Information on microwave beam power is given in viewgraph form. Information is given on orbit transfer proulsion applications, costs of delivering 100 kWe of usable power, and costs of delivering a 1 kg payload into orbit

Faymon, Karl A.

English

NASA Technical Reports Server

N 9 0" 10 16 5., _I_'5- :_:_
LEO TO&EO AN_PRETURN TRANSPOR T v ,
MICROWAVE BEAM POWER
KARL FAYMON
NASA LEWIS RESEARCH CENTER
"' " t3 j
397
https://ntrs.nasa.gov/search.jsp?R=19900000849 2020-03-20T00:22:44+00:00Z
lEO TO6EORNa RETURN TRANSPORT
CHARACTERISTICS OF LOW THRUST PROPULSION
• ORBIT RAISING:
-REQUIRES INCREASED "/_V" OVER IMPULSIVE HOHMANN
TRANSFER BECAUSE OF THRUSTING THROUGH PLANETARY
"POTENTIAL WELL".
• PLANE CHANGE MANEUVERS DURING ASCENT
-NON-OPTIMAL PLANE CHANGE-INCREMENTAL PLANE
CHANGES MUST BE DONE INITIALLY AT HIGH ORBIT VELOCITIES
WHICH REQUIRE GREATER IMPULSE FOR A GIVENAO.
• LOW THRUST PROBABLY NOT ADEQUATE FOR ORBIT RENDEZVOUS.
VEHICLE NEEDS AN ORBITAL MANEUVERING SYSTEM FOR BOTH ORBIT
INSERTION AND DOCKING.
lEO TO 6EO RNa RETURN TRRNSPOR T
7D
U
G
-, S5
TO
:
f_
¢.5
4,0
10-4
LEO-TO.GEO ORBIT TRANSFER PROPULSION
(ONE WAY)
10 6
ETRLAUNCH 0.5_
0.26_
10": 10"' 10"_ 10°
THRUST.TO-WEIGHTRATIO
Dem-VmcMe_fwIow-mnmoeMalIrm_W
REFERENCE:P.W.GARRISON,J.F.$TUCKY,FUTURESPACECRAFTPROPULSION,JPL,PASADENA,CA
JETPROPULSION,O.4, VOL.8,1987.
398
lEO TO 6EO 4Na RETURN TR/INSPOR T
ASSUMPTIONS:
• POWER BEAMED TO VEHICLE
-TERRESTRIAL LOCATION
-ORBITING POWER STATION
ELECTRIC PROPULSION VEHICLE
-90,000 KG MAX. WEIGHT IN LEO
-10,000 KW RECTENNA' 50,000 SQUARE METERS AREA
-TOTAL THRUST AVAILABLE 370 NEWTONS
* 1000 30 CM ION THRUSTERS
* XENON PROPELLANT
LAUNCH TO LEO RENDEZVOUS FROM KSC
o
-28.5 PARKING ORBIT INCLINATION
-300 KM ORBIT ALTITUDE
-PAYLOAD RETURN GEO TO LEO - 25% OF MAXIMUM PAYLOAD
RIU_ PGNRR &PPLZC&TZORSz LKO TO 010 &liD RRTO]N TIL_ISPORT
Iteferencm/Bamnllno: Brown, We. C., "LZO to OIO Transportation System Combining Zlectrlc Propulmlon Wlth Beamed MicroNeve
Power Fron _rth"0 28th Ooddnrd 14emorlel Symposlun, Vimlor_ of Tomorrow: A Focua on Rational
Trenaportutlon Zemuem; Volume 59, Science end Technology Series,
Amerlcan Astronautlcel Society Publication.
Jhtsollne Vnhlcle/Nlnnion Revlmed Vohlcle/Nloslon - X Revlm_t Vehlcle/Nlmnlon - XX
Total 1488o In _0-($00 EM) 90,000 kg.
Propellentc 14,000
Amcent 9,900
Return 4,100
Thrnatere 10,O00
Rscte_ 10,000
Structure end PMAD 10.O00
Loaded veh. Nt. (lemm P/L) 44.000 F_.
Payload (SIS) J 4_.000 Fa.l
Total Name In LKO-(500 134) 90,000 Kg.
