This study analyzes certain selected topics in rival dc and high frequency ac electric power systems for a Space Station. The interaction between the Space Station and the plasma environment is analyzed, leading to a limit on the voltage for the solar array and a potential problem with resonance coupling at high frequencies. Certain problems are pointed out in the concept of a rotary transformer, and further development work is indicated in connection with dc circuit switching, special design of a transmission conductor for the ac system, and electric motors. The question of electric shock hazards, particularly at high frequency, is also explored. and a problem with reduced skin resistance and therefore increased hazard with high frequency ac is pointed out. The study concludes with a comparison of the main advantages and disadvantages of the two rival systems, and it is suggested that the choice between the two should be made after further studies and development work are completed

Hanania, J. I.

English

NASA Technical Reports Server

%\ N86-
A STUDY OF SOME FEATURES OF AC _ND DC
_' E[_21_IC POWER SYSTemS FOR A SPACE STATION
Jack I. Hanania, Ph.D.
Professor of Electrical Engineering
American University of Beirut
Beirut, Lebanon
" ABSTRACT
This study analyzes certain selected topics in rival DC and high frequency
, AC electric power systems for a Space Staticn. The topics are c_hosen either
because they a£e potential pzoblem areas or becmuse t]_ere seems to De the need
"_ for further study and development work.
The interaction between the Space Station and the plasma environment is
analyzed, lead_: _ a limit on the voltage of the solar array &nd a potential
problem with ....or. _-; coupling at high frequencies. Certain problems are
!
; pointed out in the conoept of a rotary transformer, and further development
_rk is indicated in connection with DC circuit switching, special design _f a
tran_niss1_n conductor for the AC system, and electric motors. The question,
of electric shock hazards, partzcularly at high frequency, is also explored, ",-.. i
and a problem wieh reduced skin resistance and therefore increased hazard with
a
high frequency AC is pointed out.
The study concludes with a cc_rison of the maih advantages and
disadvantages of the two rival syste.msr and it is suggested that the choice
_et_een the two should be made after further studies and development worP are
completed.
Center Research Advisor: William A. Chandler
i
k _
-!s: 8-1
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1986004609-076
https://ntrs.nasa.gov/search.jsp?R=19860004616 2020-03-20T16:33:48+00:00Z
RINTRODUCTION
- The design of the electric power system for a Space Station in low earth
orbit has received cor.siderable attention over many years. A number of
• studies (I-6) have been carried out based upon different alternative systems,
. some primarily DC, some primarily AC, and sczre a hybrid of the two, but it was ,
clear frcm the start t_hat the old 28 volt DC system used in previous space
missions would no longer De adequate for the Space Station powers envisaged, _
while the familial 60 Hz and 400 Hz AC systems _ould lead to excessive weight
• of electromagnetic equipment.
--i The choice of system tl_erefc_ essentially rests between a relatively high
voltage DC and a r_atively high voltage, high frequency AC, with same
• variations based upon these two. The voltages are referred to as relatively ;
• high since there are factors that tend to limit these voltages to a few _i
hundred volts, as will be shown below. Too low a voltage, however, would lead i
to excessi._ tran._ni "ion conductor size and losses. The optimum voltage
level, a_ _el _ as optimum frequency if AC, will have to be determined subject
_ to sc_e constraints, in view of the effect that these factors have on the _
-iI•
mR overall station weight and cost. I
A study of the two rival systems shows that they are both essentially
feasible, sub]ect to some constraints and problems which are discussed below.
There are strengths anu weaknesses in )oth systems; and a good case can be
_ made for one or the other. No attempt will be made _o choose between the two
• systems. However, certain specific topics are selected for study, either
. because they seem to be potentlal problem creas in one system or the other, or
because there may be inadequate data or insufficient past development work.
