AD--783 851 NONDESTRUCTIVE EVALUATIONS OF COM.- POSITE HEATSHIIELD MATERI1,ALS BElL-OPE AND AFTER AN UNDERGROUND NUCLEA, R EXPOSURE James R. Brown, Jr., et .1l Southern Research Institute P r ecpa r ed c, "}i Air Force Weapons Laboratory June 1974 DISTRIBUTED BY: National Technical Information Sarvice V!. S. DEPARTMENT OF COMMERCE 5285 Port Royal Road, Springfield Va. 22151
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AD--783 851
NONDESTRUCTIVE EVALUATIONS OF COM.-POSITE HEATSHIIELD MATERI1,ALS BElL-OPE
AND AFTER AN UNDERGROUND NUCLEA, REXPOSURE
James R. Brown, Jr., et .1l
Southern Research Institute
P r ecpa r ed c, "}i
Air Force Weapons Laboratory
June 1974
DISTRIBUTED BY:
National Technical Information SarviceV!. S. DEPARTMENT OF COMMERCE5285 Port Royal Road, Springfield Va. 22151
AFWL-TR- 73-247
IAIR FORCE WEAPONS LABORATORY
A-Ir Force Systems CommandKirtlend Air Force Base
* v ~Newi Mexico 87117 II
II
IWhen US Govuiement drawings, specifications, or other data are used for
any purpose other than a definitely related Government procurement operation,the Government thereby incurs no responsibility nor any obligation whatsoever,,And the fact that the Government may have formulated, furnished, or in any waysupplied the said drawings, specifications, or other data, is not to beregarded by implicition or other'ise, as in any manner licensing the holderor any other person or corporation. or conveying any rights or rarm'-slon tomanufacturs, use, or sell any patented invention that may in any way berelated thereto,
DO NOCT tTIVIRNI TuTC irr~nV. nRETAINNDETO'I
UNCLASSIFIEDw.~ .ily Ciasnifirsti-:n _______________
)DOCUMENT CONTROL DAIA &R & D(Srturtrty clas&,hg•aftoh of tilre. bod' of abaltac d And inde ai rr t , be a -,,,d L n the o-1e.11 repo., I. ¢1sl.Te 1)
IOR C• INA TIG ACIlVITY (Corporste aughorj n....R. R1 ISIECURITY T LAS311FICA TION
Southern Research Institute UNCLASSIFIEDBirmingham, Alabama 35205
3 R•PORT IITLE
NONDESTRUCTIVE EVALUATIONS O0 COMPOSITE HEATSHIELD MATERIALS BEFORE A4'D AFTERAN UNDERGROUND NUCLEAR EXPOSURE
4 DESCRIPTVE NOTES (Tpe of report and nclsve dater)
Final Report; May 1972-Noýember 1973t AU Tf-ORI$I (irSft name, middle Inlriehl last na e)
James R. Brown, Jr.; H. G. Sanders; C. D. Pears
0 RPý'_ORT DATE 7r. TOTAL NO. OF PA•FS 7b. NO. OF R EPS
June 1974 122 Noner*. CONTRACt OR •RANT NO 9a. ORIGINATOR'S REPORT NUMBER(S)
F29601 -7?-C-0058b. PROJECT NO. 627A AFWL-TR-73-247
. Task No. 0 9. OTHER REPORT OSj, (Any other nu..•.r thatmay be ... l.ned.thif report)
d.
1 DISTRIBJT:ON STATEMENT
Approved for public release; distribution unlimited.
II SU"PLLM NTARY NOTES J12, SPONSORING MILITARY ACTIVITY
AFWL (DYV)Kirtland AFB, NM 87117
"ABSTRAC . Distribution Limitation Statement AI Nondestructive evaluations were performed on various composite heatshield materialsbefore and after underground nuclear exposure. Qua'ity coiLrul riondestructiv,: eval-uations were used to select representative rings from a larger sample. Additicnalnondestructive testing and nondestructive mechanical (NDM) evaluations were used tocharacterize the selected rincs before and after exposure. Improved methods of.hAr... r....i.. Vir rTC aftr -- sure were developed and will be iruip- emiented inCarbon-Carbon Design Program. The materials evaluated included an angled, tape-wrapped carbon-phenolic (R6300); 3D carbon/quartz-phenolic (3DC/QP); 3D carbon-phenolic (3DCP); 3D car1 on-carbon (3DCC); and felt carbon-carbon (felt CC'. AllmatFrials were evaluate! before underground exposure. After, exposure the R6300,3DCC, and felt CC were evaluated. In the follow-on program, the two CC materialswill receive furtner evaluations.
R.L,,Idd, 'd 11V
r NATIONAl TLCI INICAIINFORMAIION SERVIC:F
U S Dp-r ... ,'-, TI (orNMeLUcV
DD NOV 147• UNCLASS I F I EDS~Security Cl0%sifiCation
IINf'.IASSIFT .Scecurity Claim = a fia, ~n
14 LINK A LIl'.K 1 LINK C
AOLE WT ROLC ST ROLE WT
Composite materialsNondestructive testingMechanical prcperties evaluationThermal propeTties evaluationuarbon-carbQ,'Carbon-phenol ic
, pUNCLASSIFIEDSecurity Classification
NONDESTRUCTIVE EVALUATIONS OF COMPOSITE HEATSHIELD MATERIALS
BEFORE AND AFTER AN UNDERGROUND NUCLEAR EXPOSURE
James R. Brown, Jr.H. G. Sanders
C. D. PearsSouthern Research Institute
Birmingham, AL 35205
Final Report for Period May 1972 through November 1373
i
TECHNICAL RFPORI NO. AFWL-TR-73-247
Approved for public release; distribution unlimited.
ibI
AFWL-TR.-73-247
FOREWORD
This report was prepared by the Southern Research Institute, Birmingham,Alabama, under Contract F29601-72-C-0058. The research was performed underProgram Elemenit 63311F, Prcject 62/A, Task 0, and was funded by the Space andMissile Systems Organization (SAMSO).
Inclusive dates of research were May 1972 throug.h November 1973. Thereport was submitted 22 April 1974 by the Air Force Weapons Laboratory ProjectOfficer, Captain John A. G~rdon (DYV)
This technical report has been reviewed and is approved.
