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11. I I I I I ‘I I 1 ‘I ‘I ‘I I 1 I I I 1 I I ER47Sb MATERIALS MANUAL Fot Use With TRW Space Radidor-Codemser Design ond Performance &lysis Computer Progmms February 1966 TM EQUWMEHT UBORATORfES A DIVISION OF TRW INC. CLEVELAbJD. OHfO 44117 https://ntrs.nasa.gov/search.jsp?R=19660013060 2018-07-14T00:16:41+00:00Z
Transcript
Page 1: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

11. I I

I I I

‘I I 1

‘I

‘I ‘I I 1 I I I 1 I I

ER47Sb

MATERIALS MANUAL

Fot Use With TRW Space Radidor-Codemser Design ond

Performance &lysis Computer Progmms

February 1966

T M EQUWMEHT UBORATORfES A DIVISION OF T R W INC. CLEVELAbJD. OHfO 44117

https://ntrs.nasa.gov/search.jsp?R=19660013060 2018-07-14T00:16:41+00:00Z

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1. I I I I I 1 I I I I I I I I I I I I

1.

Text

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I I I I I I I I I I I I I I I I I I

TABI;E OF CONTENTS

Page No.

lWE3ODUCTION . 1

s l m 4 m Y . . . . . . . . . . . . . . . . . . . . . . . . . 1

I. TEXT

1.0 Power Systems Survey . . . . . . . . . . . . . . . 3

2.0 Thermo-Physical Properties of Working Fluids . . . 7

3.0 Construction Materials Properties . . . . . . . . . 8

4.0 Radiator Coatings . . . . . . . . . . . . . . . . . 17

5.0 Reconmendations . . . . . . . . . . . . . . . . . . 29

11. TABLES Table No.

Results of Power System Survey . . . . . . . . . . . . . 1

Properties of Organic Working Fluids

Thermo-Physical Properties of Working Fluids . . . . . . 3

Thenno-Physical Pruperties of Radiator Materials . . . . 4

Materials Compatibility With Working Fluids

Radiator Fin and Tube Material Compatibility . . . . . . 6

2 . . . . . . . . . .

. . . . . . . 5(a)-5(b)

Radiator Emittance Coatings . . . . . . . . . . . . . . . 7(a) -7 (g)

111. FIGURES Figure No.

Water Properties . . . . . . . . . . . . . . . . . . . . 1-10

Mercurypruperties . . . . . . . . . . . . . . . . . . . 11-18

Potassium Properties . . . . . . . . . . . . . . . . . . 19-28

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TABLE OF CONTENTS (continued)

111. FIGURES (continued) Figure No.

Rubidium Properties . . . . . . . . . . . . . . . . . . . 29-37

Organic Properties . . . . . . . . . . . . . . . . . . . 38-49

Radiator Materials Properties . . . . . . . . . . . . . . 50-58

Esnissivity Coating Test Results . . . . . . . . . . . . . 59

Effect of Coating Thickness . . . . . . . . . . . . . . . 60

IV. REFERENCES

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IIU!RODUC!FION

The purpose of t h i s manual is t o provide a caupact reference f o r the thermo- L--

physical properties rec@red i n the design of space radiator-condensers.

e f f o r t w a s performed as part of the Space Radistor-Condenser Design and Per-

This x ” _ _ - - _- .

formance computer m- un&r contract m g-UB4 with the NASA - Space- c r a f t Center. It is intended that this manual supplement these computer programs

by providing, i n one report, the fluid and construction materials pruperties

required as inputs.

SUMMARY

~ ~ E H T l l b o R A T o l w E s

1 I I I I I I I I I I i I I I I i

Section 1.0 presents the results of a power system survey undertaken t o assess - t he u t i l i za t ion of worirhg fluids and materials on actual and proposed space

e l ec t r i c parer systems emplaying direct condenser-radiators.

Section 2.0 contains data on f ive working fluids.

a survey of their current use in actual direct condensing systems or contemplated

future systems.

Their selection is based on

Section 3.0 contains the properties of candidate radiator materids.

other than those i n current o r proposed use have been included t o extend the

u s e m e s s of t h e ccmptlter prograin as bonding and joining technology advances.

Materials fabrication compatibility and working f lu id compatibility are indicated

t o a id i n the selection of suitable radiator-condenser materials f o r a given

application.

Materials

Section 4.0 presents the emittance coatings which wou ld be suitable f o r extended

service i n space-vacuum conditions. Solar and thermal absorptivity values are

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TRW EQUIPMENT LABORATORIES

included where available f r o m the literature.

with substrates, methods of application, and service temperature limitations are

tabulated to aid i n the proper coating selection for t h e intended application.

Coating bonding compatibility

Section 5.0 presents some of the areas which, upon searching the literature,

were found t o be i n need of further study.

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,I I I I 1 1 1 I 1 1 1 1 1 1 1 1 I I I

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1.0 POWER SYSTEM SURVEY

A survey of space e lec t r ica l power systems employing direct condenser-radiators

presently being investigated and those considered as primary or candidate systems

f o r spacecraft applications is suarmarized in Table 1. Only those systems which

have received serious dievelcpxmtal attention or extensive study were included.

Since t h e only sources ut i l ized in t h i s survey were exoteric company and

government reports, some systems may have inadvertently been overlooked. With

these q d i f i c a t i o n s , t he f lu ids selected are: mercury, potassium, water,

rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene.

1.1 Mercuq

During the last decade, mercury rose as the most prominent Rankine cycle working

f lu id for e lec t r i ca l generation space application.

reactor powered SNAP 2 and SNAP 8, and the solar powered Sunflower accelerated

mercury t o the foref’ront as a space system working fluid.

intended mission spelled the end of t h e SNAP 1 (SPUD) system.

or iginal ly space oriented, has been redirected t o a study-type system test

program due t o lack of specific application.

similar fate, being relegated t o a component development program as emphasis

shifted from high t o l o w output parer generation systems.

solar powered Sunflower system ha6 been bypassed f o r lack of a mission and waning

in te res t in solar powered mercury systems.

s t i l l remains 88 one of t h e more prominent working f lu ids f o r R a n k i n e cycle power

plants with outputs ranging from 3 t o 300 KW.

The S W 1 (SPUD), the thermal

The cancellation of the

The SNAP 2 system,

The S W 8 program suffered a

The highly successful

Regardless of these events, mercury

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Radiator materials in direct mercury radiator-condensers varied depending on

intended application.

stainless steel throughout.

considered:

tubes and copper fins.

of 347 stainless steel tubes and UOO-0 (non-structurel) aluminum fins.

the SNAP 8 di rec t radiator-condenser designs u t i l i zed Haynes Alloy No. 25 tubing

and aluminum fins.

The SNAP 1 (SPUD) radiator w a s fabricated from 316

Two types of SNAP 2 radiator-condensers w e r e

Hqynes Alloy No. 25 tubing and aluminum fins and 17.7 molybdenum

The Sunflower system used a radiator-condenser composed

One of

1.2 Potassium

Potassium found application 86 a working f l u i d i n the SPUR/SNAP 50 system which

has also been reduced t o component development. The use of potassium i s s t i l l

very at t ract ive for future space applications pending fast reactor revival and

t he avai labi l i ty of container materials suitable f o r 10,OOO hours or more

service at the higher temperatures seen in these systems. In 1965, T R W prepared

a potassium Rankine cycle test capsule t o evaluate the boiling and condensing

properties of potassium i n space. A failure of t he boost vehicle during launch

led t o an abrupt conclusion t o the experiment. Another test capsule i s being

b u i l t t o repeat the experiment, indicating a continuing interest i n potassium

as a cycle working fluid.

The radiator materids proposed for t h e SPUR/SNAP 50 direct condenser were 316

stainless steel tubing and 316 stainless steel clad copper f ins . The T R W heat

t ransfer test capsule radiator-condenser u t i l i zed 316 stainless steel tubing w i t h

copper f i n s brazed t o the tubing (88).

TRw EQUIPMENT LABORATORIES , I I I I 1 1

1 I 1 1 1 1 I I 1

a

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I I I

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-EQUIPWENT LABORATORIES

1 I I I I I I I I I I I I I I I I I

1 . 3 Water

A steam system w a s investigated u t i l i z ing the SmAp 8 reactor by ASTRA, Inc. (73).

The proposed systems utilized nuclear and solar heat sources.

were i n i t i a l l y considered to be aluminum (tube and f in s ) with beryllium as the

ut,biate inaterial.

studies in this e a .

Radiator-condensers

---.I. mT & &"her c q & e s hme q m s ~ r e d internally funded

1.4 Rubidium

The i n i t i a l working fluid of the ASTEC p r o m (Advanced Solar Turbo Electric

Concept) was rubidium. The program wa8 redirected before reaching the system stage.

A radiator-condenser test segnent (tubes and fins) was fabricated from Inconel.

B e r y l l i u m tubes and fins would have been the ultimate radiator-condenser materials.

Rubidium is not considered to be a lurely working f l u i d f o r the space applications

presently under investigation.

1.5 Organics

Interest i n organic f lu ids f o r space power agplications has developed ragidly i n

t h e last f i v e yesrs.

program f o r the Navy and Air Force fo r a 1.5 KY solar power plant using Dowtherm-A.

No details are available as to the mSterials being considered.

t h a t Dowtherm-A is the most favorable working f lu id f o r an isotope-heated system

as a pa r t of the Manned Mars Mission Study (75).

a contract t o build a system f o r a U t i - t u b e Orbital Rankine Experiment (77)

using Dowthem-A as t he working fluid.

be 347 stainless steel.

Sundstrand (74) i s currently involved i n a development

T R W has concluded

TRW has recently been awarded

Tubes and headers f o r t h i s system w i l l

Mns will be 5083 &luminum. Various Binary systems

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TRW EQUIPMENT LABORATORIES

proposed included ortho-xylene or ethylbenzene as t h e bottom cycle fluid.

Aluminum tubes and f i n s were proposed i n most cases.

A comparison of various organic working f lu ids and t h e i r properties is shown i n

Table 2.

as the most promising f o r space systems, based on favorable ccmbinations of t h e i r

v q o r pressure/temperature relationships, freezing point, corrosive nature, and

thermal s tabi l i ty .

From t h i s chart , ethylbenzene, ortho-xylene and Dowtherm-A were chosen

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I I I I I I I I I I I I I I 1 I I I I

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IRlkr E Q U I ~ W LAboRATiolwES

I I I I I I I I I I I I I I I I I I

2.0 ~ - P H ! l S S C A L FFtOFEEiTm OF WORWOG

!be therm-physical properties of eight prima,ry and candidate working f lu ids

have been prepared as a m c t i o n of te!xperature. These include ___I^ wate.e.-mex~ury, - cc_

rubidium, potassium and three organics (ortho-xylene, ethylbenzene and I)owthexm-A). -./- . ~ - - - e .--_._ , l _ .