1986004609-077
THEORY AND RESULTS
Pla-__naInteractions
The voltage of the solar array is limited by the level of discharge from
the array to the s:_rrounding plasma and the resulting power lots (7'8). This
discharge is a function of the plasma density, which depends upon the altitude
" , of the Spaoe Station. The optimua station altitude, taking into account
correction for aerodynamic drag and the launching of resupply missions from
_ earth, is in the region of 400 km (215 NMi). Unfortunately, this is an
_ altitude at which plasma density is close to a peak (8), Figure i. At 400 _n,
the plasma density is of the order of Ix106/(ml3, and the voltage breakdown
- threshold, Figure 2, is roughly 400 volts. The positive/negative solar array
potentials are not symmetrical with respect to the surrounding pla_na because
of the ease of collection of electrons, resulting in approximately +20V/-380V
• potential distribution for a 400-volt array. Other factors to be considered
are: the additional ionized material introduced through the action of the ion
thrusters, the sharp rise in array voltage as the array emerges at the end of
the eclipse period into sunlight, and the apparent ineffectiveness of
attempting to insulate exposed areas of the array in order to operate at
q
higher voltages. Pending additional plasma data in low earth orbit, it would
be prudent to it the solar array voltage to between 250V and 275V or below.
There is a possibility of resonance between the AC transmission syst_
frequency, if an AC system is used, and some natural plasma frequencies (9),
particularly the ion plasma frequency _i and the lower hybrid frequency _LH"
These are given by:
wi _ Q i----f- WLn = leM----f=.
_' 8-:3
198G004G09-078
vi
, where Q Js ion charge, Mi ion mass, Ni ion density, e electron charge, Me Ji
{
electron mass and B the earth's magnetic field. Estimates of _i and _LH have
i been made by General Dynamics (3) for a range of altitudes around low earthi
!
orbit, giving coi as varying from 23 to 74 kHz at 300 km, and from 7 to 43 kHz
at 600 kin, and _LH varying from 5 to 10 kHz over the range 300 to 600 km. If
resonance coupling were to take plaoe unchecked, large power losses would
result. This points to the need for avoiding parallel c_nductors with an AC
system and for proper shieldirz/ of electra, agnetic equipment. Meanwhile, more
work should be done to verify the plasma density data presently available and
then to recompute the pla_ma frequencies. f
" Rotary Transformer
As part of an AC system, a rotary transforme.r has been proposed to provide
power transfer electr(magneticall F from the solar array side to the rest of _'
the Space Station, thus avoiding the need for sliding contacts. A General
: Electric (I0'II) design uses four 25-kW modules with a ferrite core and a 0.01" .
airgap, w{th a frequency of 20 kHz and a flux density of 0.25 T. The airgap
leads to questions about leakage inductance, and the _ctness of the
transformer achieved through the use of high frequency makes heat dissipation
more difficult. Unless proper dissipation is achieved, winding failures could
_ i_
occur leading to a total shut down of power to the Space Station, unless
- %
redundancy is introduced by usilg more than one transforme_. Because of the I
_ed for an electrical link b_tween the solar array and enerc/] storage i
equipment (fuel cells or batteries), the use of the rotary transformer gives
t_ options: either energy storage is on the station side of the rotary joint
which needs additional conversion equipment, or it is on the array side,
adding to the mass of the array and preventing a decentralized storage and
(x)nversion system.
, |
•:i 8-4
9 :
_p
1986004609-079
Circuit Switching%
Although AC circuit interruption has always been easier to achie,e than I_
becaus_ of the availability of current zeros, recent developments (I2'13'I4)
with solid state devices are making DC circuit interruption easier than it has
been. The following techniques can be.used:
, (i) GIX)s (gate turn-off thyristors) can switch a circuit very rapidly,
from 2 to I0 microseconds. Units have been developed and tested up to 65A,
800V, and GTOs with substantially higher ratings are presently available.
t
(ii) Power MOSFETs have been tested in units up to 100A, 150V. Because of _.
)
current rating limits, parallel oDe.ration of MOSFETs is needed, unlike the
g
(iii) GTO/SCR systems are used with the GID driving an SCR bridqe circuit, I_
either by controlling the on/off function of the SCRs or by diverting current
° array from the SCRs. This eliminates bulky conmutation circuits from the {
usual SCR system.