GORDONCaptain, USAFProject Officer
ARL D. STUBER DAVID M. ERICSONMaJor, USAF Lt Colonel. USAPChief, Materials/Vulnerability Chief, Technology DIvision
ii
ABSTRACT
(Distribution Limitation Statement A)
Nondestructive evaluations were performed on various composite heatshieldmaterials before and after underground nuclear exposure. Quality controlnondestructive evaluations were used to select representative rings from alarger sample. Additional nondestructive testing and nondestructive mechanical(NDM) evaluatiors were used to characterize the selected rings before and afterexposure. Improved methods of characterizing rings after exposure weve devel-oped and will be implemented ii Carbon-Carbon Design Program. The materialsevaluated included an angled, tape-wrapped carbon-phenolic (P6300); 3D carbon/quartz-phenolic 3DC/QP); 3D carbon-phenolic (3DCP); 3D carbon-carbon (3DCC);and felt carbon-carbon (felt CC). All materials were evaluated before under-ground exposure. After exposure the R6300, 3DCC, and felt CC were evaluated.in the follow-on program the two CC materials will receive further evaluations.
iii/iv
CONTENTS
Paae
SECTION 1
INTRODUCTION ... ..... .......................... 1
SECTION II
MATERIALS EVALUATED ................. ...................... .. 3
AVCO 3D Carbon-Carbon (3DCC) _ ................ .............. 3Sandia Felt Carbon-Carbon (Felt CC). . . . . ........... 3AVCO R6300 3..........................3AVCO 3D Carbon/Quartz-Phenolic (3DC/QP) ......... ............ 3AVCO 3D Carbon-Phenolic (3DCP) . . . . .............. 4
SECTION III
APPARATUSES AND PROCEDURES ........... .................. . . . . 5
Nondestructive Testing and monitor Evaluations ..... ........ 5
Visual .......................... ..................... 5Gravimetric Bulk Density. .......... ................ 5Radiography ..................... ..................... 5Ultrasonics .................... ....................... 6Liquid Penetrant Inspection . ................ 7
Nondestructive Mczihanical Evaluations (NDM) ...... . . . . . 8
Ring Flexure . . . . .................. 8Hydrostatic C:-Tmpression . .................. 8
SECTION IV
DATA AND RESULTS ...................... .......................... 10
Nondestructive Testing and Monitors .... ......... . . . . . 10
AVCO R6300 . . . . . . ......... . .................. 10AVCO 3DCP . . ................. . ... . ..................... 11AVCO 3DC/QP. ......................... 12AVCO 3DCC .................................... .. . . 13Sandia Felt CC ............... ..................... .. 14
NondestrucLive Mechanical Evaluations. ...... ............. .. 15
v
I
CONTEI2'S - Continued
SECTION V
IMPROVED METHODOLOGY ............. ...................... 17
Eddy Current .............. ........................ 17Circumferential Segment Velocity ................. . ITurntable X-ray , . .. ... . 9... , . .Curved Coupon Compression . . .................. 18Ring Segment Testing .......... .................... .. 19
Ring Segment Compression (RSC) .... ......... . . . . 20R v . .. . . ..... .. . .. . . ( .. .. 2 0Ring Segment Results ................ . 20
Comparison of Ring Tests......... . . . . . . . . . 21
SECTION VI
ADDITIONAL EVALUATIONS ........... . .... ..... ................... 22
Matrix for 3DCC and Felt CC Underground Exposure and KamanSciences Equivalent Rings . . . . . . . . ...... . 22
vi
/7*
LIST OF ILLUSTRATIONS
Figure Page
1 AVCO Orthogonal 3D Carbon-Carboxi - Material 8 . .. .... 24
2 "(CO 116300 - Single Phase, 2D, 20-Degree AngleTape-Wrapped Carbon-Phenolic . .............. 25
3 AVCO Two-Phase 3D, Orthogonal, Carbon/Quartz-Phenolic-Material #15 ............... ...................... 26
4 SoRI Indexing and Orientation System for Rings .. . 27
5 Definition of Structure-Change Terms. ... ....... . . 28I
6 Ultrasonic Attenuation Setup Using the PulsedThrough-Transmission Technique ..... ............ 29
7 Schematic of Ring Flexure Setup Used for Modulusof Elasticity in Flexure (MOE) Evaluations . .... . . 30
8 Schematic of Hydrostatic Ring Evaluation Setup Usedfor Compressive Modulis Evaluation .... .......... . 3]
9 Photographs Showing Typical AVCO R6300............ .. 32
10 Thickness Variation for Ring 83301-305-1 from AVCOR6300 .................... ......................... 33
11 Sketch Showing Inspection Results on Ring 83301-400from AVCO R6300 .............. .................... 34
12 Sketch Showing Inspection Results on Ring 83301-305-4f[uin AV.CU R6300 ...... .................... ........ 35
13 Sketch Showing Inspection Results en Ring 83301-305-1 ifrom AVCO R6300 .............. .................... 36
1. Photograph Showing Outer Surface of Exposed Ring83301-305-1 from AVCO R6300 ........ .............. 37
15 Photograph Showing Typical AVCO 3DCP for Rings 1, 2,4, 8, 9, and 11.. ................ .................... 38
16 Photograph Showing Typical AVCO 3DCP for Rings83301-200, 83301-202A, 83301-305-2, and 83301-305-3 . . 39
vii
A
LIST OF ILLUSTRATIONS - Continued
Figure .Page
17 Photograph Showing Visual Revin-Starved Areas AroundRadials in Ring 2 from AVCO 3DCP ...... ........... 40
18 Photograph Showing Bumped Outea Edge on Ring 2from AVCO 3DCP ................ ..................... 41
19 PhotogrL-ph Showing Visual Resin-Starved Areas AroundRadials in Ring 8 from AVCO 3DCP ...... ............ 42
20 Sketch Showing Inspection Results on Ring 1 fromAVCO 3DCP ................. ........................ 43. . .
21 Sketch Showing Inspection Results on Ring 2 fromnAVCO 3DCP ................. ...................... .. 44
22 Sketch Showing Inspection Results on Ring 83301--200from AVCO 3DCP ...................... .............. .... 45
23 Sketch Showing Inspection Results on Ring 83301-202Afrom AVCO 3DCP ................ .................... 46
24 Sketch Showing Inspection Results on Ring 83301-305-2from AVCO 3DCP .................. ................... 47
) C; Sketch Showi.ng Inspeution Results on Ring 83301-305-3from AVCO 3DCP ...... .................... 48 f