Propellants 17,000
Amcent 11,000
Return S,O00
Thrusters 10,o00
Rectenns 10,000
Recterma Structurm: (1) 5,000
Structure end PNAD lO,O00
Orb. Maneuver. Symt.: (2)
Propulsion and t_ge 1,oo0
Propellants 13000
Loaded Veh. Mr. (lame P/L) SS,0OO Xg.
Payload (27K) _4,000 raJ
Total Name In LRO-($OO RN) 90,000 Re.
Prop@llmltm 19,000
_cent 12,000
Return 7,000
Yhrusterm IO,O00
Rectenna 500
Rectnnna Structure: (1) 200
Structure and PM&D lO,OOO
Orb. Maneuver. Syet.: (3)
Propulmlon and t_ge SOS
Propellants 2.0oo
Loaded Veh. Mr. (loon P/L) 42,800 Re.
Payload (85_)
........................................ | ........................................ s ........................................
Rearm ; Notes; Notes;
ThrusterS; Zop m 4500 sac.
I_/uatorlel amcent from $00 r. altitude;
Delta V (one amy} to GRO - 4800 a/:.
Single mlcromave bean tranemleelon frou
terrestrial equatorial station.
No payload return to LEO.
Microwave bean frequency: 2.45 Ghz.
(1): Rcctenna weight st 0.2 Eg/n=
Is Interpreted nnwelght only of
rectonna blanket. Additional
structure 18 requlred to ensure
adequate seperatlon of rectenna
modes and vnhlcls structural end
control nodes.
Thrusters; l|p - IS00 eec.
Launch azimuth 28.5 dee. (300 rm);
Delta V (one way) to SKO - 6100 m/m.
Single microwave beam transmission
from terremtrlel equatorial station
Orbital maneuvering system rulers
LEO orbit trna 300 r_ to 1000 Ka
prior to start of bean pomsr ph_0e.
Thln la required for equatorial
power etatlon to "see" vehlcle.
255 of nsxlmun payload returned to
LEO.
Nlcrotmve beam frequency: 2.48 Ghz.
(_): Orbital maneuvering system J!
req_lrud for rnn4evona at
ZJlO and OEO.
Space shuttle m_stem with
sO0 m/s delta V total
capability Is assumed;
lop o 513 seconds,
Propellants; NIO4-1eU4,
Thr_Btern; Inp m 4800 gec.
Launch anlmuth 28,5 dngo (300 _Ja);
Delta V (one may) to GSO - $100 m/n.
Single mlcroNave beam tranamlsmlon
from orbltlng power station In 28.8
degree orbit et 300 Ca. altitude.
25_ ot naxlmlun payload ret_rr_d to
LEO.
Microwave lena frequency: 100 Ohz.
(S): Orbital ss,eovorl_ system Im
required tar rondosvona at LEO
and OZO, Requirements are Icon
then CARE I slncc SEO lnJectlon
point can nlways be =seen" by
orbiting power station.
Space shuttle system is also
neo_wd,
399
BIUIIPOir_IiL*FLICATIOIg: LIOTOGEOIIIDIUETUIUITILUISFOIn"
_41torel_:olBeceline: Broom, _. Co,'LKO to GKO Transportation 8ymten Combining Electric Proimlalon With Beamed NlcroNave
Power From Earth', 28th Godd&x_l Namrlel Sylpoalmm0 VlalonB of Tooorrow: & rocul on National
Transportation Zcmuoo; Vollule 69, 3ctance and Technology Series,
IUm_lca_ AatromLuticll Society L_bllcetlon.
Revlmed Vablclo/Nlmolon - ZlZ
Total Iqaes In LEO-($O0 Ir_) 90,00o r4.
Propollanto 12,0OQ
Aacont 12,000
Return .....
Thruatora 10,000
Eoctonna 600
Eecteonal Structure: (1) 400
Structure and iq4AD 10,000
Orb. 14anouver. Syst.: (2)
Proi_llmlon end tankage 1,000
Propellants 3,200
Beet ehlald I,QOQ
Loaded Voh. We. (lore P/L) 37,100 I[g.
Payload (_9_) I _2.900 Ea.I
WateR:
Thrusters; Icp- 4800 aac.
Launch azimuth 28.0 dog. ($00 IUn);
Delta V (one tmy) to GEQ - 6100 m/o.