The working ffuids, t he i r respective properties and a mfemi3e figiire inmiber for I -

- # .*- - _" "- - _.

each property are summarized in Table 3.

The properties compiled f o r each working f lu id are those necessary as inputs t o

the computer programs and are as follows: molecular w e i g h t , heat of vaporization,

specific heat, specific heat r a t i o , density, absolute viscosity, liquid-vapor

m a c e tension, t h e m conductivity and vapor pressure. These appear on

Hgures 1 through 49.

freezing point, c r i t i c a l temperature, c r i t i c a l pressure, specific heat r a t io and,

Single valued quantities are given for m o ~ e c d a r weight,

i n some cases, specific heat. A l l data is presented in the units required by the

design and performance analysis radiator cosnputer programs.

In most instances, the information is the result of the l a t e s t t e s t data avd lab le

in the literature, but in some cases, most notably rubidium, the curves represent

calculated values since no t e s t data could be found.

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TRW EQUIPMENT LABORATORIES I

3.0 CONSTRUCTION MMERULS PROPERTIES

3.1

Seven properties were selected and tabulated for each of the candidate radiator

materiaLs. These properties include density, tension moudules of e las t ic i ty ,

thermal conductivity, specific heat, themel expansion, yield strength ( .2$),

and melting temperature. Only the density, tension modulus of e la s t i c i ty and

thermal conductivity a r e required as inputs t o the computer program, but thermal

expansion was included t o assess fin/tube compatibility, yield strength and

melting temperature t o establish service limits, and specific heat t o facilitate

transient study. A cross-reference between each candidate material and the

respective property curves is given in Table 4 including figure number and the

reference numbers.

as a function of temperature in the referenced figures.

value is contained direct ly in Table 4.

temperature are found on Figures 50 through 58.

uni t s required by the design and performance analysis radiator computer programs.

Tube, Header and Fin Thermo-Physical Properties

Where important and available, t h e information is presented

Otherwise, a single

Materials properties as a f h c t i o n of

AU data i s presented i n t h e

Some of the properties listed vary widely depending on the form of the material,

i.e., sheet or bar, heat-treated or wheat-treated, etc. This is especially t rue

of the yield strength. In each case, the form most representative of t ha t usable

i n condenser-radiators w a s listed or, i n some cases, a range i f more than one

form i s applicable.

3.2 Materials Compatibility with Working Fluids

A literature search w a s conducted t o obtain materials/working f lu id compatibility

infonuation. The working f lu ids considered were those found t o be candidate

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1, I i I 1 l I i 1 I 1 I I I 1 I I I I

fluids for space systems as a result of the system survey (section LO), namely,

n~rcury, water, rubidium, p o t s s s i ~ l and selected organics.

considered included, but were not limited to, those candidate materies of

section 2.0.

The materials

Tables 5(a) and 5(b) are a sumarary of the informstion.

The temperatures on this table represent (a) the test temperature at vfi ich l i t t l e

or no corrosion (loss or gaAn i n weight) was detected, (b) acceptable corrosion

temperature limit e x t n ~ o l a t e d frau test data at lower temperatures, o r (c)

temperature limits based on tests of similar fluids.

duration is less than lo00 hours, more than 10,OOO hours, or i n same cases as

noted.

condenser operating temperature for that fluid is higher than the service tempera-

ture of the material or (3) the canbination of fluid and container materid is

i l logical.

In each case, the test

Where no data is presented either (1) none could be faund, (2) the normal

3.2.1 Water

The temperatures given i n Tables 5(a) and 5(b) are based on t h e results of both

s t a t i c and dynamic tests.

The static corrosion rates were determined as a byproduct of autoclave tests

conducted at temperatures below 500 F.

purposes as crevice corrosion andbearing combination studies i n connection with

water-cooled reactor systems.

0 The tests were perfonned f o r such

Dynamic testing was carried aut at temperatures between 500 and 6009 which i s

the normal operating range of water-cooled reactors.

t o 30 f p s .

Velocities ranged from 1/60

The dynamic corrosion rates of materials studies a t 500% is increased

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TR W EQUIPMENT LABORATORIES

between 5 and 20 t w e e when tested at 6009 (17).

The effects of water velocity on the corrosion rate of 300 series s ta inless

s t e e l are delineated i n reference (19).

solution velocity was established af'ter 400 test hours.

1 5 times tha t amount as velocit ies were t r ip led and quadrupled f o r t h e same

number of hours tested.

A weight loss of 10 mg/cm2 at 10 f't/sec

The rate increased 3 t o

Studies (18) on high purity water corrosion indicated tha t t h e use of water w i t h

a pH above 10 caused the corrosion rate of mild steel t o decrease with exposure

t i m e . The corrosion of aluminum and i ts allays above took the form of

serious intergranular attack.

temperature range t o about 60o0F (19).

condition) may not be feasible i n fuel c e l l radiators using hydrogen and €$O

mixtures.

Decreasing the pH t o 2 could extend t h e uperating

However, regulation of pH t o 2 (acidic

Aluminum alloys containing nickel, iron, titanium, si l icon, beryllium and zirconium

tend t o displace the cathodic reaction from the aluminum surface and make the

alloys less sensitive t o corrosion.

also found t o be beneficial.

The addition of hydrogen t o the water w a s

A considerable increase of corrosion i n flawing as against s t a t i c water w a s noted

by researchers (19) and increasing the r a t i o of area of aluminum exposed t o

volume of water was found t o reduce dynamic corrosion.

Beryllium and i t s alloys showed good resistance t o corrosion below 200'F (about

one mil penetration per year). Above t h i s temperature the corrosion rate increased

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~ I , EQUIWENT LABORATORIES

I rapidly and became more unpredictable (19).

Magnesium alloys had high corrosion rates (0.1 -/day) at 300% (19).

use should be restr ic ted below 150% for long duration operation.

Their

mamie eomsia i s%-tit~ies 011 cvmez-zickel ( T Q - ~ Q ) micat& %hat ~ Y W corrosion

rates could be maintained a t 200% with 30 i p s w a t e r velocity.

rate could be maintained by the addition of hydmgen into the water.

rates at 500% and 30 f p s without the presence of hydrogen increase about 200

t i m e s compared t o the 200% rate of 34 mg/in2-yr.

at 7 throughout the t e s t s (17).

rapidly with increasing water velocity and temperature.

was immediately available on the refractory metals.

A t 500% the same

Corrosion

The water pH was maintained

The corrosion rate of copper tubing increases

No w a t e r corrosion data

3.2.2 Mercury

The temperatures indicated i n Tables 5(a) and 5(b) axe a result of extensive

mercury materials compatibility work done at TRW (30,31,32).

and circulation loops operating between 700 and U00% provided the basis f o r

most corrosion temperature limitations.

on selected materials by NASA-Lewis.

have provided endurance tes t ing data f o r boiling systems i n the SNAP 8 temperature

Refluxing capsules

These tests were corroborated t o 130O0F

Studies at Brookhaven National Laboratory

range and higher (86).

3.2.3 Rubidium

Materials c q a t i b i l i t y data with rubidium include beryllium, cobalt alloys,

nickel alloys, some refractories, s ta inless steels and vanadium. Testing duration

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TRW EQUIPMENT LABORATORIES

has been i n the 1000 hour range.

resu l t of the nonaal condensing temperature range associated with rubidium cycles

( 1000-l~OO°F).

only those materials that can s t ructural ly withstand the temperature range.

Refluxing l iquid vapor capsules and some dynamic loop t es t ing provided the bulk

of information available i n the l i terature .

"he temperature range investigated is a d i rec t

Compatibility studies have generally been aimed at screening

3.2.4 Potassium

Refluxing capsules and dynamic loop tests of 1000 hours or less dominate the

current investigations and provide the basis f o r the corrosion temperature limits

shown i n Table 5.

velocity potassium at 4 in/sec indicated corrosion r a t e s of about 0.12 mils per

year (14).

Dynamic 5000 hours 316 stainless s t ee l loop tests with low

3.2.5 Hydrocarbons

3.2.5.1 Dowtherm-A

Corrosion data f o r Dowtherm i s limited. The f lu id i s not corrosive and does not

scale w i t h standard materials of construction. The materials containing temper-

atures i n Table 5 are considered t o be standard. The refractory metals show no

compatibility temperatures but probably are campatible t o the operating limits

of Dowtherm-A.

When contaminated with water, Dowtherm reacts t o form highly corrosive hydrocholoric

acid.

subject t o corrosion by the acid should be used with caution.

I n t h i s respect, where contamination wi th water is possible, materials

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3.2.5.2 Ortho-xylene and Ethylbenzene

Over lo00 hours of tes t ing indicated tha t 300 series stainless steel was not

attacked when suspended i n l imid ortho-xylene at 55OoF.

at 180% on 347 stainless steel, 406 stainless steel, 1010 carbon steel, pure

Low temperature tests

aiuminum, aiuminum alloys, kconel, ' J W m &!lay (Ti - 6Al. = 4V) md 9-e~ 25

showed no evidence of' attack (24). Capsule tes ts of 304 stainless steel and

1010 carbon steel at about 700% f o r almost lo00 hours indicated no effects on

either material (25).

and ethylbenzene are actual3.y f o r biphenyl and isoproplybiphenyl.

tut ion w a s made because of the similari ty i n t h e i r corrosion characteristics and

the ava i lab i l i ty of data.

The remainder of the corrosion data listed f o r ortho-xylene

This substi-

Extensive static corrosion tests (26) w e r e made with biphenyl at 500% f o r 4500

hours and 750%' f o r 4700 hours. W s t of the general material categories listed

on Tables 5(a) and 5(b) w e r e covered by the tests. Dynmic corrosion rates were

available f o r isoproplybiphenyl at veloci t ies frm 0 t o 27 f'ps. Corrosion rates

increased by a factor of 20 at 27 f p s Over s t a t i c corrosion rates f o r 300 series

stainless.

3.3 "ube and H e a d e r Material Meteoroid Protection Capability

Meteoroid col l is ion represents the greatest potent ia l hazard t o f l u i d radiators

i n space.

theories used t o predict amor thickness requiremen ts.

based on material properties (modules of e las t ic i ty , hardness and density) as

well as some evaluation of meteoroid flux.

by NASA-Lewis u t i l i ze s the modulus of e l a s t i c i ty and density of the armor.

D a t a from unmanned ear th orbit ing satellites has reinforced ear ly

Correlations are presently

The correlation currently advocated

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TRw EQUIPMENT LABORATORIES

This approach is used by TRW t o determine the meteoroid armor thickness i n t h e

radiator design programs.