1-
26 Photograph Showing Typical AVCO 3DC/QP for Ring 3. . . . 49
27 Photograph Showing Typical AVCO 3DC/QP in Rings83301-202B and 83301-305-5 .......... ......... .. .. 50
28 Sketch Showing In!-pection Results on Ring 83301-202Bfrom AVCO 3DCP/QP ............. ................... 52
29 Sketch Showing Inspection Results on Ring 83301-305-5from AVCO 3DCP/QP ............. ................... 53
30 Photogiaph Show'ing Typical AVCO IDCC ......... 54
viii
LIST OF ILLUSTRATIONS - Continuwd
Figure Pg
31 Sketch Showing Inspection Results on Ring 1109-35-2from AVCO 3DCC ................ ...................... . 55
32 Sketch Showing Inspection Results Qn Ring 1109-35-3from AVCO 3DCC ......................................... 56
33 Photographs Sho ainq As-Received Ring 1109-35-2 frc. iAVCO 3DCC After Exposure ................................ 57
34 Photographs Showing As-Received Ring 1109-35-3 fromAVCO 3DCC After Exposure .......... ................. 59
35 Photographs Showing Structural Change After Exposurein Ring 1109-35-2 from AVCO 3DCC . . ......... 62..
36 Photograiphs Showing Structural Change After Expcurs
-.in Ring 1109-35-3 from AVCO 3DCC .............. ........ .. 65
37 Fhotographs Showing Typical Sardia Felt CC . . . . . . . 71
38 Sketch Showing Inspection 1%esults oe- Ring 9N-2 fromSandia Felt CC....................... 72
39 Sketch Showing Inspection Results on Ring 9P-2 fromSandia Felt CC ............. ...................... 73
40 Photographs Showlng As-Received Ring 9N--2 fromSandia Felt CC After Exposnre ....... ............... .. 74
41 Photographs Showing As-Received Ring 9P-2 fromSandia Felt CC After Exposure ......... ............... ..
42 Photographs Showing Structural Change After Exposurein Ring 9N-2 from Sandia Felt CC ..... ........... .... 78
43 Photographs Show2.ng Structural Change After Exposurein Ring 9P-2 from Sandia Felt CC ............. .80
44 Curved Specimen Compression Test FixLure ... ......... .. 83
ix
LIST OF ILLUSTRATIONS - Continued
FigurePa e
45 Comparison of Initial Portions of Stress-Strain Curvesof Several Compressive Evaluation Methods on Felt CCMaterial ...................... ...................... 84
46 Circumferential Compression 3rCC Curved Specimen 5-0Supported Laterally,. .............. ................. 85
47 Circumferential Compression 3DCC Curved Specimen 4-0 -No Lateral Suoport Showing Cumulative Effects ofRepeated Loading ............... ................... 86
48 Compressive Modulus vs Strain History-Curved2DCC - No Lateral Support ............... ................. 87
49 Stress-Strain Curve for a 3DQP Curved CompressionSpecimen 4.ith Lateral Support ....... ............... .. 88
50 Schematic of Ring Segment Tension/Compression Fixture. 89
51 Felt CC Ring Segment Compression, Ring #1 .... ........ 90
52 Load Unload at 100% P/A Felt CC Ring #1 (Debug) ........ ... 1
53 Ring Segment Tensile/Comipressive Cycle of Felt CC . .. 92
54 Comparison of Cuip-On vs Strain Gage Data inCompression for Curved Felt CC Specimen 3-1-UnsupporLed. 93
x
LIST OF TABLES
Table Page
1 Evaluations Completed on Rings for the Underg.roundExposure Program. . . . ................... . 94
2 NDT and Monitor Inspection Results on A'TCO R6300 RingsBefore and After Underground Nuclear Exposure ......... ... 95
3 14DT and Monitor Results on AVCO 3DCP Rings BeforeUnderground Nuclear Exposure ........ ............... 96
14 NDT and Monitor Inspection Results on AVCO 3DC/QP
Rings Before Underground Nuclear Exposure ............ .. 98
5 NDT and Monitor Inspection Results on AVCO 3DCCRings Before and After ThLderground Nuclear Exposure. 100
6 NDT and Monitor Inspectior Results on Sandia Felt CCP-ingcs fBlnfn~ren -n cfe1 ne rgr rotr-,ndv~ E x -,- ur c. ...n
i7 Di-monsions of Underground Exposure and Kaman Sciences
Equivalent Rings ......................... ....... 103
8 Bulk Modulus of Elasticity for Underground Exposure andKaman Sciences Equivalent Rings ....... ............... 104
9 Felt CC Curved Compression Test Results (Fixed EndTest) ................... ........................... 105
10 3DCC Cuived Compression Test Results (Pixed End Test). . 106
11 Comparison of Clip-On Versus Strain Gage Data inCompression for Curved Felt CC Specimen 3-1 Unsupported. 107
12 Comparison of Modulus of Elasticity at DifferentLocations for 3DQP Rings ................... 108
Xi/xii
I
SECTION 31
INI RODUCT ION
Nondestructive evaluations weic performed on variouscomposite heatshield materials before and after nuclearexposure. Quality control (QC) nondestructive evaluationswere used to select represenLat3.ve rings fro:.:, a largersample which included specimens for both this program(underground exposure) and the Advanced He-tsnield ConceptAssessment (AHCA) program. Aditional nondestructive testi~ng(NDT) and nondestructive mechanical (NDM) evaluations wereused to characterize the selected rings bt;fore and after theirunderground nuclear- exposure. The materials evaluated includedan angled, tape wrapped, carbon-phenolic (R6300); 3D carbon/quartz phenolic (3DC/QP); 3D carbon-phenolic (3DCP); 3D carbon-carbcn (3DCC) and felt carbon-carbon (felt CC).
The underground exposure and the related AHCA program wereconcerned with the effects of hostile encounter as simulatedby nuclear exposure or flyer plate impact on the properLieso'f r- - ca...r- and ........ compubite2 heatshield materiais.For these two programs QC evaluations consisting of ulk density,visual inspection (witt, photographic documentation) and radio--graphy were completed on a total of 67 rings. Using the QCresults as a guide, ten rings were selected for application in
. the underground expsure, and six rings we-:e selected for moreextensive evaluations in the AHCA program. Results of the QCevaluations on the 67 rings arc given in Nondestructive,Thermal and Mechanical Pro eiesvauatons of Co____ste
HeatshieId Materials, PechnicalReport AFWL-TR-73-189 preparedfor the Air Force Weapons Laboratory.
I
An unexpected failure mode of the 3D carbon/quartz-phenolic(3DC/QP) rings and 3D carbon-phenolic (3DCP) rings during flyerplate testing at Kaman Sciences dictated a change in applicationof seven of the ten rings selected for thi3 program. Theseseven rings had received little more than QC NDT when theirapplication was redirected. Eight rings were supplied as re-placements for the redirected seven rings. Two additional rings(felt CC) had been designated for this program by SandiaLaboratories.
The test matrax, Table 1, outlines the specific evalu-ations compleced on each ring in this program. Seven ringsreceived only QC NDT evaluations. Thirteen rings receivedQC NDT plus additional NDT consisting of penetrant inspection,sonic transmission, and sonic velocity. An attempt to polishthe rings for photomicrograp~lv (40X) using trimethylpentane was
,msuccessful. These 13 rings were subjected to NDM evaluationsconsisting of hydrostatic compression and ring Ilexure.After underground exposure, 4 carbon-carbon rings were reevalu-ated using all of the previous nondestructive evaluations. ThreerC6300s were also reevaluated after underground exposure usingall of the previous nondestructive evaluations exceFt hydrostaticcompress ion.