Although there is an obvious need for further development work and there are ]
some problems to be resolved, it is expected that M_FETs will replace SCR
systems up to 30 to 40 kW, and GTOs or hybrid GTO systems will take over at
higher power levels. _"-I_
%
Transmission line Parameters
Q
With a 1)2 system, designing a transmission line conductor and cxlr_ting
line parameters present no problem. With an AC system at high frequency,
several points shculd be considered. Skin effect is pr_inent, leading to a
thi:_ hollow tube construction. Reactive voltage drop can be very high unless
a coaxial conductor design is used. This can be seen in Figure 3 and Figure 4
which are taken from the work of Renz (8) and his associates. The computation
• _ of line parameters at high frequency and with unsymmetrical conductor sections
• ¢
_: 8-5 "
I,
1986004609-080
Jr
needs fur%her study and experimental verification.
Electric Motors
The traditional DC motor with commutator and brushgear cannot be used
because of the plasma environment, and the "brushless DC motor" is in fact an
AC motor supplied through a DC/AC converter. With a high frequency AC system,
frequency conversion will be needed to avoid excessivel_ high motor speeds. ,
The choice is between the 3-phase synchronous samarium cobalt permanent magnet
motor and the 3-phase squirrel-cage induction motor. The latter has the
advantages of simplicity, ruggedness and greater long-term reliability. The
: compactness of the high frequency motor results in the need for proper heat _,
• dissipation, since core losses rise substantially with frequency. Additional
rotor losses arise with non-uniform rotating magnetic fields (15)
Electric Shock Hazards
: In view of the widely varying body resistance, current rather than voltage !
is used as a measure of electric shock hazard. The let-go current, which is _;
the level at which a person just fails to release an electrode, is a danger
threshold. With such a current, prolorged contact with the electrode can lead
to respiratory difficulties and to skin changes that greatly reduce skin
resistance thereby allowing larger currents to flow, With these higher _"
currents, ventricular fibrillation can set in. Table 1(16) gives typical . I
figures for DC, 60 Hz and i0 kHz AC, and the median let-go currents at 60 Hz
are seen to be.about one-fifth those with DC. That is why 60 Hz AC is
sametimes said to be five times as dangerous as DC (17). Since skin resistance
is _t far the largest component of the overall body resistance, skin condition
greatly affects the severity of shocks. Voltage also affects skin resistance,
high voltage causing a sudden drop of resistance.
_ Table 1 also sh(_._ the let-go currents at I0 kHz to be about equal to
8-6
J
low
1986004609-081
those with DC. This is confirmed by the work of Daziel (18'19) and is shownl
in Figure 5, although the curves of Figure 5 go as far as 7 kHz only. But the
skin resistance at high frequency may present a problem. The curves of Figure
6 were taken from the work of Stacy (20) and Burns (21), and show dry skin
resistance at 10 to 20 kHz to be about one-hundredth that with DC. If this is
confirmed by other studies, it would mean that high frequency AC voltages
w_uld have to be much lower than DC voltages for the same degree of safety.
Other factors that add to the uncertainties (22) are the effect of the varying
t
time element, the wide range of let-go currents for the different percentiles,
and the extrapolation, for obvious reasons, of the ventricular fibrillation
_._, threshold currents fram the results of animal studies to humans. _
Comparison of AC and DC Systems
The main advantages of the AC system are:
_. i. The system is inherently flexible because of ease of voltage
transformat ions. !i
• i
2. Circuit switching and fault interruption are inherently easier because of
current zeros.
3. With a rotary transformer, sliding contact across the rotary joint is
eliminated.
!
The main disadvantages of the AC system are: 1.
I. More development work is needed for the rotary transformer and other
(x_nponents for high frequency operation.
2. More work is needed in the study and design of a suitable transmission
]ine.
3. There is the possibility of L_sonance coupling with plasma natural
frequencies.
4. There is a possibility of high electric shock hazard through reduced skin
c
8-7
1986004609-082
resistance.
5. There are potential problems with synchronizing separate AC buses if
: needed.
6. There is a need to balance single-phase loads -n the 3-phase system in
order to minimize the neutral current.