Single microwave beam tranmmloaJon frcl
orbiting ILX_wor etatlon In 20.6 degree
orblt at 300 Xn, sltltu_a.
Aerobraking reentry on return to 300 rdm.
LEO rondazvoua.
25_ of mutlmmpayload returned to LEO.
Nlcrm_va bemm treq_oncy: 100 GlUl.
Ch_Ically PropellKl Vehicle
Total me In LEO-($00 Ea) 90,000 Kg.
Propellemta 70,OO0
Agcont 52,000
Eeturn 17,500
Orb. I_m. 600
Structure and Oils 10.000
_4_ Vmh. Nt. (loom P/L) 80,000 ICg.
Payload (11_9
..........................................
Rotoa:
Launch azimuth 28.6 dog. (300) Km.
Hohaana traoater olllpoo.
Delta V (one _y) 4.2 Ir_/aoc. wLth
plane change at apogee.
Advanced R2-02 propuleloo eyotoa.
ZOp = 600 oecotlda,
251 of smine.s payload returned to tJO.
(I): Additional structure Is (2): Orbital maneuvering
requlrod to protect roctahrut ayatu w$11 inject
durlng aerobrmklng reentry lnto Rohuann transfer
and LEO rendezvous, ellipse tar LZO reentry
_d LEO rondozvoos.
lEO TO GEORNa RETURN TRRNSPOR T
FIGURE OF MERIT COMPARISION OF MISSION VERSIONS
• FIGURE-OF-MERIT:
PAYLOAD MASS/SUPPORT MASS DELIVERED TO LEO
• SUPPORT MASS DELIVERED TO LEO
-PROPELLANTS FOR LEO TO GEO AND RETURN
-PROPELLANTS FOR ORBITAL MANEUVERING SYSTEM
-SPECIAL TRANSFER VEHICLE REFURBISHMENT HARDWARE
-TRANSFER VEHICLE REPAIR AND MAINTENANCE HARDWARE
-PRORATED (150 MISSIONS - 30 YR LIFE) POWER STATION MASS
-PRORATED OPERATIONS SUPPORT MASS IN LEO
• THIS ISNOT A TRUE "COST" FIGURE-OF-MERIT: THESE ENTITLES HAVE
A VARYING "COST OF DELIVERY" TO LEO.
-CAPTIAL COST OF SUPPORT ENTITIES/FUNCTIONS IS NOT
ACCOUNTED FOR.
4OO
lEO TO 6EO RETURN TRANSPOR T
ORBITING POWER STATION - MISSION SUPPORT ASSUMPTIONS
• 50,000 kW REQUIRED: (20% END TO END EFFICIENCY)
• 100 W/kg FOR NUCLEAR POWER SYSTEM (UNMANNED STATION)
• STATION IS MULTIPLE USE - PROVIDES OTHER FUNCTIONS
- 250,000 kg CHARGEABLE TO ORBIT RAISING FUNCTION
• 30 YR LIFETIME: 5 LAUNCHES/YR, - 150 TOTAL LAUNCHES
POWER SYSTEM MASS:
STATION MASS - CHARGEABLE
OPERATIONS & MAINT. (30 YRS)
TOTAL MASS OF ORBITING
STATION CHARGEABLE TO
ORBIT RAISING FUNCTION
STATION CHARGEABLE MASS/MISSION
500,000
250,000
300,000
kg
1,050,00 kg
7,000 kg
BEAM POWER APPLICATIONS; LEO TO GEO AND RETURN TRANSPORT
MISSION VERSION COMPARISIONS: Support mass/payload delivered to LEO to support a mission.
Mission Version
Propellents/Misslon
Special Matnt. Items/Miss.
Total Mission Support;
Mass delivered to LEO
For D;rect Miss. Support.
I.
30,000 kg.
30,000 kg.
II.
21,000 kg.
21,000 kg.
III.
15,200 kg.
1,000
16,200 kg.
IV.
70,000 kg.
70,000 kg.
Prorated Op'e Support: 5,000 10,000 10,000 5,000
.Mass/Misslon.
PAYLOAD 24,000 kg. 47,500 kg. 52,900 kg. I0,000 kg.