During the course of these evaluations, the need forimproved techniques to determine material properties of ringsafter exposure to hostile environments became apparent. Newtechniques %jere developed and included compressive evaluationson a curved coupon specimen, tensile or compressive evaluationson a segment of a complete ring, eddy current evaluations onthe carbon-carbon materials, ciicumferential velocity of asegment of a complete ring, and improved X-ray techniques forring-
2
SECTIO)N II
MATERIALS EVALUATED
AVCO 3D CARBON-CARBON (3DCC)
Tlie 31PCC cylinders were orthogonal, three-dimensional, carbon-carbon composites manufactured by AVCO Corporation. Thecomposite was fabricated, densified by phenolic impregnation,pyrolyzed and graphit±zed. The construction of this materialis shown in Figure 1.
The 3DCC rings evaluated were identified as 1109-35 #2 and1109-35 #3 and received all evaluations before and afterthe underground exposure.
SANDIA FELT CARBON-CARBON (FE•LT CC)
The felt CC was a multidirectionai carbon.-cart,;on compositefrom Sandia Laboratories. A rayon felt carcass wa:a reinforcedLy needling, a process which pulled some of the tibý.rs throughthe thickness direction The carcass was infiltr•-td by vaporcdeposition and graphitized.
The felt CC rings evaluated were identified. as £N-2 aiod9P -2 and were evaluated using all NDT and 14DM before andalter the underground exposure.
AVCO R6300
The R6300 Composite was a single-phase, 20, 20-degree angletape-wrapred phenolic-carbon from AVCO Corporation. A t ofthe constr-uction of this material is shown in Figure 2.
The three R6300 rings evaluated were identified as 93.301-400, 83301-305-1 (#9) and 83301-305-4. All rings receiived NDTand NDM evaluations before and after the underground exprsue.
AVCO 3D CARBON/QUARTZ-PHENOLIC (3DC/QP)
The 3DC/QP rings were a two-phase material made of 3D,orthogonal, phenolic--graphite over a 3D, orthogona., phenolic-quartz manufactured by AVCO Corporation. The radials werephenolic-carbon. A sketch shczing the constructicn of thimaterial is shown in Figure 3.
3
The 3DC/QP ring identified as !DC/QP ring #3 received onlyQC NDT. Rings 8330i-202B and 83301-305-5 received full NDT andNDM evaluations before the underground exposure only.
AVCO 3D CARBON-PHENOLIC (3DCP)
The 3DCP material was a single-phase, 3D, orthogonal, phenolic-graphite identical in construction to the 3DC/QP material exceptwithout the phenolic-quartz substructure.
The six 3DCP rings identified as #&, #2, #4, #8, #9, and#11 received QC NDT only. Rings 83301-200, 83301-202A, 83301-305-2, and 83301-305-3 rectived the full NDT and NDM evaluationsbefore the underground exposure only.
4
AE!
SECTION III
APPARATUSES AND PROCEDURES
NONDESTRUCTIVE TESTING AND MONITOR EVALUATIONS
VISUAL - For virgin (unexposed) material, visual inspections(lx to 1OX) were made on surfaces to determine material macro-levEcl typicality and surface anomalies. This was effective fordetracting surface variations such as yarn bundle fraction vari-ations, separations, macrovoids, discolorations, resin-rich andrein-starved areas, yarn bundle wrinkling and spacing variatiuns,ply spacing variations, and void clusters. Results were documentedplotographically.I
• / For exposed (hit.) materials, visual inspections (lX to 1OX)Vere performed on the edges and surfaces of the specimens to
1 /ssess macro-level structural change. Results were documentedhotographically. Results from these inspections were compared
to those from virgin material for assessment of 6tzucLural/change. The Southern Research indexing and orientation :ystems/used to locate specific features are shown in Figure 4. Anrgular
locations witnout any additional designation are relative to the/ exposure centerline. Angular locations such as SoRI 900 areSrelative to the ScRI chosen 00 reference. Definitions of terms
used to describe structural change are shown in Figure F
GRAVIMETRIC BULK DENSITY - Bulk density measurements forspecimens were calculated froin direct measurements of weight'ýand dimensions. An a alytical balance having a senbitivity of±0+o-gram wa; used fc4ý weighing. Micrometers read to thenearest u.0005-inch were used for measuring lengths.
R-ADIOGRAPHY - Raigrnh wra pcfrme v'~-J4tAusing ~L~L~
art X-ray techniques for low-absorptive materials. The radio--graphic unit used was a Radifluor 360 manufactured by Torr X-rayCorporation, a division of Phillips Electronics. This unit israted for operation from 0 to 120 kv at either 3 or 5 ma, makingit ideal for phenolic and carbon-carbon type materials. Theunit incorporates certain characteristics that are essenti.aifor examination of low absorptive materials with high resolutionand sensitivity. The focal spot size is 0.35 mm, and the X-raltube window is 0.015-inch thick beryllium. A small focal spotsize provides high sensitivity and distortion-free imaging ofsmall discontinuities. Radiographic sensitivity using extra-finegrain film is within . percent (per MIL STD 453).
5
Operational and film development procedures were consistentwith conventional good rpdiographic practices. For example,image sensitivity and contrast was enhanced by using minimumpower settings for longer time periods. Sharp imaging wasensured by using extra-fine grain film (such as Eastman Type M)and by using a long focus to film distance (FFD) of up to 46-inches.Hland film processing in accordance to the film manufacturer'ssuggested procedure was used to assure maximum quality. Imagequality was checked using penetrameters from similar material.Penetrameter hole sizes used were 1/2T, 1T and 2T (1T and 2T holesas definced by MIL-STD-453). Radiographs were inspected in a darkroom using a high intensity (variable) spot illuminator.
ULTRASONICS - Basic apparatus used in the ultrasonicmeasurements of velocity and through-transmission are a SperryUM721 Reflectoscope and a Tektronix 564 Oscilloscope. Velocityis evaluated using the through-transmission, elapsed-time tech-nique. The Sperry UM721 is used as the pulser, and the Tektronix564 complete with a 3B3 time base (precision of 1 percent) anda 3A3 vertical amplifier is used as the signal measuring device.Transmission measuremerts were made using the pulse through-transmission technique with an in-line attenuator to simulatethe varying degrees of structural change. The basic apparatusesused were the Sperry UM721 as the signal pulser, the Tektronix564 as the signal measuring device, and a Kay Model 20-0, 41-dBin-line attenuator for asscssing relativu btructural change inthe various specimens.
