Me=12 (Is)i 6 RL- i@=s
Rocket Engine 400 278 208450 860 2500
Specific Impulse
Mass Breakdown 333,291 134,548 34,685
Propellants k ) 51,275
Fuel I_-_,) 282,015
Oxidizer (LAX} 970 1,937 499PropellantTank
Total Volume (m3.) 8,158 10,849 2,797
Mass (kg)
Pressurization 1,374 1,828 471
Helium System (kg) 792 10,270 30,000
Engine (kg) 3,411 4,538 1,170
Miscellaneous (kg) 383,024 198,033 105,123
:. Total Vehicle Mass
!
29
VJY_I M!
£l The initialvehicle mass serves as the key ,,
criterionof optimization
0 The higherspecific impulseof the fusion
systemresults in lowerpropellant and vehicle
massfor the specifiedmission and payload
241
1991012826-241
;I
FISSIONAND FUSIONROTVCOMPARISON iTOTAL VEHICLE MASSvs. RETURNED PAYLOAD FROM GEO
Assumes Each V_hicle Has Delivereda 36, -kg Payload to GEO
A 175,000 Lf I ' I ..... [ ' : [ ' • = ] _t
--o-- LANL Alpha 2 Nuclear Engine i _,o
- _ Fusion Engine WithIs = 2000 s i
- --->-- Fusion Engine WithIs = 1500 s _
./" i "15o,ooo- "i _ '
- Thrust F = 100 kN ! _'- :
- Mass Me = 12 (Is) I._
125,01111
_ " ,, , , '
3 lO0,0o0
!,-
75,000 I I _ a I I J I J _ t _ I I J m
0 lx104 2X104 3x104 4X104
Massof Payload Returned, Mpl (Kg)
30
_MDC-GA FUSION SPACE TRANSFER
lOl_ml SGX
VEHICLE SIZING DATA
Mlssi, J: Transfer 36,000 kg to Geosynchronous Orbit (GEO)
Return Vehicle Empty and with Original Payload
Engine: GA Fusion Engine
Is = 1500 s, Thrust = 100 kN, Mass = 12 (Is)
LEO-GEO LEO-GEO
MassBreakdown EmptyReturn Return payload
Propellant (kg) 27,910 57,597
Propellanttank
Total volume (m3) 402 829
Mass (kg) 2,251 4,644
_Pressurization (kg) 379 783
Engine (kg) 18,000 18,000
Miscellaneous (kg) 941 1,942
Total VehicleMass(kg) 98,070 118,967
III I II
242
4
--- ............ "......................... 1991012_26-242
2f_ VJY4S6, I M15AA
_I MATTER/ANTIMATTER ANNIHILATION
Problems and promises
• Production: USAF has priced a production facility at BNL
for 10_s _/yr at approximately $14 million (1989)
• Containment: Antiprotons have been stored for long
periods at CERN and preliminary designs for
transportable storage bottles have
been proposed
• Antimatter use holds great promises for applications in
-- Medicine: Diagnosis and eradication of tumors
-- IVmterials:Location and cure of flaws, processing of
composites, etc,
• This synergism should be explo:ed and pursued
243
1991012826-243
VJY4I7.1MIIIAAFAR FUTUREPROPULSIONSCHEMES
CI Matter/antimatter
• Antimattersafely stored will deliver its energy,
via beamtechnology, to a flowing propellant. ._
Rates of energy delivery and propellant flewr_te _'
to control the level of the thrust to any i
desiredlevel i
L"JTeleportation "Beam me up, Scotty"
• Matterdestructuring(i.e., breakdown into
particles),and restructuringto be first
perfectedon inanimateobjects.
Transportationto be done by beam technology
34
VJY4M ! MISAAFAR FUTUREPROPULSIONSCHEMES(CENT)
_1 Antigravity
• Gravity waves will be fully characterized (Why not?)
• Each celestial body sends out waves whose amplitude and
frequency are directly related to its mass end :;ize
• The net gravity field at any point in space is the result of the
gravity wave Interferencepattern
• Super sensors and supercomputers analyze this wave pattern and
identify its basic components
• An "antigravity wave generator" will then generate waves of
precisely tha same amplitude and frequency but of opposite
phase° Thus, by causingan exact destructive interference, it will
precisely cancel out the gravity field
• A suitablepropulsion systemcan then accelerate the vehicle to
very high velocities with a rather low force and low
energy expenditure
244
-- IIIII ............. I | I | -- - - i,,,, .... .- - ......
1991012826-244
....... ,_..._.,_._ , • • r,-T_-¸_ ........ _ ..........
t
VJYO 141_ -'_
WAVE,:-.FE.ENCE I,l-
1
_- / e'
g.
