sift; -~y carl r. ha1b c , rebecca r
TRANSCRIPT
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SODllJM-SULFUR _ ..... 'AJAJ
Sift; -~y )S/":; 18 - j 1'\ . ~ \) IntrocSuct 0
> A Na-S cell
Carl R. Ha1b c , Rebecca R.
Spac 825
Palo
Shuttle f1igh hich individua cell. Th performance as such. condi tions which t h I 5-day flight. Th d of microgravity by co p ri on with gro t t control ce1 s experi encing dentical t est conditions but with gravity. Specifically, li itations of transport dynamics and associated cell perf ormance charact ristics should be revealed.
Experiment Descrip
/ The Na-S Cell Technology Flight Exp ri . separate experim nt d iqned to d t in
characteristics, d t il d 1 ctrod kin distributions. Th xp r nt, ar controll ed by an autono ou Exp ri n Subordinate controll r includ Po e Thermal Control E1 ctronic (TCE) and (OCU). A total 0 6 a-S c 11 nclos ithin 2 th enclosures will be mount d 0 a HitchH k r-M structur within the Shuttle cargo bay, as indicated in Figure 1. The PCU, having high power dissipative loads, will also be mounted on a top pallet for improved heat rejection. The ECU, TCE and DCU will be
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The batteri es allow support orderly-
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enerqy s Gas canister . -s cells and
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2 a C Afte /2 C 1 • MAlF CHARGED Af ter til CNG , • 1IA.lf CHARGED After C/l DIS , a FULL DISCNG After C/2 DIS
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Desiqn Consider io.
The two most control and cells must b since each t
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t co 300·C.
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at al
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An outer module tructur (Fiqur 4) with in ulation i al d by gaskets t o form a t hird hermetic enclo ur. Each experiment module is anchored to th HH- M top pallet with a NASA-LeRC designed support frame attachment that permits elongation of the enclosure as it periodic l ly i heated and cooled, but hich constr ins transverse mo i on .
Thermal Desiqn . To ini ize he t 10 th nclosur I evacuated MLI (Multi-Lay r In ulation) i utiliz d on th larg area sidewall, nd h i gh quality fibrou insulation (Min-K 1301) is used on the nd . Thr or four larg lectrical conductor ar requi red per ncl o ur t o provid fl xibility in control of t t curr nts up to 80A. Pow r and i nstrument tion lead must be carefully s ized to i nimi z heat loss across the thermal gradient. Steady thermal loss f or the present design is projected at about SOW per enclosure, resulting in approximately 10 kWh of energy demand for thermal control.
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emerg ncy
Pow r Co test high-po energy we h ve
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r
1 ct d for curr nt ith th
o the
th 5-day Flight Exp ri nt, 32 Wh which ub tantially to individu 1 xp ri nt.
r control y t i about 12 k ,and 1 ctrical h at r to ov rcom th rm 1 10 e fro the two
hou ings i about 10 kWh. Th ubtotal of 22 kWh i within n rgy budg t, assuming th a-S xp ri ent i granted
half th normal HH-M energy (i n proportion t o i ts area usage) plus a request f or half the available supplemental HH-M energy. The maximum power level for these loads is well within allowable values.
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l2aL c:..tro ECU TCE PCU DCU w.llii To als
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3.OW 15 30 10 0
TIS
TABLB 2. BSTIXATED DBIlGY
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El tronfcs Electron c Electronics Electronics Electronfc
STS-BU
TEST I SOW 150W 150 ~ 340
4.5 4.9 2:1 9.9
Heatup , ntain TEST II 50 TiST III 100 Totals 140
Cel l a.a i,.. TEST I TEST II TEST II I Totals
320W 130 ~ 440
6. 3.3 Y 10.2
T~rature
Recharge - Cells
STS-BUS
AG- BATT On -third of th total en rgy i quir d to r charq th Na-S cell , and uch of thi occur t hiqh P ak pow r 1 v ls. Such peak power d ands if add d to th oth r continuou load would exce d HH- aximum power lev 1 and would con tr in th ti inq of t he individu 1 xp riment to avoid ov rlappinq th po er p ak • By incorporating th Ag-Zn primary battery source, the separate cell experi ents can be performed independently, and the overall energy r quir nt f alls within the budget for HH-M experiments. Kission Pl anning
Payload int qration and pr -1 unch t ting ar particul rly imple becaus the Na-S cells ar inactiv at ambient temperatur • Fol lowing orbit tabilization nd c 11 h tup , a space conditioni ng cyc l i includ d for all c 11 to di rupt t he gravity-induced r eact nt di tribution th twas carri d into space by the cells beinq frozen prior to launch.
Because of th hort S-day i sion and th ti cell , careful planning of te t sequence inc ary. Con inqency plan will b dev loped for alternate tests and for maximizing information should a shuttle emergency or experiment malfunction develop and require premature shutdown by the autonomous controller. Cells will be secured with all reactants frozen pri or to re-entry.
AckDo 1 dg8Jllen
We gratefully cknowledge the program support of Olga Gonz ezSanabria and the technical suggestions of Harold Leibecki of NASA Lewis Research Center during the preparation for this critical space experiment.
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MISSION TIME, hours
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ORJGINAL PAGE • C'6. POOR QUAU1y
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AgZn-Battery
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Chargel Discharg Controller
Passive Load
Switching NaS-Network Tes
Cells
J'iqure 5. POWBR COIITROL OIT CO)fCBPT
r -- ---- .., r - -- ----- - ----- .., r-~--_+~---------------1 1
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-=- AgZn2
T 1 Current LInear 1 FI I 1
K6---'\...r-ri-~5 2 I I I
-------- I L--_ ....
Gas Can1ster ~=::::::.~ PCU
CI I NaS..I...
C2
I C3 I I Nas..I..
C4 L ___ __ _
Exper1ment Module
J'iqure ,. .WITCBIBG nftOu CIRCUIT
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