In using the through-transmission, elapsed-time techniquefor measuring acoustic velocity, a short pu~se of longitudinal-mode sound is transmitted through the specimen. An electricalpulse originates in a pulse generator and s opplied to a ceramicpiezoelectric crystal (SFZ). The pulse genErated by this crystalis transmitted through a short delay line and inserted into thespecimen. Tiie time of insertion of che leading edge of thissound beam ii the reference point on the time base of the oscil-loscope which is used as a hiqh-speed stopwatch, When the leadingedge of this pulse of energy reaches the other end of the specimen,it is displayed on the oscilloscope. The difference between theentrance and exit times is used with the specimen length in cai-culating ultrasonic velocity. A short Lucite delay line is usedto allow time isolation of the sound wave from electrostaticcoupling and to facilitate clear presentation of the leadingedge of the entrant wave resulting in a more accurate "zero" fortime.
Using 0.5/1.0 MHz transducers coupled with alcohol, theprecision for this velocity measurement technique has been estab-lished for polygraphites such as ATJ-S as ±0.002 inch per micro-second for a 4-inch long by 1/2-inch diameter specimen and as±0.010 inch per microsecond for a 1/4-inch long by 1/4-inchdiameter specimen. High purity trimethylpentane was used as thecoupling medium for these evaluations.
In using the thrcugh-transmission technique for detectingstructural variations, Figure 6, sound is transmitted throughthe specimen and displayed by the oscilloscope. The gain ofthe oscilloscope is held constant and a calibrated step atten-uator located in the input circuit is used to maintain thedisplayed wave-form at a constant amplitude. Values of trans-mission (called added-dB) relative to a reference material maybe read from the step attenuator. Measurements are made in abath (trimethylpentane for these evaluations) to minimize effectsof contact coupling and near field effects. A suitable fixtureis used to align the transducers and to hold the specimen squarelyin the sound beam. When specimen geometry is such that part ofthe energy in the sound beam could by-pass the specimen, foampadding is used as a block to absorb this energy. The sensitivityof the calibrated attenuator is 1 dB with a minimum-maximum from0 to 41 dB.
LIQUID PENETRANT INSPECTION - Volatile liquids are used onporous materials such as graphites, phenolic and carbon-carboncomposites as a nondestruýtive test for surface discontinuitiessuch as gross porosity, wide density variations, large inclusionsand cracks. When a material is wetted with a volatile liquid,porous areas and cracks remain wet for a longer period of timethan the surrounding material. This differential evaporationeffect is discernible by visual observation. Although thistechnique is not quantitized (it probably could be), it iseffective in revealing surface discontinuities.
The v.lat-Ie liquid i"zipection procedure involves the
following:
1. Application of a volatile liquid to surface of specimenusually for 5 to 10 seconds. This can be done by flooding,brushing, or immeising.
2. Inspection of specimen surface as the liquid evaporates.Porous areas will remain wetted while the surrounding smooth areaswill dry. Cracks also will remain wetted depending primarily uponthe depth and width of the crack.
7
3. Record is made of visual observations.
This technique is useful in revealing surface discontinu-ities. Other NDT methods of inspection such as ultrasonics andradiography can be used in conjunction with the penetrantinspection to determine the extent of the surface discontinuityinternally. The volatilc liquid used was high purity, 2, 2,4-trimethylpentane.
NONDESTRUCTIVE MECHANICAL EVALUATIONS (NDM)
All rings receiving the full NDT evaluations also weregiven nondestructive mechanical evaluations. Two differentmethods were used b~iore and after the underground exposure:first-ring flexure evaluation and second-hydrostatic compres-sion evaluation. During these evaluations, the rings wereloaded to no greater than 20 percent of the ultimate strengthas defined by data from the Advanced Heatshield Program (AHP).
RING FLEXURE - A schematic drawing of the setup used forthe ring flexure evaluations is shown as Figure 7. The ringwas instrumented with four strain gages on the inside surfaceoriented in the circumferential direction. The ring to beevaluated was located between the crnssheads of a Tinius-Olsentesting machine. Three dial indicators were located aroundthe ring to measure radial deflections z.s shown in Figure 7.Strain was read using a Baldwin strain indicator. Load wasread from an internal load cell in the testing machine. Thering was loaded incrementally and all dial indicator and straingages read at each load increment. The ring was loaded to 20percent or less of its ultimate strength. The sequence wasrepeated at least twice with the arbitrarily selected NDT zeroorientation under the loading pad, rotated 45 degrees counter-clockwise and at 90 degrees to the vertical. Modulus valueswere calculated using classical ring equations.
HYDROSTATIC COMPRESSION - The hydrostatic compressionevaluation was run in a hydrostatic loading rig shown sche-matically in Figure 8. The loading medium was a thin wallrubber bladder which was connected to a hydraulic cylinder.The bladder was contained on the outside diameter by an cuterclosure ring and top and..bottom closure plates. The bladderwas contained on the inside diameter by the test ring and spacer
III8
rings. The spacer rings were sized to give an assembled heightwith the test ring in place which wai: 0.005 inch less than theouter closure ring. The bladder was oversized for the cavityin the rig and this combined with its thin wall ensured thatthe bladder supported a negligible portion of the hydraulicloading. The hydraulic system was filled and bled. Thehydraulic cylinder was loaded in a Tinius-Olsen testing machine.Load was measured by an internal load cell in the testingmachine. This was was converted to hydraulic pressure andstresses were calculated using thick walled cylinder relation-.ships.S~R2
SO = 2P ---2 2
R 2 - R
where
a = Circumferential stress at I.D.
P = Hydraulic pressure
R2 = Outside radius
R, = Inside radius
Strain was read using a Baldwin strain indicator. From thestress and strain values modulus was calculated using theHook's Law relationship:
- Ec
9
SE'CTION IV
DATA AND RESULTS
NONDESTRUCTIVE TESTING AND MONITORS
AVCO R6300 - The NDT and monitor results on Rings 83301-305-1, 83301-305-4, and 83301-400 are presented in Table 2 andFigures 9 through 14. Material background and before and after-exposure variations as indicated by vision, X-ray, and liquidpenetrants are also detailed in the table and figures.
Generally, the material background was similar to AHPR6300 material which was reported in "Thermal and MechanicalPrperties of Advanced Heatshield Resinous (CP) and Carbonaceous(CC) Composites" No. AFML-TR-72-160. Variai ns consideredtypical for the rings were residual porosity to 20 mils,Figure 9a, and reinforcement wrinkling Figure 9b.
The following results were obtained for before and after-exposure values of density, axial velocity, radial velocity:and radial transmission. For Rint 83301-305-1, the respectivevalues were 1.338 and 1.343 gin,/cm , 0.129 and 0.130 in./,lsec,0.127 and 0.114 in./ýisec, and 44 and 43 added-dB. Significantvariations in radial velocity and transmission were measuredin the exposed iing. For radial velocity, low values of 0.0887,0.0996, and C.1011 in./!sec were measured ag 00, 450, and 3150.
