NASA Technical Memorandum 88888 ? A Heater Made From Graphite Composite Material for Potential Deicing Application ? (NASA-TH-€?883&) A HEATER HADE PEUEl GRAPHITE N87-12559 1 CCMPOSITE MBTEBlAI ECE FOTENTIAL CEICING i AEPLlCBTION (NASA) 22 p CSCL OlC Unclas 7 &, G3/05 44729 Ching-Cheh Hung Lewis Research Center Cleveland, Ohio and Michael E. Dillehay and Mark Stahl Cleveland State University Cleveland, Ohio Prepared for the 25th Aerospace Sciences Meeting sponsored by the American Institute of Aeronautics and Astronautics Reno, Nevada, January 12-15, 1987 https://ntrs.nasa.gov/search.jsp?R=19870003126 2018-05-01T01:39:48+00:00Z
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NASA Technical Memorandum 88888
?
A Heater Made From Graphite Composite Material for Potential Deicing Application ?
(NASA-TH-€?883&) A H E A T E R HADE PEUEl G R A P H I T E N87-12559 1
CCMPOSITE M B T E B l A I ECE FOTENTIAL C E I C I N G i A E P L l C B T I O N (NASA) 2 2 p CSCL O l C
Unclas 7 &, G3/05 44729
Ching-Cheh Hung Lewis Research Center Cleveland, Ohio
and
Michael E. Dillehay and Mark Stahl Cleveland State University Cleveland, Ohio
Prepared for the 25th Aerospace Sciences Meeting sponsored by the American Institute of Aeronautics and Astronautics Reno, Nevada, January 12-15, 1987
2. Gaier, J.R., " S t a b i l i t y of' Bromine I n t e r c a l a t e d Graphi te Fibers," NASA
TM-86859, 1984.
3 . Di l lehay, M. and Gaier, J.R., "The M i l l i n g of P r i s t i n e and Brominated
P-100 Graphite Fibers," NASA TM-88828, 1986.
4. Jaworske, D.A. and Z lno labedin i , R., "Graphite F ibe r I n t e r c a l a t i o n :
Dynamics of the Bromine I n t e r c a l a t i o n Process," NASA TM-87015, 1985.
5. "Thornel P-100 Carbon F ibe r Grade VS-0054," Union Carbide Corporat ion,
B u l l e t i n No. 465-246.
6. Gaier, J.R. and Marlno, D., "Homogeneity of P r i s t i n e and Bromine
I n t e r c a l a t e d Graphi te Fibers," NASA TM-87016, 1985.
7. Hung, C.C. and M i l l e r , J., "Thermal Conduct iv i ty of P r l s t i n e and
Brominated P-100 Fibers," NASA TM-88863, 1986.
8. M i l l e r , J. and Hung, C.C., NASA Lewis Research Center, Cleveland, O H ,
unpublished data, 1985.
9. Hung, C.C., " A Micrographic and Gravimetr ic Study o f I n t e r c a l a t l o n and
De in te rca la t i on of Graphite Fibers," NASA TM-87026, 1985.
10. Jaworske, D.A., Vannuccl, R.D., and Z ino labedin i , R . , Vlechanical and
E l e c t r i c a l Proper t ies of Graphite F iber Epoxy Composltes Made From
P r i s t i n e and Bromine I n t e r c a l a t e d Fibers," t o be publ ished i n Journal o f
Composite Mater ia ls , 1986.
11. Scola, D.A. and Pater, R . H . , "The Proper t ies of Novel B ls imlde Amine Cured
Epoxy/Cell ion 6000 Graphi te F iber SAMPE Journal , Vo l . 18,
12. Maciag, C. and Hung, C.C., NASA Lewis Research Center, Cleveland, O H ,
Unpublished Data, 1986.