The main advantages of the DC system are:
I. The system is basically simpler and therefore potentially more reliable.
2. With the exception of circuit interruption, system design and ccmponents
are generally at a higher stage of development than with high frequency " ;
AC,
3. The DC.system is inherently free of potential problems peculiar to all
polyphase AC systems, such as reactive voltage drop, load balancing across
phases, synchronization.
f
The main disadvantages of the DC system are:
I. Absence of current zeros makes circuit interruption more difficult.
2. Circu{t switching techniues using GTOs or MOSFETs are still in an early
•_ stage of development.
3. DC systems are inflexible in matching a suitable voltage to the load.
: 4. A sliding contact, as in a slip ring, will be needed for the rotary joint, _,
!
or the roll-ring if that proves to be reliable. . !
j
}
CONCLUSIONS
,p
Some special features of AC and DC system designs have been studied, and
certain potential problems have been pointed out, leading to a comparison
b_t_en the principal strengths and weaknesses of the two systems.
: Interaction of the solar array with _he surrounding plasma sets an upper
-,'J 8-8
1986004609-083
% %
limit to the array voltage at between 250 and 275V or below. The use of a I0
to 20 kHz AC system could lead to resonance coupling with pla_na frequencies
under certain conditions. ':
Specific problems with the rotary transformer, DC circuit switching, AC
_ transmission line design and electric motors have been pointed out. The
possibility of a nigher electric shock hazard at high frequency was referred
to.
The cQ,parison between the AC and DC systems shows problem areas on both
sides, and it would be advisable to defer making a choice between the two
until further development work is done and some of those problems are
zesolved.
7
I
!
• I
I
I
_, _ 8-9
i
1986004609-084
LREFERENCES
I. Feiste, V. K., "Conceptual Design of Space Base Electrical Power System w,
NASA JSC, August 1969.
2. "Space Vehicle Electrical Power Processing Distribution and Control
Study", TRWReport, NASA-CR-123907, June 1972.
3. "Study of Power Management Technology for Orbital Multi-100 kWe
Applications", General Dynamics report, GDC-ASP80-015, NASA-CR-159834, ,
July 1980.
.4
4. *Study of Multi-Megawatt _%chnology Needs for Photovoltaic Space Power
Systems", General Dynamics report, GDC-ASP81-019, NASA-CR-165323, May
1981.
%
[ 5. "Solar Array Switching Power Management Technology for Space Power i
. Systems", TRWReport 37243, NASA-CR-167890, September 1982.
: 6. "Space Power Distribution System Technology", TRWReport 34579-6001, NASA
-_ Control NAS8-_3198, March 1983.
7. Stevens, N. J., Berkopec, F. D., Purvis, C. K., Grier, N. T., and Staskus,
J. V., "Investigation of High Voltage Spacecraft System Interactions with
Plasma Environments", AIAA Paper 78-672, April 1978. {
i
p
: 8. Renz, D. D., Finke, R. C., Stevens, N. J., Triner, J. E., _ Hansen, I.
G., "Design Considerations for Large Space Electric Power Systems", NASA
Technical Memorandum 83064, April 19A3. i
9. Chen, F. C., Introduction to Pla_na Physics, Plenum Publicatiens, 1974.
10. "Preliminary Design Development of 100 kW Rotary Power Transfer Device",
General Electric Report GE-81SDS4215, NASA-CR-1654 _, March 1981.
II. "Design Study of a High Power Rotary Trar_former", General Electric Report _
GE-82SDS4222, NASA-CR-168012, July 1982. %l
12. Billings, W. W. and Sundberg, G. R., "Solid State Remote Power Controllers [
for High Voltage DC Distribution Systems", National Aerospace and I
Electronics Conference, Dayton, Ohio, May 1977. I
13. "High Voltage DC Switchgear Development for Multi-kW Space Power Systems", "
Westinghouse Electric Corporation Report, _AED-81-05E, NASA-CR-165413.
14. "Kilovolt UC Solid State Remote Power Controller Development",
Westinghouse Electric Co_%Doration Report, WESDL-82-07E, NASA-CR-168041.
15. Nagarkatti, A. A., Mohammed, O. A., Demerdash_ N. A., "Special Losses in
Rotors of Electronically Cammutated Brushless DC Motors Induced by
Non-Uniformly Rotating Armature _Fs", Transactions, Power Apparatus &
Syst_ns, I01, _ . 12, December 1982. pages 4502-7.