_J-_
--It ' (lO
(a) The dashed line is a sswtooth *'wm_" conv'noniy imcountm_i In steclronics. The Fouder Imriee
for this function is y(t) : - 1__ sin (_ - I 1x _ sin2m- sin2m.....
The solid IIn_ is the sum of the HrM six terms of Ibis _ lind can be seen to the Iq_p_ximate the
satvtooth quits ciose_;.
_ (b) Here we show the first six lerms of the Fourier series whir.h, when added IogMItef, ytetd Ihe
T solid curve in (a).
36
D VJY410MI _A
i- WAVE ESTRUCTIVEINTERFERENCE
WAve o
J-m_
_.-_- f_.
"Anti°
Wive" J
I_-_--
,-,.-?--
Result:
No Wsve
245
................. IIII I I I
........ '"" 1991012826-245
¥JV41! MIII/IA
SCIENCEFICTION?
IO-- _. I
re_!
13Sciencefiction of one time period
is sciencefact of some later time
I
0 Let us consider the following
38
_BUCK IN THE 25th CENTURYROGERS
246
/
1991012826-246
TI_¸- ................................ _1
-I
1
SCIENCEFICTION1934
_ 4-.: .... _ , I
_NOWS MOw
/
_o u_scl_:
J .
i BUCK ROGERS' SPACESHIP m BUCK ROGERS WITH HIS
FLYINGBELT
OR_G]NAL PAGE IS
OFPOOeQum.n'Y
40
SCIENCE FACT "1984II THE 25 TM CENTURY RRIVED IN 50 YRS
./
I ASTRONAUT'SSPACESHIP • NASA ASTRONAUTWITH HIS
"FLYING BELT"
247
- , , |
_-- ' .... ' ' -' -"...... 1991012826'247
SCIENCE FICTION 1966
i
• 23_ CENTURYSTARSHIPENTERPR|$1:POWEREDBY AN
ANTIMATTERREAalON CHAMBER CAN REACH SPEEDS
UP TO WARP 8
ORIG_;_,L PAGE ;$
_2 OF PJOR (_N.ffY
._._ _O|E_OEF_ICT2BI&7(Cil:lVEi_Fi._i t_TIEH)
• WILl. THE 23 *DCENTURY'HAVE .,_RRIVED?
I WILL STARSHIPENTERPRISEAND STARBASEi2
HAVE BECOME REALITIES?
"PIONEIERING THE SPACEFR_NI"IIER"
248
-%
J
1991012826-248
,.
r
,m
ORIGINAL PAGE 18
OFPOO_Qu_LrrY
VJY_r_ _ MtSAA
CAN WE DO IT?
C) Recent history tells us: Yes!
O We went from Sputnik 1 to Apollo 11 in less
than 12 years
L-')From th_ b__sicuniversity lab atom splitting !
experiment (Berlin, Dec !"938_to Hiroshima and
Nagasaki (Aug 1945) in 6.5 y(_ars
O We need a strong resolve, committment of
resources, and dedication
C) We should not be afraid of risk and milure
249
L
_-- ] -- _ _ -- -- r ...... J --_ iT _'_r ...... '.... 1 I I I , •
1991012826-249
_!
0 Some of the greatest advancesand discoveries
resultedfrom some apparent "failure" and setback
Example: The negativeresultsof theMichelson Morleyexperimer,t resulted
in the Theoryof Relativity, E = MC z etc,
The spaceexpBorationinitiative,some times called
"The Bush Push", will presentus with unparalleled
challengesand it will undoubtedly lead to even
greaterdevelopmentsand discoveries
Go For P!
46
VJW2N 2M2CA
HISTORICSCIENTIFICMILESTONES
Q 1905: E = I_C2
Q 1938/39: Uranium Nucleus Split/Einstein writes to FDR
Q 1945: Alamogordo- Hiroshima - Nagasaki (40 yea_s later)
• Note__:- Pressing need (WWlI)
- Manhattan Project, $$$, etc.
Q 1955:- Antiproton is discovered
- Antimatter becomes fact
Q 1984:- Trapping and storage of antiprotons achieved
Q 1995: ? ? ?
(40 years later)
SHOULD WE BE DOING SOMETHING?
250
1991012826-250
-!
1
FAMOUS PRONOUNCEMENTS
Q "Heavier than air flying machines are impossible"
Lord Kelvin, President, Royal Society, 1895
Q "Everything that can be invented has already been
invented"
Charles H. Duell, Director of U.S. Patent Office, 1899
Q "There is no likelihood man can ever tap the power of
the atom"
Robert A. Millikan, Nobel Prize in Physics, 1923
"Who the hell wants to hear actors talk"
Harry M. Warner, Warner Bros. Pictures, 1927
48
251
I-- 11'I I ............... " ........ In i i i i i u , --
1991012826-251


The 21st century propulsion

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