13. Perry, J . H . , Chemical Enqineer's Handbook, 4th ed., HcGraw Hill, N Y , 1973.
14. Handbook of Chemistry and Physics, 56th ed., 1975-1976, CRC Press, Boca
Raton, FL, 1976.
15. Gaier, J.R. and Slabe, H.E . , "Effects of Graphitization on the
Environmental Stability of Brominated Pitch Based Fibers," to be presented
at the Materials Research Society Meeting, Boston, MA, Dec. 1-6, 1986.
16. Hung, C.C. and Stahl, M . , "Effects o f Sequential Treatment with Fluorine
and Bromine on Graphite Fibers," to be presented at the Carbon Conference
of the American Carbon Society, Worcester, MA, July 1987.
17. Evans, U.R. , The Corrosion and Oxidation of Metals: Scientific Principles
and Practlcal Applications, Edward Arnold LTD, London, 1960.
18. Plurner, J . A . , Lightning Technologies, Inc., Pittsfield, MA, Personal ,
Communication, 1986.
15
TABLE 1. - PROPERTIES OF P R I S T I N E AND
BROMINATED P-100 FIBERS
E l ec t r i c a l r e s i s t i v i t y i n f i b e r d l r e c t i o n , p s c m
The rma 1 c o n d u c t i v l t y , W/m-K
Diameter, p
Dens1 t y , gm/cm3
Bromine/Carbon wei g h t r a t 1 o
Spec1 f 1 c heat , c a l /gm- " C
V i s t 1 ne P-1 00
250 (Ref .5 )
300 (Ref .7)
9.1 (Ref .6)
2.18 (Ref .8)
0
0.17 (Ref .12)
3rominated P-1 00
50 (Ref .6)
270 (Ref .7)
9.5 (Ref .6)
(Ref .8)
0.18 (Ref .9)
0.20 (Ref .12)
2.30
TABLE 2. - TRANSPORT PROPERTIES OF THE
BROMINATED P-100 FIBER-EPOXY
COMPOSITES WITH 60 PERCENT
F IBER VOLUME FRACTION
E l e c t r i c a l r e s l s t i v l t y , R-cm
Thermal conduct1 v i t y , W/m-K
Densi t y , g/cm3
Spec i f i c heat, c a l /gm-K
Thermal d i f f u s i v i t y , cm2/sec
L o n g i t u d i n a l d i r e c t i on
b83xl 0-6
162 (Ref . 8)
a1.90
0.22 (Ref .12)
0.93
Transverse d i r e c t i o n
0.5 (Ref . l o )
2.2 (Ref .8)
a1.90
0.22 (Ref .12)
0.013
aCal c u l a t e d va 1 ue
bCa 1 c u l a t ed Val ue
( f i b e r d e n s i t y = 2.30 Ref. 8, epoxy d e n s l t y = 1.30 !3/Cm3, Ref. 11)
( f i b e r r e s i s t i v i t y = 50 pQ-Cm, Ref. 6)
TABLE 3. - POTENTIAL DIFFERENCE BETWEEN THE ENDS, AND TEMPERATURE AT THE CENTER AND BOTH ENDS OF THE 3.4 CM WIDE HEATER WHILE
UNDER DRY HEATING TESTS AT A 20 A CURRENT
temp., C
T o t a l d u r a t i on I n water ,
73
( - ) temp., (+ ) temp., C C
T o t a l d u r a t i o n w i t h 20 A
a p p l i e d c u r r e n t , hr
91 90.5 86 88.4 94
0 6 7
28.8 59.2 79.5
90 1 5 84 82 86.5 80 18 86
90 94 I
End- to-end potent I a1 d i f f e r e n c e ,
V
0.65 0.65 0.69 0.73 0.95 2.05
Center 1 End 1 I End 2
r NICKEL F O I L (TOP VIEW)
PPROTECTING LAYER FlBER ,ti GLASS C W O S I T E
I . . , L - a
(SIDE VIEW) / I; NICKEL I
HEATING ELEMENT LAYERS 1 F O I L GRAPHlTE FIBER COMPOSITE ’ FIGURE 1. - STRUCTURE OF THE COMPOSITE
M T E R I A L HEATER,
FIGURE 2.- MODEL HEATERS USED I N THE TESTING. TOP: HEATER FOR HEATING PERFORMANCE EXPERIMENT. MIDDLE: HEATER FOR
CORROSION TEST. BOTTOM: CONTROL SAMPLE.