For transmission, low values of 34 and 35 added-dB were measuredat exposure 0". A slight variation in thickness was measuredfor the exposed ring. As shown in Figure 10, thickness variedfrom 0.4048-inch at 315' to 0.4132- inch at 90'. For Rincg83301-305-4, the respective values were 1.339 and 1.341 gm/cm-,0.128 nd 0.130 in./..sec, 0.124 and 0.124 in./psec, and 49 and48 added-dB. There were no significant local variations in thpdata for the exposed ring, including thickness variations aroundthe ring. For Ring 83301-400, the respective values were 1.340and 1.343 gm/cm3 , 0.128 an3 0.130 in./bsec, 0.124 and 0.].23in./psec, and 48 and 47 added-dB. There were no significantlocal vaiiations in the after-exposure data, and no significantthickness variation around the ring.
Visual, X-ray, and liquid penetrant inspections on the vir-gin ra1gs revealed a single flaw in Ring 83301-305-1. A 20-millow-absorptive area was indicated by axial X-ray close to the inneredge at 1800. The 00 orientation was designated to avoid this flaw.
10
Sketches sununarizing the NDT and monitor inspe'.tion resultson the virgin rings are given in Figures Ii through 13.
Some structural change was indicated in exposed R~ings83301-305-1 and 83 3 01-400 by visual, X-ray, and liquid pene-trant inspoctions. For 83301-305-1, the change was visually"apparent matrix damage on the front face (outer surface) ofthe exposed area, Figure 14. Also, increased porosity to adepth of 100 mils on the tear face (inner surface) of theexposed zone was visually apparent. For 83301-400, the onlychange detected was increased porosity to a depth of 80 milson the rear face (inner surface) of the exposed zone. Nochange was detected in Ring 83301-305-4.
AVCO 3DCP - NDT and monitor inspection results on virgin-Rings 1, 2. 4, 8, 9, 11, 83301-200, 83301-202A, 83301-305-2,and 83301-305-3 are presented in Table 3 and Figures 15 through25. Because of an unexpected failure in some 3DC/QP rings sub-jected to flyer plate testing at Kaman Sciences, work on somerings was stopped and application was redirected. Thedata presented include only the results from the virgin inspec-tions.
The material background was generally similar toAHP 3DCP reported in AFML-TR-72-160. For Rings 1, 2, 4,8, 9, and 11, the material had lower porosity and straightercircumrferentiais than the AHF material, Figure 15. For Rings83301-200, 83301-202A, 83301-305-2, and 83301-305-3, thematerial had an extremely high residual porosity along theradials, Figure 16. The reinforcement in both sets of ringswas workmanly placed.
The following results were obtained for virgin values ofdensity, axial velocity, radial velocity, and radial trans-mission. For Ring 1, the respective values were 1.406 gm/cm3 ,0,371 in./isec, 0.165 in./I'sec, and 25 added-dB. For Ring 2,the respective values vere 1.415 gm/cm3 , 0.367 in./lsec, 0.164
occurred before the velocity and transmission measurements weremade. The respective densities of these two rings were 1.409and 1.412 gm/cm'. For Ring 9, the respective values of density,axial velocity, radial velocity, and radial transmission were1.413, 0.366 in./Psec, 0.168 in./lisec, and 24 added-dB. ForRing 11, the respective values were 1.404 gm/cm' , 0.370 in./Psec,0.167 irn./psec, and 23 added-dB. For Ring 83301-200, the respec-tive values were 1.316 gm/cm", 0.284 in./lisec, 0.193 in./Psec,
11
and 30.5 added-dB. For Ring 33301-202A, the respective valueswere 1.317 gm/cm 0. 0.284 in.Ausec, 0.188 in./Jsec, and 26.5added-dB. For Ring 83301-305-2, the respective values were1.316 gm/cm3 , 0.285 in.A!sec, 0.190 in./isec, and 26.5 added-dB.For Ring 83301-305-3, the respective values were 1.321 gm/cm",0.281 in./jsec, 0.189 in./psec, and 28 added-dB.
Visual, X-ray, and liquid penetrant inspection (exceptliquid penetrant on Rings 4 and 8) were completed on alldesignated rings before the work stoppagc. No single flawswere revealed in Rings 1, 83301-200, 83301-202A, and 83301-305-3. For the other rings, flaws or anomalous materialvariations generally consisted of various indications of resinstarved areas around radials by vision and low-absorptivealignments by a:nal X-ray. These and other variations aredetailed in Table 3 and are depicted in Figuics 17 through 19.Sketches sununarizing the NDT and monitor inspection resultson Rings. 1, 2, 83301-200, 83301-202A, 83301-305-2, and 83301-305-3 are given in Figures 20 through 25.
AVCO 3DC/QP - NDT and monitor inspection results on virginRings 3, 83301-202B, and 83301-305-5 are presented in Table 4and Figures 26 through 29. Again, because of the .expe.tcdfdilure in some 3DC/QP rings subjected to flyer plate testingat Kaman Sciences, work on some rings was stopped, and theirapplication was redirected. The data presented include only theresults from the virgin inspections.
The material background was generally considered similarto AHP 3DC/QP material reported in AFML-TP-72-160. ForRing 3, the material had lower porosity and straightercirctmferentiels than the AHP material, Figure 26. For Rings83301-202B and 83301-305-5, the material had an extremely highresidnal porosity along radials and between axials, Figure 27.Also: for these rings, missing pivues of axials and circum-ferentials from machined surfaces and residual porosity betweenradials and axials at the inner surface were typical of thematerial, Figures 26 and 27.
The following results were obtained for virgin values ofdensity, axial velocity, radial velocity, and radial trans-mission. For Ring 3, the respective values were 1.476 gm/cm3,0.343 in./Psec, 0.166 in./Psec, and 30.5 added-dB. For Ring83301-202s, the respective values were 1.343 gm/cm', 0.287 in./Isec, 0.192 in./Psec, and 21 added-dB. For Ring 83301-305-5,the respective values were 1.354 gm/cm', 0.284 in./Psec, 0.192in./Vsec, and 21.5 added-dB.
12
UN -% fV4 U . l *J .*.t...o j • *y , .. !ml•,. • ,j.... *., ~..flf.6h.••., •. ,,.i.UbflinEI hflt • 'UP & -,'
No single flaws were detected in the virgin rings byvision, X-ray, and liquid penebrant. Sketches summarizingthe NDT and monitor inspection results on Rings 83301-202Band 83301-305-5 are given in Figures 28 and 29.
AVCO 3DCC - The NDT and monitor results on Rings 11.09-35-2and 1109-35-3 are presented in Table 5 and Figures 30 through36. Material background and before and after-exposure variationsindicated by vision, X-ray, and liquid penetrant are also detailedin Table 5 and Figures 30-36.