The following expression is a form of t h a t result ing fram the work by Loeff'ler,

Lieblein, Clough of NASA-Lewis and Whipple, Cook and other6 at Hamard ( 8 4 ) :

where ta = armor thickness, inches

A = vulnerable area, ft2 (taken as the inside tube area)

P(o) = probability of no meteoroid penetrations

f = armor density, lb/in.

E = modulus of e l a s t i c i ty of armor, p s i

= mission t i m e , days

The properties of density ( p ) and modulus of e l a s t i c i ty (E) f o r all radiator

materials are referenced i n Table 4. h o r w e i g h t i s proportional t o the term

p 5/6 E - l / 3 ,

Recent hypervelocity impact investigations of advanced armor and/or fin materials

such as beryllium and pyrolytic graphite have indicated tha t these materials

exhibit br i t t le characteristics which make them unsuitable as space radiator

s t r u c t u r d members (115). In t h i s respect, t h e present approach advanced by

NASA t o determine meteoroid armor should be used with rest raint .

have t o be modified t o account for the very b r i t t l e radiator materials which

of fer very attractive, but p06Sibly erroneous, w e i g h t advantages over more

conventional materials such as aluminum and steel under the present method of

The theory w i l l

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m o r determination.

3.4 Compatibility of Radiator Fin Materials t o Tube Materials

Table 6 lists cambinations of possible space radiator tube and f i n materials.

These have been ccmpared fram the standpoint of bonding and joining techniques,

thermal expansion limitations and susceptibil i ty t o galvanic corrosion.

tube material. canbinations masked with a dash (-) indicate tha t the combination

is either not applicable, not feasible, o r no information is available on the

union .

The f i n

3.4.1 Bonding and Joining Techniques

The method(s) by which fin materials can be fastened t o tube materials is highly

dependent on the types of material involved and the radiator operating tempera-

ture.

manual. Bowever, the major techniques are delineated below.

A detailed discussion of each possible method is beyond the scope of this

1. Welding

a) hellarc

b) arc

c ) electron beam

2. Brszing

a) torch

b) f’urnace

3. Mechanical

a ) casting

b) clamping and crimping (interference joints)

c) pressure lamination

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fRw EQUIPMENT LABORATORIES

d) extrusions

4. chemical

Another important aspect of joining dissimilar fin-tube materials is the

consideration of thermal resistance (82, 83).

mechanical techniques have been employed.

w a l l and a f i n converts the mechanism of heat transmission from highly e f f ic ien t

conduction t o radiation.

t o f i n increases t h e condensing temperature.

"his i s especially important when

The presence of a gap between a tube

An increase i n t h i s thermal resistance from tube w a l l

3.4.2 Thermal Expansion Limitations

Large differences i n thermal expansion coefficients between tube and f i n radiator

materials subjected t o l u g e temperature variations require special attention.

The use of these combinations is normally not recommended from a pract ical or an

economic standpoint.

can be m a d e by building up layers of different thermal expansion materials, main-

taining the difference i n thermal expansion coefficients small between adjacent

layers.

of temperature exre compared i n Figures 57 and 58.

If a requirement f o r such combinations exis ts , t h e bond

Thermal. expansion coefficients f o r vmious radiator material as a f'unction

3.4.3 Galvanic Corrosion

Direct contact between dissimilar metals such as copper and aluminum or aluminum

and steel axe susceptible t o galvanic corrosion (35).

t o be one of these environments.

of radiators of these types without adequate protection should be avoided.

Galvanic corrosion norma,lly takes the form of severe pit t ing.

S a l t water is considered

Ekcessive exposure (usually during ground tes t ing)

- 16 -

,I 1 I I I I I I 1 1 I I 1 1 I I I I 1

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1 . I I I I I I I I I I I I I I C I I I

TRWEQUIPMENT LABORATORSES

4.0 RADIATOR COATINGS

Radiator coatings prwide protection f o r the substrate m e t a l from vacuum

conditions of space as w e l l as providing control of the thexmd. radiative and

absorptive properties of' t he surface. An effective radiator coating must have

a high Lnfra-red or YnernwL &%tame md, b the case ef' a Im teqeratxre

radiator, low solar absorptance. Coatings meeting these requirements have been

developed and, i n many cases, extensively tested under sjmulated vacuum

conditions of space.

A l i t e r a t u r e survey w a s conductedto determine the most effective coatings, their

applicable temperature range, the methods of application, t he substrates Wli-

cable, and the tes t ing duration. The results of this survey are shown i n Tables

7 ( 4 throw3h 7(g).

4.1 W t t a n c e

"he tabulation of t o t a l hemispherical emittance values i n Tables 7(a) through

7(g) includes only those coatings o r surfaces with values greater than -7 as

determined at test temperatures above 30O0F f o r a minimum of 20 hours in a

simulated space environmerrt.

The results of' extensive emittance coating studies by Pratt and Whitney Aircrm

(54) are reproduced in Figure 59.

Temperature.)

temperature s t a b i l i t y under vacuum conditions we shown.

program, temperatures w e r e measured on the netal substrates. "his eliminated the

need f o r temperature drop and opaqueness corrections and allows direct use of the

(Total Hemispherical Emittance versus

O n l y those coatings possessing high emittances and good high

In the above tes t ing

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TRW EQUIPMENT LABORATORIES t

emittances i n radiator design.

4.2 Absorptivity

There are two types of thermal radiati n i n space. The first is solar, e ther

di rec t or reflected f m planets (albedo), w i t h a wave length of 0.2 t o 3.0

microns. The second i s infra-red or thermal being emitted from planets and

other astronomical bodies wi th a wave length of 5 t o 50 microns.

wave length difference, almost all surfaces have difference absorptances t o the

two types of radiation.

Due t o t h i s

Thermal absorptance i s taken as being equal t o thermal emittance and is usually

high as a result of a desire f o r a high t h e n d . emittance.

on the other hand, is somewhat independent of thermal emittance and a balance

between high thermal emittance and low solar absorptance can be obtained and is

desirable, especially fo r a low temperature radiator.

solar absorptivity is a f'unction of the temperature leve l of the radiator and the

intensi ty of t h e incident solar energy. Solar absorptivity values have been

determined i n the laboratory f o r various structural materials and coatings.

These have been included as par t of Tables 7(a) through 7(g).

Solar absorptance,

The importance of the

4.3 Comparison Parameter ( OC s/ H)

The r a t i o of solar absorptivity t o t o t a l hemispherical emittance ( 4 s/ H) is

an important parameter f o r comparing the performance characterist ics of various

radiator materials.

Since the ideal is unattainable i n real i ty , materiaJ.8 with 6; s/ E than . 3 are considered acceptable (66).

The ideal radiator surface would have an 6 s/ c H = 0.

r a t io s less

Values f o r ( s/ e H) are shown i n

I I I 1 I 1 I I I I I I I I I I

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~RWEQUIPMENT LABORATORIES 1 . I I I I I I I I I I I I I I I I I I

Tables 7(a) through 7(g) f o r sane coatings and surfaces.

4.4 Coating Thickness

Thickness plays an bpor tan t r o l e i n determiningthe emissivity and solar

absorptivity characterist ics of a coating.

low absorptivity inorganic paints (66) indicated t h a t about 3 t o 5 m i l s coating

thickness was required t o cover metallic surfaces.

solar absorptivity (6,) and the solar absorptivity-emittance r a t i o ( d;s/ E H)

reached a mininnUn value with a 5 m i l o r greater coating thickness (Figure 60).

Multiple coats of 1 t o 2 mils bu i l t up t o 5 mils gave indications of having

Studies made with high emissivity,

The study also found t h a t

superior bonding properties than a single 5 mil coat.

4.5 Coatings and Substrates

4.5.1 Coatings

Coatings are classified as single a ides , multiple oxides, non-oxides, stably

oxided al loys and paints.

part of Tables 7(a) through 7 ( g ) .

The high emittance members of each group are shown as

4.5.1.1 Single Oxides

The single oxides coatings screened by P.W.A. (54) are l isted below.

hemispherical. emittance values are shown f o r temperatures ranging from 300%

minimum t o 22OOoF maxinrum.

Tote3

Single Oxides

1. Aluminum Oxide

2. Ceric Oxide

3. Chromic Oxide

T o t d Hemispherical Emittance

.69 - .63

-75 - 965

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4.

5 -

6.

7.

8.

9.

10.

, I I 1 I I I I

TRW EQUIPMENT LABORATORIES

11.

Cobalt Oxide (COO

Manganese Oxide ( M n q

Nickel Oxide ( N i O 1 Silicon Dioxide (Si021

Titania (Ti2031

Zirconium Oxide (zro2)

Stannic Oxide ( snO2 1

"Titania Base" Powder

.88 - .go -75 - -85

.45 - .82

-87 - .70

.92 - .85

8 7 7 - e82

-83 - e 8 8

.88 - .86

4.5.1.2 Multiple Oxides

The multiple oxide coatings screened by P.W.A. (54) axe l i s t ed below. Total

hemispherical emittance values are shown f o r temperatures ranging from 300%

minimum t o 2200% maximum.

Multiple Oxides Tot& Hemispherical Emittance

1. Silicates - Zirconium Si l icate .83 - .51 2. Spinels

a) Ma@;nesium Aluminate (MgO - Al 0 ) .00 - .60 2 3

b) 4oqd Nickel Chrome Spinel

60% Silicon Dioxide .88 - -82

3. Titanates

a) Barium Titanate (BaTi03) .75 - .64

b) Calcium Titanate (CaO Ti 02) .81 - e92

c) Iron - Titanium Oxide .85 - .07

d) Iron - Titanium-Aluminum Oxide .83 - -88

4. Zirconates - calcium Zirconate .62 - -56

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Minirmrm and maxirmrm values of t o t a l hemispherical emittance are indicated for

a31 substrates tested regardless of substrate o r coating thickness.

4 . 5 . 1.3 Non-Oxides

The non-oxide coatings screened by P.W.A. (54) are listed below.

hemispherical emittance values are shown below f o r tmperatures ranging f’rosl

30O0F minfrmrm t o 2200°F maximum.