. FIGURE 3. - ELECTRICAL CIRCUIT USED TO TEST THE ELEC-
T R I C I T Y PENETRATION I N THE TRANSVERSE DIRECTION.
FIGURE 4. - ELECTRICAL CIRCUIT USED TO ESTIMATE THE CONTACT RESISTANCE BETWEEN THE F O I L AND THE COM- POSITE.
TEMPERATURE
0 CENTER 0 ONE END 0 OTHER END
42
u 3% w
I- 4 g 34
E 30 26
22 0 20 110 60 80 100 120
HEATING TIRE, SEC
FIGURE 6.- TEMPERATURE NEAR THE TWO ENDS AND AT THE CENTER OF THE HEATER AS A FUNCTION OF TIME. HEATER W I D T H = 1 . 2 7 CM: CURRENT= 6 A .
0 u 40 [I
0 0
0 5 10 15 20 POSITION, cn
FIGURE 7.- STEADY STATE TEMPER- ATURE AS A FUNCTION OF HEATER POSITION. HEATER WIDTH= 1.27 CM: CURRENT = 6 A .
1. Report No.
NASA TM-88888
9. Performing Organization Name and Address
National Aeronautics and Space Administration Lewis Research Center
12. Sponsoring Agency Name and Address
Cleveland, Ohio 44135
2. Government Accession No.
10. Work Unit No.
11. Contract or Grant No.
13. Type of Report and Period Covered
Technical Memorandum
4. Title and Subtitle
9. Security Classif. (of this report) Unclassified
A Heater Hade from Graphite Composite Material for Potent i a1 Dei c 1 ng Appl 1 cat1 on
22. Price' 20. Security Classif. (of this la e) 21. No. of pages Unclas Ified
7. Author($
Chlng-cheh Hung, Michael E. Dillehay, and Mark Stahl
3. Recipient's Catalog No.
5. Report Date
6. Performing Organization Code
505-68-1 1
E-3298
National Aeronautics and Space Administration Washington, D.C. 20546 14. Sponsoring Agency Code 1
I 15. Supplementary Notes
Prepared for the 25th Aerospace Sciences Meeting, sponsored by the American Institute of Aeronautics and Astronautics, Reno, Nevada, January 12-15, 1987. Ching-cheh Hung, NASA Lewis Research Center; Michael E. Dillehay and Mark Stahl, Cleveland State University, Cleveland, Ohio 44115.
A surface heater was developed using a graphite fiber-epoxy composite as the heating element. One-ply unidirectional graphite fiber-epoxy composite was laminated between two plies of fiber glass-epoxy composite, with nickel foil contacting the end portions of the composite and partly exposed beyond the com- posites for electrical contact. The model heater used brominated P-100 fibers from Amoco. The fiber's electrical resistivity, thermal conductivity and dens- ity were 50 VQ-cm, 270 W/m-K and 2.30 gm/cm3, respectively. intercalated, and therefore highly electrically conductive fibers, may be used as alternatives to the P-100 fibers. through the composite in the transverse direction to make an acceptably low foil-composite contact resistance. When conducting current, the heater temper- ature increase reached 50 percent of the steady state value within 20 sec. There was no overheating at the ends of the heater provided there was no water corrosion. If the foil-composite bonding failed during storage, liquid water exposure was found to oxidize the foil. perforated nickel foil is used, so that the composite plies can bond to each other through the perforated holes and therefore "lock" the foil in place.