For background, the material was generally uniform, workman-like, and similar to AHP 3DCC material which was reported inAFML-TR-73-16'J. The exception was that the delams (also calleddebond and matrix rich areas) along the circumferentials weremore frequent than for the AHP matcrial, Figure 30. These delamswere uniformly distributed throughout the material. Also, missingzadials in machined edges were also typical of the material.
The following results were obtained for before and after-exposure values of density, axial velocity, radial velocity, andradial transmission. For Ping 1109-35-2, the respective valueswere 1.638 and 1.636 gm/cm3 , 0.375 and 0.363 ir./ldsec, 0.244and 0.218 in./vsec, and 1-8 and 22 added-dB. Systematic shiftswere measured between the before and after data; however, nosigniticant local variations were measured in the exposed ring.The variation in thickness around the exposed ring was onlyslight, Table 5. For Ring 1109--35-3, the respective valueswere 1.645 and 1.640 gm/cm3 , 0.377 and 0.356 in./gsec, 0.247 and0,237 in./psec, and 22 and 21.5 added-dS. Again, systematicshifts were measured between tne before and after data, but nosignificant local variations were measuted in the expnsed ring.There was no significant variation in thickness around the ring,Table 5.
Visual 7 X-rayi, and liquid penetrant inspections on ther ngoA~' rcVale n oj.Single -Claws. * uthLUzl ' bý'ULLUIdt iziny
the NDT and monitor inspection results are given in Figures31 and 32.
Structural crange was visually apparent in both rings.Photographs showing the as-received rings are given in Figures33 and 34. Generally, foz both rings, the. change consisted ofra.t.sed or recesse, and missing radials, cracking along loc&lpreexisting circumferential delanis completely aroiund the ring,
13
spalled sections of matrix and circumferential reinforcement(ciics) over radials in edges, yarn lift from the front face,and discolorations (dark) on the front face. These and otherchanges are detailed in Table 5 and Figures 35 and 36. Absorp-tion of trimethylpentane into edges of both exposed rings washigher in the exposed zone than out of the exposed zone. Theonly change indicated by axial X-ray was a 1-1/2-inch longcircumferential low-absorptive alignment at 3150.
SANDIA FELT CC - The NDT and monitor results on Rings 9N-2and 9P-2 are presented in Table 6 and Figures 37 through 43.Material background and before and after-exposure variationsindicated by vision, X-ray, and liquid penetrant are alsodetailed in the table and figures. For background, the materialwas typical Sandia felt CC and was uniform throughout. Residualporosity was to approximately 12 mils, Figure 37.
The following results were obtained for before and after-exposure values of density, axial velocity, radial velocity,and radial transmission. For Ring 9N-2, the respective valueswere 1.813 and 1.814 gm/cm-, 0.116 and 0.115 in./-Isec, 0.119and 0.117 in./jisec, and 51.5 and 49 added-dB. Local shifts inafter-exposure radial velocity of 0.1117 at 0' and 0.1100 at3150 were siginifiaunt variations. The variations in after-exposure axial velocity and radial transmission were systematicrather than local. A slight variation in thickness was measuredaround the ring. The thickness varied from approximately 0.497inch at 0' to 0.499 inch at 900 and 270'; Table 6. For Ring9P-2, the respective values were 1.830 and 1.830 gm/cm3 , 0.115and 0.112 in./ýisec, 0.117 and 0.118 in./psec, and 52 and 50.5added-dB. The only significant local variation was in thevalue of radial velocity of 0.1095 in./ sec at 3150. A vari-ation in thickness similar to 9N-2 above was measured for 9P-2.The thickness varied from approximately 0.4975 inch at 0' to0.499 inch at 900 and 2700; Tablh 6.
From the visual, X-ray, and liquid penetrant inspectionson the before-exposure rings, only axial X-ray was effectivein determining single flaws. For 9N-2, the single flaws re-vealed were a single skew low-absorptive alignment at 110 - 125'and a single 0.15-inch long radial low-absorptive alignment whichextended inward from the outer surface at 2550. For 9P-2, theonly single flaw revealed was a 1/4-inch by 1/2-inch low-absorptive area near the inner surface at 2250. Orientationswere designated to avoid these flaws. Sketches summarizing theNDT and rnonitor results are given in Figures 38 and 39.
14
No really significant structural change such as cracking"was detected in these two rings. Photographs showing the ringsas-received are given in Figures 40 and 41. For 9N-2, the onlychanges or noteworthy observations were that the exposed-zonesegment of the bottom edge was slightly more porous, Figure 42a,and the exposure-zone outer surface (front face) was slightlydiscolored (dark) and rougher in texture, Figure 42b and c. For9P-2, change and noteworthy observations were discoloration (dark)on top edge, 80 mil chip in top outer edge at 3150, higher porosityin exposure-zone of bottom edge, 20-mil voids in bottom edge at240 - 2550 and 2700, and material removal and discolorationin exposure-zone front face. These changes are detailed inTable 6 and depicted in Figure 43. Axial X-ray and liquidpenetrant inspection did not reveal any structural change inthese rings.
NONDESTRUCTIVE MECHANICAL EVALUATIONS
The two 3DCC rings an4 two felt CC rings which were exposedin the underground event and one ring of each material which hadreceived flyer plate testing at Kaman Sciences (called Kamanequivalents) weze all disassembled at Southern Research. Table7 summarizes diameter measureraents at various stages of assemblyand disassembly. It is interesting to note that the out-of-roundness figures indicate that the Kaman hit rings were moredistorted than the station 4, underground exposure rings whichwere supposed to have had similar energy inputs.
Table 8 contains the iesults of all bulk modulus evaluationsin the rings of the underground exposure program plus the tworings which had received flyer plate testing at Kaman Sciences.From the resu'.ts several conclusions may be drawn.
1. The modulus values of the 3D materials calculated fromdeflection measurements from ring £lexiu2e aLz yuiuelaily luwerthan for the other evaluation methods. (The more homogeneousmaterials, felt CC and R6300, do not show this result.) Onepossible explanation for the low modulus values could be theshear deflections which are probably increased for the 3D materialsover the more hoF geneous materials by the numerous small cir-cumferential delaminations which seem to be more prevalent inthem.
2. The moduli values of these rings seem to be similarto those measured in the AHP program on coupon specimens. Seethe last four columns of Table 8 for the AllP data range.
15
3. The 3DCC station 4 ring and Kaman ring seem to havesimilar retained moduli.
4. The felt CC station 4 ring and Kaman ring seem tohave similar retained moduli, but this conclusion is notquite as evident as for the 3DCC rings.
