. .

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

1

'.

in e supp

. .

The batteri es allow support orderly-

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The ov raIl

TAB

TOT ... IA

II

II

111-1

111·2

TO

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2

2

2*

6

c u ti

condition arth.

l C

2

2

2*

6

..

CY

1lJIt 0

350

350' 300

350' 300

350

350

enerqy s Gas canister . -s cells and

SC1UutG£: e/2, C , /2, 2C CI ,C/2, I, C : cn, c C/4, C/2 : cn, C CI , cn

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ion

a a

for

:

Desiqn Consider io.

The two most control and cells must b since each t

p ct of th

I, for i ioning

t co 300·C.

th al -S

nd

at al

bus.

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.

3

I

emerg ncy

Pow r Co test high-po energy we h ve

:

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.

4

I

I

l2aL c:..tro ECU TCE PCU DCU w.llii To als

.. te:r r

~

3.OW 15 30 10 0

TIS

TABLB 2. BSTIXATED DBIlGY

3.6klll 1.6 2.0 1.1 }J 11.6

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.

S

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20 40 60 80 100

MISSION TIME, hours

GAS CANISTER (Ag-Zn 8ATnAlES)

400

350

300

250

200

\ 150

100 120

Figure 2. CBLL COIUlD1T TID LIn - TB8T I

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ORJGINAL PAGE • C'6. POOR QUAU1y

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Chargel Discharg Controller

Passive Load

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Cells

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C4 L ___ __ _

Exper1ment Module

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