Total

Non-Oxides Total Hemispherical Emittance

1. Borides

a) Crys tmine Boron .70 - .00

b) Boron and Si l i ca -78 - -79

c) Molybdenum Diboride -42 - -64

d) Tantalum Bride 049 - -59

.43 - .60 e ) Zirconium Boride

2. Carbides

a ) Acetylene Black i n Xylol

b) Boron Wbide

.72 - .92

.76 - .8o c ) G r a p h i t e Varnish -56 - e62

d) Hafhium Carbide .52 - .62

e ) Molybdenum Carbide -42 - -49

.80 - .g2

.05 - .07

.4J+ - .59

f) Silicon Carbide

g) Silicon Carbide and Silicon Dioxide

h ) Tantalum Carbide

i ) Titanium Carbide .42 - .62

j ) V a n a d i u m Carbide .48 - .60

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3. Fluorides - Calcium Fluoride

4. Nitrides - Boron Nitride i n Synar

060 - e47

-02 - .69

4.5.1.4

Some oxidized metals and t h e i r alloys exhibit t o t a l hemispherical emittance

values above .7.

range making an oxided metal surface unfavorable f o r use i n low temperature

r adiat or-condensers .

Stably Oxided Metals and Alloys

Unfortunately, t h e i r solar absorptivity values are i n the same

In high temperature (above 12OOOF) radiator-condenser applications ( systems

condensing potassium o r rubidium vapor), the effects of higher solar absorp-

t i v i t i e s are not as pronounced and the use of oxided metal surfaces may be

warranted.

Oxided metal surfaces require heating t o high temperatures t o accomplish the

oxidation process.

are 1 b 0 F with similar levels fo r Inconel, Inconel X and Haynes Alloy 25.

I

Typical oxidizing temperatures required f o r stainless steels

TRW EQUIPMENT LABORATORIES 'I i I I I 1 I 1 I I I I I I 1 I I I 1

The stably oxided metals surfaces screened by P.W.A. (54) are listed below.

Total hemispherical emittance values are shown f o r 300'F and 2200'F.

Total Metallic and Oxidized Metallic Surfaces Hemi spherical Wtt anc e

1. Columbium and Oxidized Columbium

2.

3. Cupric Oxide

4. Molybdenum

5. Oxidized Nichrme

Columbium - I$ Zirconium U o y

- 22 -

.26 - .69

.ii - .30

e 8 6 - .46

.20 - .34

.73 - .82

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1. ~RWEQUIPWEHT LABORATORIES

1 II I I I I 1 I I I I I I 1 I I I I

6. Lithiated and Oxidized Nickel

7. Oxidized AISI-310 Stainless Steel

8. Tantalum

9. Rrngsten

io. ciirixi&-~ Black

11. Platinum Black

-63 - .%

.47 - .84

4.5.1.5 Paints

Organic Enamels

High emittance organic enamels are a t t rac t ive from the standpoint t h a t they are

eas i ly applied and can be applied to any substrate.

Organic enamels w e r e found t o be u n f i t f o r long duration space applications since

most of t he coatings exhibit Wpreciable vapor pressures i n a vacuum a t room

temperature (68). The ef fec t is even more pronounced at elevated taperatures.

The lowest temperatures expected would be about 200°F i n the indirect fue l cell

radiator.

A t best, organic paints may be used where short duration thermal control appli-

cations (weeks-months) are required below 575OF.

and absorptivit ies are shown in Table 7(f) and 7(g).

Typical paints, their emittance

Water Glass Enamels

Si l ica te base paints are also known as water glass enamels.

inorganic coatings indicates that alkali-metal silicates, pigmented with

refractory silicate materials, were found t o possess l o w absorptivity-emissivity

r a t io s and high emissivities (66).

Ektensive tes t ing of

These coatings have the ahvantage of appli-

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cation by standard spray, dip or brush techniques.

can be accomplished by low temperature curing cycles between 200 t o 4W°F.

coatings are f lexible and ductile, have excellent t h e m s t ab i l i t y characterist ics

under 95OoF and are resis tant t o thermal shocks.

on aluminum and magnesium based substrates which makes them excellent candidates

f o r low temperature water o r organic radiator-condensers.

properties of inorganic coatings are included i n Tables 7(a) through 7(d).

Stabilization of the coating

The

These coatings have been applied

Typical radiative

4.5.2 Substrate Materials

High temperature coatings (above 1200'F) have been successfully bonded t o a wide

range of substrates.

columbium-l$ zirconium, nickel, columbium and molybdenum.

such as beryllium and copper can accept some coatings applicable t o 310 stainless

steel (49) due t o the slmilarity i n expension coefficients.

These include aluminum (1010, 6061) 31.0 stainless steel,

Substrate materials

Where large differences i n thermal expansion coefficients exis t between substrate

and desired coating, the difference can be reduced by W t i p l e layering of

several coatings.

Low temperature organic and silicone coatings (below 1000°F) can be bonded t o

most materials w i t h adequate surface preparation.

s t ra tes can be coated with inorganic pigmented, a l k a l i m e t a l . s i l i ca t e vehicle

coatings .

Magnesium and aluminum sub-

4.6 Application Methods

4.6.1 Themd Spraying

H i g h emittance coatings may be applied t o radiator surfaces by t h e plasma-twc

- 24 -

TR W EQUIPMENT LABORATORIES ,I 1 I I I I 1 I I I 1 I I 1 1 I I I I

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and the Rokide thema3 spraying processes.

The plasma-arc spraying process uses an e lec t r ic arc t o heat and ionize a vehicle

gas.

material i n powder form.

the union and the combination impinges on the radiator surface.

(argon, nitrogen) are generally used i n the plasma-arc spreying process.

The ionized gas is then combined with a second gas carrying the coating

The coating material powder is melted or softened by

Inert gases

The major advantage of the plasma-erc spraying technique is t h e ab i l i t y t o protect

the coated material f r o m an oxidizing atmosphere.

maintained below 40O0F while controlling coating thickness, f i n i s h and density.

The substrate material can be

The Rokide spraying process uses an ignited IIllxture of cambustible gases and a

so l id rod of coating material.

i n to t h e flame and is carried by the gas stream t o the surface t o be coated.

This process yields a more porous coating than t h e plasma-arc process because of

the lower gas veloci t ies and temperatures used.

The coating material rod vaporizes as it is fed

Plasma-arc and Rokide techniques are applicable t o stainless s teels , aluminum

alloys, refractory metals and their alloys, beryllium, copper alloys and cobalt

8llOy.s.

The Rokide process re-s t h e use of a coating rod material t ha t matches the

thermal expansion characterist ics of the substrate material f o r high temperature

applications.

4.6.2 Slurries

Coating materia3 may be applied in slurry form.

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TRW EQUIPMENT LABORATORIES *I I

A slurry i s a finely divided coating material suspended i n a l iquid binder.

It may be appl ied to the radiator surf'ace by spraying, brushing or dipping.

The coating i s air- and oven-dried t o remove vola t i le liquid.

technique finds application where substrate materials cannot withstand the

extreme temperatures of thermal spraying.

are l is ted below:

The slurry

The more promising slurries considered

slurry

Aluminum phosphate

syn=

xylol

curing w erature

500 t o 800°F

500%

Room temperature

4 6 3 Electrodeposition

Electroplating i s another method of applying a high emissivity coating t o a

radiator surface. The method i s extremely useful i n controlling the thickness

of the desired coating.

solutions include chromium, copper, nickel and platinum. Titanium, refractory

metals and duminum tiwe electroplated from fused-salt electrolytes.

solutions can also be used t o electroplate aluminum.

Metals and alloys that can be electroplated from aqueous

Organic

Electrodeposition h a s ma,ny advantages.

be deposited at near zero stress.

by applications of br ight copper and nickel.

controlled from a few millionths of an inch t o 100 mils.

Thermally stable pure metal coatings can

Surface defects and roughness may be leveled

!The thickness of a coating may be

Electroplating finds extensive use in plating chromium black and platinum black

on beryllium, stainless s tee ls and nickel. ChraaniWn black can be applied t o any

- 26 -

I I B I I 1 I I I I I 1 I 1 I I I

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c

surface that can be plated with nickel or chromium.

4-6.4 Vapor Phase Deposition

Surface catalysis, thermal decomposition or reduction of a coating's vo la t i le

compound are used t o produce both metallic and non-metallic deposits on metal

substrates (69).

of aluminM, chromium and nickel. pyrolytic graphites can be produced by thermal

decomposition of methane and acetylene on a heated surface at temperatures between

1832 t o 459% (69).

p p o l y t i c grqhite coatings applicable only t o l a w thermal expansion substrates.

The high t o t a l solar absorptances (70) ranging from .85 t o .gl of graphite i n

general make them applicable only t o high temperature potassium or rubidim radi-

ator condensers.

Therma;L decomposition of metal organic compounds produce deposits

The deposition temperatures required make high emittance

The major application of vapor phase deposition f o r space radiator-condensers is

limited.

substrate and a high emittance - low solar absorptance coating when electroplating

is impractical.

coating, and has a high deposition rate ( t o 20 mils per hour) (69).

It may be used 86 an intermediate layer of material between a m e t a l

The technique produces good coverage of the surface, a pore-free

4.6.5 Other C o a t i n g Methods

Chemical deposition, vacuum mete,llizin@; and painting are also techniques f o r

coating materials. Chemical deposition finds application where the use of anodes

and currents are not feasible.

bmersion o r displacement type

vacuum metallizing consists of

Platinum black is coated on beryllium by an

coating process.

evaporating the coating m e t a l and condensing it on

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TRW EQUIPMENT LABORATORIES

the surface t o be coated.

and t h e coating thickness i s generally less than 1 mi l th i ck .

not considered practica,l f o r large radiators and at t h e present t i m e i s re lat ively

undeveloped,

The process 1s accomplished i n a vacuum environment

The process is

Organic and inorganic coatings using volat i le vehicles can be applied by t h e

conventional painting methods of brush, dip or spraying.

temperature or in an oven at temperatures up t o 400% depending on t h e type of

coating being applied.

Curing is done at room

- 28 -

I I I I I I I 1 II 1 I I 1 8 1 I I u I

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~I I I I

I I ~I ‘I I II I I I I I

,I

5.0 REc0MMEMlATIoNs

Based on the readily available data in the literature, the following areas of

work appear t o wama,nt -her attention t o more rel iably and accurately design

and analyze condenser-radiators for space power systems:

1.

2.

3.

4.

Low temperature ( 3009) emittance coating testing. Most of this

work has been i n t h e higher temperature ranges, and as a result some

coatings unacceptable at high temperatures that may be acceptable at

fuel c e l l temperature levels, f o r instance, have been neglected.

Atmospheric testing of emittance coatings.

will be ground operated prior t o f l i gh t , the effect of this operation

Since almost B;u radiators

is iMportant.

Compatibility of f i n materials, tube materials and emittance coatings.

Information on a wider range of combinations, including beryllium, i s

needed.

Meteoroid protection capability.

protection thickness that accounts f o r the duc t i l i ty of amor materid

i n addition t o density and elastic nodulus.