P • \
_ 8-10
]986004609-085
_ __ _._i t+3It
F
16. "He dbook of Laboratory Safety", edited by N. V. Steere, Chemical Rubber
17. "Co_ndiu_n of Human Response to the Aerospace Environment", NASA-CR-1205,
: Volume I, Section 1-6.
18. Dalziel, C. F., Ogden, E., and Abbot, C. E., "Effect of Frequency on
i Let-Go Currents", AIEE Transactions, 62, 1943, pa_es 745-50.
19. Dalziel, C. F., "Electric Shack Hazard", IEEE Spectrum, February 1972,
; pages 41-50.
20. Stacy, R. W., Williams, D. T., Worden, R. E., eta]. Essentials of
Biological and Medical Physics, McGraw Hill, 1955.
21. Burns, R. C., "Study of Skin Impedance", Electronics, 23, April 1950,
pages 190-200.
22. Bridges, J., "Investigation on Low-Impedance Low-Voltage Shocks", IEEE
Transactions, Power Apparatus & Syst_ns, 100, No. 4, April 1981, pages '_
" 1529-37.
1{
!
) Ir
I
L
_i _ 8-11
m
9 ,"®
-- _._.,-._ _. .,
1986004609-086
be_t
b¢
|o
:_ ! 0 °
" so no3 _ lO _o6
,, AirilY, i'm
;..:. _,,
Figure I. Plasma Number Density as a Function of Altitude
in Equatorial Orbit (_fter Sevens, Reference 8) !
J
f,
2
I
L
_our_l_1 multS u ...... •
FIX-I Flight mul_
-_ ._!, I ! _. I ,,
I_m _s_. cm"3 =
4
Figure 2. Voltage Threshold for Discharges
(After Stevens, Reference 8)
: 8-12
1986004609-087
1986004609-088
; ORIGINAL F,:,:::5 ,.i
' OF POOR QUALITY
Table I
:" . Quantitative effe,:ls ofeleclric current on m=n.
¢ r' -" -- -" " '
l Mllhampcr¢$ ,• =,
:_, _)IIII_Cl _UffCnl A]IIIn,.IIIR! C'drrc?tl
-' ' ' IIL"UI IJ
3_, I_Henz Hertz ,i
" EITICl LMco V,0mcn Mcn "' _umcn M,:n _ V..mc_ :_
i
.. P;lqllhlKnt,lhOn Oft hand I 0.6 0.4 0..1 7 $ t
Pcl'ccp|lonIhrcsho]d.reed=an 5.2 :_.5 I.! 0.? |2 8
: ;hock- not pam(ul and muscular¢ontr,.; t
.. aot lost 9 6 IJ IJ I1' I I !
P,,llnfulshock- muscularcontrol loll I
: ' by %=,, 62 41 9 6 $$ 37 -
carefulshock-- I¢l-|O Ihrclhold. median "/6 5l 16 I0.S 7J $0 i'
Painful,rod,,¢,,¢rcshock--brcdlhm[_ i
d*l_cull, muscular_..orllrOlloll b_ gg'./_** 90 60 2.] I$ 94 5]
|'Olllbl¢ *¢nlri,:ul,_¢hbrdlJtlOn
Thrcc-*ccondshocks SO0 500 6"15 6?$
Short shucktqT ,n seconds) 116/,'T 116/_,
C|pacilor d,_hargrs _ $0"
e_'NIPl.t Ih tdll,tl_,l_l'ld*,
(Taken from Reference 16) _
_ 8-14
1986004609-089
eFigure 5. Sine Wave Let-Go Current for M_n Versus Frequency
(After Dalziel, Reference 18)
!,
m"
SSrllt
! loJ . \ ntcr*root,_s_r• --..7.'2
/$ANOtO S_r_
_J
! .! t
,_, _,103 _0#
Fcequency ;n Hz
Figure 6. An Example of the Variation of Skin Impeda..,= with Frequency J
and Condition of Electrode-Skin Contact
(After Stacy and Burrs, Refecence I_)
8-15
]986004609-090


A study of some features of ac and dc electric power systems for a space station

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