PL/DIr.Sup. Mess, (kg/kg) .686 kg/kg 1.532 kg/kg 1.941 kg/kg .1334 kg/kg
Pow. Star. Sup. Mass/Miss. ? 7,000 kg. 7,000 kg. 7,000 kg.
Veh. Repair & Malnt. Sup. 1,000 kg. 1,000 kg. 1,000 kg. 1,000 kg.
[.667 ka/ka _ [1.21 ka/ka I 11.50 ka/ka [ [.12o ka/ka [
_ZLZVmRSDPA,YLOADMASS.k_g
TOTAL SUPPORT MASS kg
401
lEO TO GEO 4ND RETURN TR/INSPOR T
SUMMARY
• BEAM POWER SHOWS ADVANTAGES IN REDUCED MASS DELIVERED
TO LEO TO SUPPORT MISSION
-ARE TECHNOLOGY ASSUMPTIONS VALID?
-FURTHER WORK NEEDS TO TRANSLATE MISSION COMPARISONS TO
"TRUE DOLLARS" PER kg OF PAYLOAD
• IF ASSUMPTIONS HAVE "ANY" VALIDITY-BEAM POWER ORBIT RAISING
FOR LEO-TO-GEO AND RETURN TRANSPORT HAS SIGNIFICANT POTENTIAL
LAUNCH
COST
s3
kO
1988 COSTOF DELIVERING1 kg PAYLOADTO ORBIT
(ADVANCEDLAUNCHSYSTEMNOT INCLUDED)
100
10
-- 4,
. E$
+ .v,.mous.
_, STi+-CENTAURG'
.//_/llllll'-'_'" COMMERCIALAUNCHSERVICES
0 TITANIII
_, ATLAS-CENTAUR
z
o ° 8 =
.iCLU
"-I W • •i
I i i I i I i i I i
0.1 1 10 100 1000 10,000 100,000
DISTANCEFROM EARTH (1000% n.m. )
402
COSTOF DELIVERING100 kWe OF USABLEPOWER
lo8
TRANSPORTATION
COST,
MILLION DOLLARS
104
102
10
LEO GEO MOON
1 10 100 1,000 10,000
DISTANCEFROM EARTH, lO00's n.m.
MARS
100o000
(d
Z(
0
..J
)-
G.
27K-
20K-
28K-
24K -
MICROWAVE BEAM POWER APPLICATIONS
ip EO TO GEO AND RETURN TRANSPORT VEHICLE |
AYLOAD
i I I I
3600 4000 4600 6000
SPECIFIC IMPULSE: SEC.
403
SPACE PROPULSION APPLICATIONS--DISCUSSION SUMMARY
by Ja H. Lee
This miniworkshop dealt with both microwave LEO _ GEO propulsion and
laser LEO _ low lunar orbit propulsion. Laser propulsion was compared
with chemical and nuclear reference propulsion missions already estab-
lished by the Pathfinder program. A difficulty encountered immediately
was that the reference missions had two separate scenarios: chemical
propulsion for transportation of men and nuclear propulsion for
freight-only missions to lunar base and then to Mars.
The laser propulsion option did not closely follow these two separate
missions but took an intermediate size to accomplish the lunar mission
by a series of repetitive trips to the moon. However, this approach
left the comparison indirect; therefore, the conclusions that were
favorable for the laser option were criticized for being ambiguous, at
best, by the session chairperson.
The microwave option presented was for LEO-to-GEO propulsion only. The
GEO to the moon base was not addressed, and a study of different
schemes of propulsion for such long distance beyond GEO has to be made.
Perhaps the microwave option is entirely out of the question for a
distance >5,000 Km, and its application may be limited to near-Earth
missions due to the large receiver size.
Placing the nuclear reactor in near-Earth orbit below GEO is obviously
a sensitive issue related to the radiation safety of the earth. There-
fore, the solar-driven laser propulsion then becomes a more desirable
option. However, this issue is not confined to technical issues but
depends upon the national and international policies on space nuclear
power. Future studies may find suitable multi-missions that the space
laser station can accommodate for its cost-effective operation. The
duty cycle of the laser station for LEO-LLO propulsion is extremely
low, and the high capital invested in the laser station cannot be
justified by a single laser propulsion mission.
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Microwave beam power

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