Develup an expression f o r amor

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1. i I 1 I I I I I 1 I I I I I I I 1 I

Page 35: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

1. I I 1 I i I i I I 1 I I I 1 I 1 1 i

E3 I- v) w c I- I (3 - -1 LL

a I-

c

PL z! - a

VI a w m

Z

U Z

5 w

w LL W Y w LL w

2

Z - v) LL w m

Z 3

Page 36: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

TRW EQUIPMENT LABORATORIES

m .- -0

0 P 2 0' U 4 0

i - 0 c s E b

Y

Y

0 c L

C

I I I I I I I

I

Page 37: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

I 1. i 1 1 1 I 1 I I; I I I I 1 1 I I I I

w PI

I- 2

w o: v) v) w oc 0.

2 3 w n z w I-

Page 38: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

TR W EQUIPMENT LABORATORIES I-

-h - - -v

3 8 N y 9.0

$ 3 N N

%3 2.9 . .

Y U

84 . . 2." Y Y

- A -- 7 -

- 7 . . - -

1 1

0 0 . .

hlN mu) . . 2." U Y

-0

. . .".E u u

2 2 u ) u )

nh cs 00s 0.0. N r 4 . .

A

Q) h-

T 7 z z $8 z z

d ? Y 9

vu

Z Q

N ( 1 mu) . .

." .'" LLY

h

0. z 5: 7 .0

N 8

si . 2 Y

3 . 2 u

h 0. z c

*

m 0 . ." u

0 u) . ." u

u)

h 0.

0 0. N

",

.

A z 2 z Q, v) v

VI w Ei 8 m

-

.I I I I I I I I I I I I I I I I 1 I I

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I . I I I I I I I I I I f I I I I I I I

~ W E Q U I m E N T ~ ~ ~

TABLE 5A MATERIALS COMPATIBILITY WITH WORKING FLUIDS

NUMBERS IN PARENTHESIS ARE REFERENCE NUMBERS.

TEMPERATURES SHOWN INDICATE NO OR LOW AMOUNTS OF CORROSION.

(a) MORE TESTING REQUIRED TO CHECK OUT LONG TERM CORROSION EFFECTS.

(WC) N O T COMPATIBLE (VERY HIGH CORROSION RATE OR DISSOLVES)

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TRW EQUIPMENT LABORATORIES

TABLE 5B MATERIALS COMPATIBILITY WITH WORKING FLUIDS

NUMBERS IN PARENTHESIS ARE REFERENCE NUMBERS.

TEMPERATURES SHOWN INDICATE NO OR LOW AMOUNTS OF CORROSION.

I I I i I i I I I

I

I I I

I I I

1 I

f

I

t

i

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1 . I I I I I I I I I I I I I I I I I I

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TRW EQUIPMENT LABORATORIES

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I . I I I I I I I I I I I I I I I I I I

I R

2 W W 8

v) 0 - 0 . : 591

Y 0 0 : I?

- V ) N h ' . . ? m u

a 1 I- - 00 - I-

Y

2 2 Z

I-

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TRw EQUIPMENT LABORATORIES &- .

v)

0 z - t s E

W U z U

L W

P 1 a 2 U h' w 2

2

J w z - a v)

W

5 P Y

2

I

2 W

Y

= I =

Y)

Y a W

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I

TR

f ' I

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IRW EQUIPMENT LABORATORIES I

Y : m

5 2 I 9 I U

I Il I I~ I I I I I I I I 1 I II I 1 I 1

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1 1 I I I I I I I I I I I I D

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TRW EQUIPMENT LABORATORIES I 1 I 1 1 1 1 I I 1 1 I I I 1 1 1 I I

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111.

Figures

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LIQUID WATER DENSITY (59)

70

60

50

40 0 100 200 300 400 500 600

TEMPERATURE - OF FIGURE 1

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TRW EQUIPMENT LABORATORIES

L L 0 m s I-

I m

2 w I U LL U

- W CL v,

1.4

1 . 3

1.2

1 . 1

1 .o

0

WATER LIQUID SPECIFIC HEAT

4 0 1 00 200 300 400 500 600

TEMPERATURE - OF

FIGURE 2

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WATER HEAT OF EVAPORIZATION (59)

I, 7RWrourpvEnruwwm~Es

i I I I I I I I I 1 I I I I I I I I

1100

1000

900

800

700

600

500 0 1 00 200 300 400 500 600

TEMPERATURE - OF

FIGURE 3

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TRW EQUIPMENT LABORATORIES

.40

.39

.38

.37

.36

.35

.34

.33

.32 0

WATER LIQUID T H ER MAL C 0 N DUCT I V I TY

I I L

100 200 300 400

TEMPERATURE - OF 500 600

FIGURE 4

.I I I 1 I I I I I 1 I I I I I I 1 I I

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1.3

1.2

1 . 1

1 .o

.9

- 8

.7

-6

.5

.4

.3

.2

. 1

0 0 100

LIQUID WATER VISCOSITY (ABSOLUTE)

--EMT LA80RA-a

I I 1 I 1 I I U I I I I I I I I I I

200 300 400

TEMPERATURE - OF

500 600

FIGURE 5

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TR W EQUIPMENT LABORATORIES

I- s 1

I

Z 0

Z - v,

W I- W v 6

3 LL ni

v,

.006

.005

.004

.003

.002

.001

0 0

WATER SURFACE TENSION (LIQUID - VAPOR)

(97)

100 200 300 400

TEMPERATURE - OF

500 600

FIGURE 6

,I 1 I I I I I I 1 I I I I I 1 I I I I

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1. 1 I I I I I I I 1 I I I I I 1 I I I

LL 0 m

3 m

i I-

I

5 I v LL v n

- w v,

2 .o

1.8

1.6

.4

.2

.o

.8

.6

.4

0 100 200 300 400

TEMPERATURE -OF

500 600

FIGURE 7

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TRW EQUIPMENT LABORATORIES

cv 0

X

LL 0

I- L L oi

-

r \

m

> > V 3 n Z 0 V

2 I

I- - - I-

2 z oi w I I-

3.8

3.6

3.4

3.2

3 .O

2.8

2.6

2.4

2.2

2 .o

1.8

1.6

1.4

1.2

1 .o

.8 0

WATER VAPOR THERMAL CONDUCTIVITY

100 200 300 400

TEMPERATURE - OF

500 600

FIGURE 8

.I I I I I I I I I I I I I I I I I I I

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IktlwEQ&UPMEUTueoRAroRJrS

WATER VAPOR VISCOSITY

240

230

220

21 0

200

1 90

180

170

160

150

1 40

1 30

120

110

1 00

90

80

70

60 0 200 300 400

TEMPERATURE - OF 500 600

FIGURE 9

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TRW EQUIPMENT LABORATORIES

1000

1 00

10

1 0 100 200 303 400

TEMPERATURE - OF

500 600 700

FIGURE 10

1

1

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I . I I I I I I I I I I I I I I I I I I

MERCURY LIQUID DENSITY

850

830

81 0

c) c s A

' 790 >-

Z

c tn

w

- Q

770

750

730 0 200 400 600 800 lo00

TEMPERATURE - OF

FIGURE 1 1

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.035

.034

u, 0

m s .033

I

2 w I v -

.032 w CL v)

.031

MERCURY LIQUID SPECIFIC HEAT

TR W EQUIPMENT LABORATORIES . I I I I I I I I I I !

I I I

0 200 400 600 800 1000 1200

TEMPERATURE -OF

FIGURE 12

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1 . I I I I I I I I I I I I I I I I I I

MERCURY LIQUID THERMAL CONDUCTIVITY

10

800 1 000 0 200 400 600

TEMPERATURE -OF

FIGURE 13

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TRW EQUIPMENT LABORATORIES

MERCURY LIQUID VISCOSITY (AB SOLUT E)

d 0 - X

u w v) I

I- s -I I

> c

- >

12

1 1

10

9

8

7

6

5

4 0

I \ B

\ \ \ \ \ \ \ \ \

A \

200 400 600 800

TEMPERATURE -OF

1000 1200

FIGURE 14

. I 1 1 1 I 1 1 I I I I I I I I

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I 1 I I I I I I I I I I I I I I I I I

~

MERCURY SURFACE TENSION (LIQUID -VAPOR)

.034

.G33

.032

I- LL

-J

t -031 0 Z - v)

w I-

t? 5 Q -030 u,

v)

.029

-028

.027

400 600 800 1 000 0 200 TEMPERATURE - O F

FIGURE 15

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TRw EQUIPMENT LABORATORIES

.014 I

MERCURY VAPOR THERMAL CON DUCT I V I TY

* 01 2

0" I I- L L

e I .010

& .008 3 n Z 0 W

;i I .OM pr: W I I-

.004

.002 0 200 400 600 800 1000 1200

TEMPERATURE -OF

FIGURE 16

,I I I I I I I I I 1 I I I I I I I I I

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1. 1 I I 1 II 1 I 1 I I I I I I I I I I

7

6

5

4

3

2

1

0 0

MERCURY VAPOR V I SCOS ITY (ABSOLUTE)

400 600 800

TEMPERATURE -OF

lo00 1200

FIGURE 17

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TRw EQUIPMENT LABORATORIES ,I

lo00

100

10

1

MERCURY VAPOR PRESSURE (111)

0 200 400 600 800 1000 1200 1400

TEMPERATURE - OF

FIGURE 18

I

I I I

~

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1 I 1 I I I I i I 1 1 1 I I 1 I I I 1

IRW EQWPMW LIIKIRAIXBRIES

POTASSIUM LIQUID DENSITY

52

50

48

m E 4 6 h A

I

> != Z w 4 4 n

LA

42

40

30 200 400 600 800 lo00 1200 1400 1600

TEMPERATURE - OF

FIGURE 19

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k I

m

a r w

TRW EQUIPMENT LABORATORIES I

POT ASS I UM L I Q U I D SPECIFIC HEAT

.23

.22

.21

.20

.19

.18

.17

.16 200 400 600 800 1000

TEMPERATURE - OF

1200 1400 1600

FIGURE 20

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1. 1 1 I 1 1 I I I I I 1 I 1 I I I I I

POTASSIUM HEAT OF VAPORIZATION

940

900

m -J

3 860 m

Z 0

5 820

+ I

I-

- 8 2

2

>

780 w I

740

700 600 800 1000 1200 1400 1600 1800

TEMPERATURE - OF

FIGURE 21

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-

TRW EQUIPMENT LABORATORIES

30

28

26

24

22

20

18

16

14 200

POTASS I UM LIQUID THERMAL CON DUCT I V ITY

400 600 800 lo00 TEMPERATURE - OF

1200 1400 1600

FIGURE 22

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1. 1 I 1 I I I 1 i I i I I I 1 I I 1 I

POTASSIUM LIQUID VISCOSITY (ABSOLUTE)

3.4

3.0

2 . 6

2.2

1.8

1.4

1.0

.6

.2 200

f

400 600 800 1000

TEMPERATURE - OF 1200 1400 1600

FIGURE 23

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. OOE

007

.OM $3 -I

I

Z 2 v, .005 Z w I- w U Q

5 .004 LL

v,

.003

.002

TRw EQUIPMENT LABORATORIES

POTASS I UM SURFACE TENS1 ON (LIQUID-VAPOR)

b

\

800 1 000 1200 1400 1600 200 400 600

TEMPERATURE - OF

FIGURE 24

.I I I I I I 1 I I I 1 1 I I I I I 1 I

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u . lRW~ourpwrrvr LABORATORIES

.28

.) 26

LL 0 .24 m s I-

I

I-

m

4 -22 r u U

- L - I J J L VI .20

.18

-16

.14 600 800

POTASSIUM VAPOR SPECIFIC HEAT (CONST. P)

L 1 000 1200 1400 1600 1800

TEMPERATURE - OF FIGURE 25

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TRW EQUIPMENT LABORATORIES

POTASSIUM VAPOR THERMAL CONDUCTIVITY (62)

.OlO

.009

.008

.007

.006

.005

.004 600 800 1000 1200 1400

TEMPERATURE - OF

1600 1800

FIGURE 26

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POTASSIUM VAPOR VISCOSITY (ABSOLUTE)

(62)

i I I

1 I I I I

1.5

1.4

1.3

1.2

1.1

1 .c

C ., 600 800 lo00 1200 1400

TEMPERATURE - OF

1600 1800

FIGURE 27

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TRW EQUIPMENT LABORATORIES

POTASSIUM VAPOR PRESSURE

1000

100

10.0

1 .o

. 1

TEMPERATURE - OF

FIGURE 28

,I I I I I I I I I I I I I I 1 I I I A

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-EQUIPMENT LA60RATORlES

RUBIDIUM LIQUID DENSITY

91

89

87

85

A

I

I- ul

>

Z -

81

79

77

75

73 200

\

400 600 800 lo00 TEMPERATURE - OF

1200 1400 1600

FIGURE 29

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T A W EQUIPMENT LABORATORIES

RUBIDIUM HEAT OF VAPORIZATION

400

380

360

340

320

300 400 1400 1600 600 800 1000 1200

TEMPERATURE - OF

FIGURE 30

,I I I E I I I I I I I I 1 I 1 I I I I

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1. 1 I I I

mw EQUWUENT LABORATORIES

RUBIDIUM LIQUID THERMAL CONDUCTIVITY

(62) 17

16

15

14

13

12

1 1

10 400 600 800 1000 1200 1400 1600

TEMPERATURE - OF

FIGURE 31

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TRw EQUIPMENT LABORATORIES

RUBIDIUM LIQUID VISCOSITY (ABS 0 LUTE)

2.0

1.8

6

. 4

.2

1 .o

0 400 600 800 1000

TEMPERATURE - OF

1200 1 400

FIGURE 32

I I

I I I

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RUBIDIUM SURFACE TENSION (LIQUID -VAPOR)

.005 1

I -004

~ ; .003 I 0

J v)

i D 0

(97)

200 400 600 800 lo00 1200 1400 1600

I TEMPERATURE - OF

I FIGURE 33

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TRW EQUIPMENT LABORATORIES

. I 1

.10

.09

.08

.07 400

7 I

RUBIDIUM VAPOR SPECIFIC HEAT

(CONST. P) (62)

1400 600 800 1000 1200 TEMPERATURE - OF

1600

,I I I 1 I 1 I i 1 I I I

FIGURE 34

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RUBIDIUM VAPOR THERMAL CONDUCTIVITY

(62)

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TRW EQUIPMENT LABORATORIES

2.0

.8

m 0 c

X

u 1.6 W v)

I- s A I

> 1.4 I- - 5 u

1.2

1 .o

RUBIDIUM VAPOR VISCOSITY (AB SOL UTE)

(62)

400 800 1 000 1200

TEMPERATURE - OF

400 1600

FIGURE 36

800

I I I 1 I I I I I I I I I I I I I

I Ii

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RUBIDIUM VAPOR PRESSURE

1 00

80

60

40

5 20 v) &

I

W ai 2 v) Lu cz

10 Z 0 8 - s 2

I-

3 6

v)

4

2

1 I

1

i

800 1000 1200 1400 1600 1800 2000 2200 TEMPERATURE - OF

FIGURE 37

300

200

1 00

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TRW EQUIPMENT LABORATORIES

70

60

50

40

\

ETHY LBE t

ORGANIC LIQUID DENSITY

L E N E (61)

I L E N E (61)

\

\

0 100 200 300 400 500 600 TEMPERATURE - OF

FIGURE 38

.I I I I I I 1 1 I I I 1 I I I I I I I

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R I I

.8

.7

.6

.5

.4

. 3 0

ORGANIC LIQUID SPECIFIC HEAT

DOWTHERM-A (23)

100 200 300 400 TEMPERATURE - OF

500 600

FIGURE 39

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TR W EQUIPMENT LABORATORIES

ORGANIC HEAT OF VAPORIZATION

200

190

180

170

160

150

1 40

130

120

110

100

90

80

70 0 100 200 300 400

TEMPERATURE - O F

500 600

FIGURE 40

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1. 1 I I I I I I I I I I I I I I I I

ORGANIC LIQUID THERMAL CON DUCT1 VlTY

.09

.a3 LL 0

I t- u.. w r 3 c .07 m

>- >

t

t- - - 6 3 -06 n Z 0 V

4 2 .05 r

a

w

t-

.04

.03 0 100 200 300 400 500 600

TEMPERATURE - OF FIGURE 41

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TRW EQUIPMENT LABORATORIES ,

.003

.002

.001

0 0 100

ORGANIC LIQUID VISCOSITY (ABSOLUTE)

(23)

200 300 400 TEMPERATURE - OF

500 600

FIGURE 42

.I I I I I I I I I I 1 I I I 1 I I I II

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28

27

26

25

* E 24 x

23 k

z 22 0

z 21

a 20

2 I

- In

W + W u LI ni

ln 3

19

18

17

16

15

14

13 0 100 200 300 400 500 600

TEMPERATURE - OF

FIGURE 43

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TRW EQUIPMENT LABORATORIES

ORGANIC VAPOR SPECIFIC HEAT (CONST. P)

.6

.5

L 0 I

m i 2 .4

5 I! .3

m I

+

I

LL - U w p. m

.2

. 1

ETHYLBENZENE &

/ ' DOWTHERM-A j23)

I

0 1 00 200 300 400 500 600 TEMPERATURE - OF

FIGURE 44

,I I I 1 I I I I 1 I I I I I I 1 I 1 I

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ORGANIC VAPOR THERMAL CONDUCTIVITY

(61 ) .022

,020

-018

u, 0

I I- LL

CY I .016 I

I- m

I

3

>. C .014 >

3 0 Z 0 u .012 Q z

- ti

J

CY Lu I I-

.010

.ow

.006 0 100 200 300 400 500 600

TEMPERATURE - OF

FIGURE 45

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TRW EQUIPMENT LABORATORIES

ORGANIC VAPOR VISCOSITY (ABSOLUTE)

90 c

X u w v, I I- s

8

J

I

I- > - U c" >

IO

9

8

7

6

5

4 0 1 00

ORTHO-XYLENE (61)

200 300 400

TEMPERATURE - OF

500 600

FIGURE 46

.I I I I I I I I 1 I I I I I I

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100.0

10.0

s v)

I n

1 .o

0.1

-I-

ORGANIC VAPOR PRESSURE (23)

0 200 300 600 700 800

SATURATION TEMPERATURE- OF FIGURE 47

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TRw EQUIPMENT LABORATORIES

6

5

4

3

2

1

0

ORGANIC LIQUID VISCOSITY (ABSOLUTE)

(1 07)

0 100 200 300 400 500 600

TEMPERATURE - OF

FIGURE 48

.I 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 I

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1 I

I 1

I 1

mw EQWWEWT LABORATORIES

ORGANIC VAPOR PRESSURE (61) lo00

100

i 100 200 300 400 500

TEMPERATURE - OF 600 700

FIGURE 49

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MODULUS OF ELASTICITY OF RADIATOR MATERIALS

ili

COBALT ALLOYS (16)

S. ST. (1) i I

I

.I I I I I I I I I I I I I I I 1 I I I

TRW EQUIPMENT LABORATORIES

PYROLYTIC 'GRAPHITE - a DIRECTION (38) I I

\

0 200 400 600 800 1000 1200 14QC TEMPERATURE - OF

FIGURE 50

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S

I ZIRCALOY-2 (1) I

1' AZ31B 8, HK31A Mg (1) I 0 200 400 600 800 lo00 1200 1400

TEMPERATURE - OF FIGURE 51

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TRw EQUIPMENT LABORATORIES

\ I Y

1 oo(

I\ I I

THERMAL CONDUCTIVITY OF RADIATOR MATERIALS

'COBALT ;ALLOYS (16)

I I I I I I I I I I I I I I I I I I I I 1 I I

I I

\ Ti - 6 A I - 4V (1)

/ PYROLYTIC GRAPHITE - a DIRECTION (38)

7075 & 2024 A I (1 ) I I I I- 1-

I I . . , . . - , I I 1

I-----

I

'\ ---

Cb-1 Zr (6)

0 208 400 600 800 1000 1200 1400

TEMPERATURE - OF FIGURE 52

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1. I I I I I I I I I 1 I I I 1 1 1 I I

1 OOG

500

1 00

50

10

5

1 0

THERMAL CONDUCTIVITY OF RADIATOR MATERIALS

I I I I I I I I

1 I

Y I I I 1 I I ’ ZlRCALOY-2,(1)

i I

I 300 SERIES I

200 400 603 800 TEMPERATURE - OF

1 O N : 1200 14co

FIGURE 53

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TRW EQUIPMENT LABORATORIES .

1 00

90

80

70 7 0 c

X - 60 v, p.

I

E 50 0 Z w oi I- Ln

-1 n 40 w > 8 7 30

20

1c

0

.2% YIELD STRENGTH OF RADIATOR MATERIALS

I I I I

’ PYROLYTIC GRAPHITE - a DIRECTION (89

.I I I I I I I I I I I I I I I I I I I

~~

0 200 400 600 830 1 OOC 1206 1400 TEMPERATURE - OF

FIGURE 54

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100

90

80

70

60

50

40

30

20

10

0

.2% YIELD STRENGTH OF RADIATOR MATERIALS

\ I

0 200 400 600 800 lo00 1200 1400

FIGURE 55 TEMPERATURE - OF

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IRW EQUIPMENT LABORATORIES

.2% YIELD STRENGTH OF RADIATOR MATERIALS

1 50

1 40

130

120 c) I 0

x 2 110

1

I I-

80

70

60

50 0 200 400 600 800 1000 1200 1400

TEMPERATURE - OF

FIGURE 56

,I I I I I I I I I I I I 1 I I I I I I

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THERMAL EXPANSION OF RADIATOR MATERIALS

I 1 I I I I I I I I I I I 1 I 1 I

9 0

X

LL 0

M W P

-

Z - & w P

Z

Z 0 Z

X

- I

- v)

2 w z w W

I- I

18

16

14

12

10

8

6

4

2

0

0

H

I 300 SERIES

Be (1/2 -3

I 1 I I

I PYROLYTIC GRAPHITE a DIRECT O N (89)

~

0 200 400 600 800 loo0 1200 1400

FIGURE 57 TEMPERATURE - OF

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TRW EQUIPMENT LABORATORIES

THERMAL EXPANSION OF RADIATOR MATERIALS

10

9

8

7

6

5

4

7

' A-286 (6)

/rli Ti - 6 A I - 4V

0 200 400 600 800 1 OCO 1200 1 400

FIGURE 58 TEMPERATURE - OF

.I I U I I I I I I I I I I I I I I 1 I

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0 0. co h c

0 0 hl

c

3 - 33NVll lW3 lV3ld3HdSIW3H lV101 FIGURE 59

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TRW EQUIPMENT LABORATORIES ,

EFFECT OF COATING THICKNESS ON as A N D CC~/'H

(68)

0.45 n

u I

\

U z 2 0.35 a

5 n

{ 0.30 Y

b

8 m 0.25 m d oi 4 0 v,

0.20 0 .OOl I 002 .003 .004

THICKNESS - INCHES

.O05

FIGURE 611

.I I I I I I 1 1 I I I I I I I I 1 I 1

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IV.

References

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Note:

but rather a publication which referenced the primary source.

ke-pt the u i i e r of refeArexes to a mesma3le m&er *Ale still emblFng the

interested user t o analyze t h e primary source of data.

I n some cases, the reference l isted is not the primary source of' data - !&is substitution

1. Sachs, G. (Editor), Air Weapons &terial Application Randbook Metals and

Alloys, ARDC-TR 59-66, December 1959.

2. Beryllium in Aero/Space Structures Brochure.

3. Superior Tube Bulletin No. 301, March 1964.

4. properties of Beryuium, Genera Astrometds corp.

5. Hughel, T. J., "Beryllium - A Space Age Metal," Metals Engineering

&uarterly, MY 1962.

6. Radiators f o r SNAP 50/SWR, AiResearch Manufacturing Coo, AFAR, TR-64-143,

March 1965.

7. Davis, Harold L., "The Future of' t h e Rankine Cycle," Nucleonics, Vol. 22,

March 1964.

8. Kelly, K. J., Klannrt, C. J., Rosenblwn, L., *=el, J. W., Jr. and

Thurber, W. C., llCorrosion of High Temperature Materials i n Alkali Metals,"

Nucleonics, Vol. 22, March 1964, 37-42.

Page 112: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

9. Freche, J, C., Ashbrook, R. L. and Sanorock, G. D., High Temp erature

Cobalt Tungsten Alloys f o r Aerospace Applications, NASA Lewis, ASME &3D,

April 1964.

10. Diedrich, J. H. and Lieblein, S., Materials Problems Associated with the

Design of Radiators f o r Space Power Plants, NASA Lewis, 0F.ARS 2535-62,

Space Power Systems Conference, September 25-28, 1962.

11. Adams, J. L., 11Spacecr8fct Mechanical Engineering," Vol. 11, space

Technology, NASA SP-66, 1965.

12. Benjamin, 17. D. and Vargo, E. J., The Current Status of Materials

Compatibility with Two-Phase Alkali Metals, TM-3697-67, TRW Inc . , May 1963 9

13. Owens, J. J., Nejedlik, J. F. and Vogb, J. W., Mercury Materials

Evaluation and Selection - The SNAP 2 Power Conversion System Topical

Report No. 7, ER-4103, TRW Inc., October 1960.

14. Liquid Metal Corrosion Meeting, Vol. I, NASA-AEC, NASA-SP-41, October 1963.

15. Space Materials Handbook, 2nd Edition, ML-TDR-64-40, J a n u q 1965.

16. Haynes H i g h Temperature Al loys Engineering Properties and Fabrication

Information, June 1962.

17. DePaul, D. J., (Editor), Corrosion and Wear Handbook for Water Cooled

Reactors, AEC, TID 7006, March 1957, 95-119.

TRW EQUIPMENT LABORATORIES . I I I 1 I I 1 I I I I 1 1 I 1 I I I I

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18. Blaser, R. U. and Owens, J. J., Special Corrosion Study of Carbon and

Low Alloy Steels, ASTM 1956, Special Technical Publication No. 179.

19. W a n h l y n , J. N. and Jones, P. V., "The AQueous Corrosion of Reactor Metals,"

Journal of Nuclear Materials, No. 6 , lbrth Holland Publishing Co.,

Amsterdam, 1962, 291-329.

20. Johnson, A. L., "Space Craft Radiators," Space/Aeronautics, January 1962,

76-82.

21. Tackett, D. E., Brown, P. E. and Esper, R. T., Review of Carbon Steel

Corrosion Data fo r High !Temperature High Purity Water in Dynamic Systems,

WAPD-LSR(C) - 134, October 1955.

22. Thermal Radiative Properties of Selected Material, DMIC Report 177,

Vol. 1 and 2, November 15, 1962.

23. Dowtherm Handbook, Dow Chemical Corporation.

24, Carlton, S. S., Operation of a Forced Circulation Loop t o Study Selected

Praperties of Ortho-xylene, TM-3633-67, T R W Inc., March 1, 1963.

25. Vargo, E. J. and Pearson, J. B., Therma3 Stabili ty Determinations of

Selected Organic Working Fluids, TM-3381-67, !TRW Inc., April 3, 1962.

26. McEwen, Malcolm, Organic Coolant Data Book, Technical Publication No. AT-1,

Monsanto Chemical Co., July 1958.

27. Radiator Condensers for space Environment, Electro-optical Systems Inc.,

Pasadena, C a l i f . , WADD TR-61-20 (ASTIA AD NO. 253791), October 31, 1960.

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IRW EQUIPMENT LABORATORIES ,

28.

29

30

31 9

32

33

34

35

36

37

Bickerman, J. J., Surface Chemistry, Academic Press, Second Edition, 1958.

Alkali Metals Boiling and Condensing Investigation Final Report,

G.E. 63 ~ ~ 0 6 6 , G.E. Missile & Space Division, January 14, 1965.

Nejedlik, J. F., The SNAP 2 Power Conversion System Topical Report No. 14,

(m-SR-6306) Mercury Materials Evaluation and Selection, ER-4461, T R W Inc.,

July 24, 1962.

Solax Rankine System Performance and Status Summary, ER-4955, TRW Inc.,

July 24, 1962.

Owens, J. J. and Nejedlik, J. F., Materials Compatibility with Mercury

at Temperatures below 1000°F, Corrosion by M e t a l . Heat Transfer Liquids

Symposium, AIME Meeting, February 22, 1962.

NASA-AEC Liquid-Metals Corrosion Meeting, Washington, D.C., NASA TN D-769,

December 1960.

Liquid Metals Handbook, Sodium-NaK Supplement, T I 0 5277, July 1, 1955.

Designing w i t h Aluminum, Kaiser Aluminum Inc., 1957.

Corrosion Resistance of Beryllium i n High Temperature Water, Brush

Beryllium Company, Cleveland, Ohio, 1957.

Titanium Design Notes, Electro Metallurgical Company, Reprinted from

Magnesia and Titanium Data, Published by Brooks and Perkins, Inc.

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38. Pyro lytic Graph i te , A Status Report, G.E. Technical Information Series,

R 63 SD &.

39. "Materials i n Design Eugimering," Materials Selector Issue, October 1963.

40. "Pruperties of Ti-6Al-4VY" Titanium Engineering Bulletin No. 1, TitaniUm

Metals Corporation of America, Revised February 1965.

41. "yp ical Pmp erties of Tungsten, Tantalum, Molybdenum and Columbium,

Fansteel Metallurgical Corporation, Brochure, 1960.

42. Steels for Elevated 'pemp emture Service, United States Steel, 1952.

43. Luoans, W., Determination of the W s s i v i t y of Materials Semi-Aunual

Progress Report, N o v e m b e r 15, 1964 through May 14, 1965, NAS 3-4174.

44. Bnanuelson, R. C., Determination of the Emissivity of Materials Semi-Annual

Progress Report, May 14 through Ncnreniber 15, 1964, NAS 3-4174, NASA

CR 54268, PWA-2518.

45. Hayes, R. J., Determination of the Fmissivity of Materials @&erly

Progress Report, July 1 thr- September 30, 1963, m - 1 0 9 9 mA-2279-

46. W e s , R. J., Detemination of the W s s i v i t y of Materials, January 1

through June 30, 1963, NASw-109, PWA-2255.

47. Hayes, R. J., Determination of the Bnissivity of Materials Quarterly

Progress Report, October 1 through December 31, 1962, NASw-104, PWA-2163.

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TRW EQUIPMENT LABORATORIES

48. Hayes, R. J. and Atkinson, W. H., "Thermal Emittance of Materials f o r

Spacecraft Radiator Coatings,

(No. g ) , 616-62~

Ceramic W l e t i n , September 1964, Vol. 43

49. Askwyth, W. H., Hayes, R. J. and Mihk, G., "Rnittance of Materials

Suitable for U s e as Space Radiator Coatings," Progress i n Astronautics

and Aeronautics, Vol. 11, 401-425.

50. Curtis, H. B,, kasurement of Hemispherical Total Rnittance and Normal

Solar Absorptance of Selected Materials i n the Temperature Range 280° t o

60O0K, AIAA Paper No. 64-256, July 1964.

51. Wood, W. D., Deem, H. W., and Luchs, C. F., The Fmittance of Ceramics

and Graphites, DMIC 148, March 28, 1962.

52. Beach, J. G., Electrodeposited, Electroless, and Anodized Coating on

Beryllium, DMIC 197, September 1, 1964.

53. Annual Progress Report, Determination of the RnissiVity of Materials,

WW-104, PWA-2309, January 1 through December 31, 1963.

54. Interim Final Report, Determination of the Rnissivity of Materials,

NASW-104, PWA-2206, Vole 1, 2 and 3.

55. V a n Vliet , R. M., Passive Temperature Control i n the Space Environment,

Macmillan Co., New York, Copyright 1965, Library of Congress Catalog

Card Number 64-21964.

.I I I I I I I I I 1 I I I I I I I I I

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1, 1 1 I I I I I 1 I 1 1 I I I 1 1 I 1

56. Betz, H. T., Olson, 0. H., Schwin, B. D. and Morrisy J. C., Detexmination

of Emissivity and Reflectivity Data on &craft Structural MaterialsL

Part 11, Techniques fo r Measurement of Total Normal Spectral Emissivity,

Solar Absorptivity, and Presentation of Results, WADC TR 56-2&,

ASTU AD 202493, October 1958.

57. Olson, 0. H. and Morris, J. C., Determination of EMssivlty and

Reflectivity Data of Aircraft Structural Materials, Part 11, Supplement I,

WADC TR 56-222, ASTIA DocMlent No. 202494, October 1958.

58. Mash, D. R., Editor, Wterials Science and Technology for Advanced

Applications, Englewocd Cliffs, N. J., Prentice H a l l Inc., 1962.

59. Keenan and Keyes, Themodynami c Properties of Steam, John Wiley and

Sons, Inc., 1947.

60. Themophysical Properties of Rubidium and Cesium, ML-TDR-64-42, Mxf 1964.

61. Maxwell, J. B., Data Book on IIydrocarbons, D. Van Nostrano C m p a n y , Inc.,

February 1957.

62. Weatherfofi, W. D., Jr., Tyler, J. C. and Ku, P. M., Properties of

Inorganic Energy Conversion and

Applications, Southwest Research Institute, \?ADD TR 61-96, Noveniber 1961.

H e a t Transfer Fluids for Space

63. Lype, E. F., The Design of a Mollier Chart fo r Vapors, m-5584, TRW Inc.,

October 9, 1963.

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TRW EQUIPMENT LABORATORIES ,

64.

65

66.

67

68.

69.

70

71

72 9

73

74

Journal of Resemh of the National Bureau of Standards, (FP 2204), Vol. 46,

1951.

Carroll, W. F., Development of Stable Temperature Control Surfaces f o r

SpacecraSt, Progress Report No. 1, J.P.L., "R-32-340, November 20, 1962.

Corrosion Protection of Magnesium and Magnesium Alloys, DMIC 205, June 1, 1965.

Handbook of Chemistry and Physics, 34th Edition, 1952-1953.

Sibert , M. E., Inorganic Surface Coatings f o r Space Applications,

Lockheed Missiles & Space Division, August 1961, 3-77-61-12, ASTIA 263-335.

Machine Design, Metals Reference Issue, September 1965, Vol. 37, Penton

Publishing Co.

Wood, W. D., Deem, H. W. and Lucks, A. F., The Emittance of Ceramics and

Graphites, DMIC 148, March 1962.

Investigation and Analysis of the Application of a Heat Pump i n Thermal

Control Systems f o r a Manned Spacecr&, General Dynamics Report

GD/C-65-120, May 1965, Revised August 1965.

hproved Radiator Coatings, Part I, ML TDR 64-146, June 1964.

Kroeger, H. R., e t al, Steam Space Power Systems with Nuclear and Solar

Heat Sources, ASTRA Inc., Raleigh, N. C., May 1963 (ASTRA 205-1.6.1).

Malohn, Donald A . , Development of an Organic Rankine Cycle Power System,

Sundstrand Aviation-Denver, Presented Winter ASME Meting, Chicago, Ill.,

November 7-11, 1965.

.I I I 1 1 I 1 I I I I I I I I I 1 I I

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1. I 1 I I 1 I I I I I I I 1 I I I I 1

75. Radioisotope Dynamic Electrical Parer Systems Study for Manned Ws/Venus

Mission, Ktd-term Report, Atcmics International Report AI-65-6 Vol. 1,

February 19, 1965 (Unclasswied Section) mAs 9-3520.

76. Nichols, K. E., 15 KW Advanced Solar Turbo Electric Concept, Vol. II of

Progress i n Astronautics and Aeronautics, "Power System i n Flight,"

(Editors) Zipkin, M. A. and Edxarrds, R. N.

77. Multi-Tube Orbital Rankine Experiment, m-6700, TRW Inc., November 1965.

78. Private Communication, J. Ra;ymer of NASA-Houston.

79. Solar Rankine System Performance and Status Summary , m-4955, mw Inc.,

July 24, 1962.

80. Tietz, T. E. and Perkins, R. A., Refractory M e t a l Alloys i n Sheet Form:

Availability, Prop er t ies and Fabrication, Journal of Spacecrafts and

Rockets, May-June 1964, Vol. 1, No. 3.

81. Schiff, Daniel, "Pyrolytic Materials f o r Re-entry Applications, 'I

Materials Science & Technology fo r Advanced Applications, Marsh, Donald R.

(Editor) h n t i c e - u , b c . , 1962.

82. Mendelsohn, A. R., "Contact Effectiveness of a Space Radiator," J m a 3

of Spacecraft &Rockets, Vol. 2, No. 6 , November-December 1%5.

83. Gardner, K. A. and Carnavos, T . C., Thermal Contact Resistance i n Finned

Tubing, Griscom Russell Co., 1959.

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84. Hagen, K. G., Integration of Large Radiators with Nuclear Electr ic

Spacecraft Systems, A i r Transport and Space Meeting, New York, N. Y.,

April 27-30, @ + .

85. Brazing and Bonding of Columbium, Molybdenum, Tantalum, Tungsten and

Graphite, Battelle Memorial Inst i tute , DMIC 153, OTS AD 278193, June 11, 1963.

86. Stang, J. H., Simons, E. M. and DeMastry, J. A . , Materials f o r Space Power

Liwid Metal Service, Battelle Memorial Ins t i tu te , DMIC 209, October 5 , 1965.

87. Thermal Decomposition of Biphenyl at 800°F and 85OoF, Monsanto Chemical Co.,

October 1963.

88. Heat Transfer Test Capsule Design Report, ER-4559, TRW Inc. , September 1961.

89. Garber, A. M., "Pyrolytic Materials f o r Thermal Protection Systems,"

Aero Space Engineering, Vol. 22, No. 1, January 1963.

90. Applied Research Program f o r Binary Rankine Cycle Energy Conversion,

ER-5925, T R W Inc., APL-TDR-64-5, April 1964.

91. space and Aeronautics R&D Handbook, 1963-1964, Materials Section.

92. Gaumer, R. E., "Problems of Thermal Control Surfaces i n the Space

Environment, I' Materials Science & Technology f o r Advanced Applications,

Marsh, D. R., Editor, Prentice-Hall Inc., 1962.

93. Radiation Heat Transfer Analysis for space Vehicles, ASD ~ ~ - 6 1 - = 9 ,

Part 11, September 1962.

.I 1 I I 1 I I I I I I I I I I I I I I

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1. 1 I I U I 1 1 I I I I I I I 1 I 1 I

94. Askwyth, W. H. and Hayes, R. J., Determination of the Emissivity of

Materials Quarterly Progress Report, July through September 30, 1962,

PWA-2128, NASW 104.

95. The Aluminum Data Book, Reynolds Metal Company, 1954.

96. Achener, P. Y. , The Determination of the Latent H e a t of Vaporization,

Vapor Presm, Enthalpy and Density of Liquid Rubidium and Cesium up t o

1800°F, AGN-TP-D, September 1963.

97. sp ace Radiator Study, ASD-TDR-61-697, October 1965.

98. International Critical Tables, 1929.

99. Oak Ridge National Laboratory Report, ORM, 3605.

100. Brown, A. I. and Mfwco, S. M., Introduction to H e a t Transfer, Second

Edition, WGraw-Hill, 1951.

101. -on, A. w., e t a ~ , Engineering Properties of Potassium, Batteue 4673,

~ i n a ~ , December 3, 1963, IUS 5-584.

102. Cooke, J. W., Thermaphys i c a l h-ape r t y Measurements of Alkali L iqu id Metals,

presented at Third Annual Conference on High-Temperature Liquid-Metal Heat

Transfer Technology, September 4-6, 1963.

103. Wallings, J. F.,et al, The Vapor Pressure and Heat of Vaporization of

Potassium frm 480 t o ll5OoC, Battelle, 4673-T3, April 30, 1963, NAS 5-584.

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7RW EQUIPMENT LASORATORIES ,

104.

105.

106.

107.

108.

109.

110.

111.

112.

113.

~ ~~

Deem, H. W. and Matolich, J., Jr., The Thermal Conductivity and Electr ical

Resis t ivi ty of Liquid Potassium and the Alloy Niobium -1 Zirconium,

Bat te l le 4673-T 6, April 30, 1963, NAS 5-584.

H a l l , E. H. and Blocker, J. M., Jr., The Viscosity of Saturated Liquid

Potassium from 70 t o l l 5 O o C by the Oscil lating Cylinder Method, Bat te l le

4673-T 1, AuPSt 31, 1962, NASA 5-584.

Deem, H. W., Eldridge, E. A. and Lucks, C. F., The Specific Heat from

0 t o l150°C and Heat of Fusion of Potassium, Bat te l le 4673-T 2, August 31,

1962, NASA 5-584.

McAdams, W. H., Heat Transmission, Third Edition, McGraw-Hill, New York,

1954

Reid, R. C. and Sherwood, T. K., The Pro-perties of Gases and Liquids,

McGraw-Hi l l , 1958.

Kirk, R. E. and Othmer, D. F., Encyclopedia of Chemical Technology, Second

Edition, Interscience Encyclopedia Inc., New York.

American Petroleum Ins t i t u t e Project 44.

Extension of National Bureau of Standards Data. (See Reference 64.)

Reactor Handbook, Second Edition, Interscience Encyclopedia Inc., 1961.

Lyons, R. N., Editor, Liquid Metals Handbook, Second Edition, Washington

Atomic Energy Commission, Department of the Navy, 1952.

.I I I I I I I 1 I I I I I I I I I I I

Page 123: I ‘I MATERIALS ‘I I With - NASA · rubidium and the organics, Dowtherm-A, ortho-xylene and ethylbenzene. ... Seven properties were selected and tabulated for each of the candidate

114. Crosby, J. R. and Perlm, M. A., SNAP 1OA Thermal Control Coatings,

Atomics International, AIAA Paper No. 65-652, presented at Thenmphysics

Specialist Conference, September 13-15, 1965.

115. Diedrich, J. R., Loeffler, I. J. and McMUan, A. C. , Hypervelocity Ixqact

Damage Characteristics in Beryllium and Graphite Plates and Tubes,

NASA Lewis, TN D-3018, September 1965.


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