.1
16
SECTION V
IMPROVED METHODOLOGY
As this program on underground exposure rings proceeded,other Air Force programs had been developing, such as theCarbon-Carbon Design Program (CCDF), where other arcs andrings were being hit above ground by inag fliers and highexplosive. It became apparent that the underground ringsshould not be subjected to further tests an6 certainly notdestructed until additional tests could be developed using bothnoniestructive energies (NDT) and nondest 2 ructive (low stress)types of mechanical tests (NDM) that woul. not further damage thematerials. Therefore, the work on the unaerground rings wasstopped and this program was directed toward improving thoseneeded additional tests including eddy current (NDT), circum-ferential velocity (NDT), turntable X-ray (NDT), curved couponcompression (NDM), ring segment tension (NDM), and ring segmentcompression (NDM). All of the NDM tests may be used tofracture if desired. Recall that only the two carbon materialsare now available for further evaluations.
EDDY CURRENT
The use of eddy current evaluation on the two carbon ma-terials involvcda thc applization of an old ti=chZnoluO'y- in,'new way. In eddy current testing, a transducer (coil o-double coil) is held close to a material and couples to theworkpiece by the impedance resulting from the resistanceand reactanace of the material. Normally, an operatingmode is selected so that the measurement is sensitive tothe surface of the work and surface anomalies, such assmall cracks. However, it is possible to operate theequipment in null-reject and at a frequency such that itmonitors primarily the resistance of the material in depthor nearly through the thickness of a ring. This lattermode was chosen so that in-depth damaqe to a ring (fromshock loading) would be related to instrument output.Indeed, an extremely tight correlation has been found onarcs and rings for output versus impact level. Thisinspection method will be used on the carbon-carbon under-ground rings.
17
CIRCUM'ERENTIAL SEGMENT VELOCITY
Another NDT method was found that correlates the damagein the rings quite well-circumferential segment velocity.In this technique, the normal instruments for measuring sonicvelocity are used, but the longitudinal wave is introducedinto the ring over a circumferential segment about 3-1/4inches long. On shorter 2-inch arcs, the technique was notsuccessful and so was discarded; however, at the longer segmentlengths, good correlations are being found with damage. Thistechnique also is now being employed on the underground rings.
TURNTABLE X-RAY
In earlier work, axial X-rays were made on groups of arcsand on rings with the X-ray aperture at (and above) the geo-metric center of the general field of view. This has beenaltereC so that, in case of a ring, it is rotated under theaperture providing a direct path through areas (or cracks)concentrically positioned in the ring and on to the film in anormal, or 90' approach. Since the ring i3 r-otatd underthe aperture, the method is called turntable X-ray (TTX). TheX-rays are sharp and a picture of the entire ring can bepresented in peif-ct geometric reproduction for overlay com-parison between virgin and damaged material.
CURVED COUPON COMPRESSION
Circumferential compression coupon testing historicallyhas been accomplished using a straight specimen. This methodyields good results on an homogeneou's material; however, if theftLaterial is a composite with curved elements in the circum-ferential direction, results from straight specimens do notgive the best results. Moreover, the outer fibers of amaterial can not be tested using a straight specimen.
Testing a curved specimen has always given poor ultimatestrengths and poor estimates of other properties due tobending, which has invariably been associated with this typetest. To obtain good results from a curved specimen, thebending stresses must be controlled.
16
The technique developed at SoRY for compression consistsof testing a curved specimen with fixed ends and the option ofrestraining lateral motion in order to achieve 100 percentuniaxial 'P/A) stress. The apparatus used is shown in Figure44. The specimen is rigidly fixed in the grips so there is nomotion of the specimen ends relative to the grips. Thie gripsare inserted in a close fitting sleeve which allows only axialmotion; therefore, load to the specimen is applied only axially.This basic setup would still allow bending in the specimen andcould not achieve )ure compression. To restrain the specimenfrom bending a latei.l support at midspan is used.
This apparatus allows the lateral load to be varied duringa run; therefore, the capability exists of running compressiontests at any given ratio of P/A stress to bending stress thatis desired. Some stress-strain curves for curved compressionare shown in Figures 45 through 47 and 54. Strains on Figures 45through 47 and 54 were measured with clip-on extensometerslocated on the edges of the specimen so that the output was anaverage strain across the specimen. Figure 48 summarizes theresults obtained in the test fixture on the influence ofrepeated cycling on the initial modulus of curved 3DCC specimens.Figure 49 shows the results of a run on a 3DQP specimen withstrain data measurements from independent strain gages on thetwo curved surfaces. This run illustrates the close agreement
by using the lateral support.
Typical results shown in Tables 9 through 11 illustratethe difference in strengths for curved specimens which wereunsupported and supported. The supported runs were run atapproximately 60 percent P/A. (This value was determined ona later test).
The results obtained at 100 percent P/A are in good agree-ment with strengths obtained from ring testing.
RING SEGMENT TESTING
Ring segment testing was developed to yield improvedestimates of the elastic modulus of selected sections ofvirgin and degraded rings in a controlled stress field andwithout introducing further degradation. Methods used inthe early portion of this program were ring flexure andhydrostatic compression or tension. Ring flexure evaluationsprovide a stress field that is essentially bending and requireassumptions about the distribution of the modulus of the ring
19
since the entire ring is stressed. Ayarostatic compression andtension evaluations are somewhat sensitive to geometric andmaterial imperfections or nonuniformity and tend to give anaverage of the entire ring. By isolating the segment of thering under test from the remainder of the ring, the newevaluation method eliminates the need for distribution assump-tions and simplifies the data reduction methods.
Basically, as shown in the sketch in Figure 50, the entirering, except for a small arc on each side, is completely fixedin the fixture. When evaluated without lateral supports, themajor portion of the stress in the gage sections is bending.When properly applied lateral supports are used, the bendingstresses are reduced, thus giving a more uniform stress field.By using strain gages on the inside and outside surfaces, theratio of P/A to total stress may be determined and controlled.If the support is just firmly applied before testing, theresulting stress distribution is approximately 50 percent P/A.By adjusting the supports during a run, the ratio of P/A tototdl stress may be maintained at any level desired. Figure51 shows the results of tests for varying percentages of P/A.
RING SEGMENT COMPRESSION (RSC) - This test is run usingthe above philosophy. The outside support is used during acompressive run to maintain the pcrcantage P/A desired. itis important that support adjustments be made continuouslyduring a run and that they be removed continuously duringunload in order not to crack the ring due to side loading orbending stresses.
RING SEGMENT TENSION (RST) - This test is run essentiallythe same as RSC, the main difference is that the inside surfacesupports are adjusted to control the percentage P/A.
RING SEGMENT RESULTS - Some of the results from initialevaluations with the fixture are shown in Figures 52 and 53.Two cycles of a compressive load/unload run on a felt CC ringare shown in Figure 52. This run was made at 100 percent P/A.This figure shows that permanent deformations may be inducedand the effects on properties for subsequent loadings or thecumulative effects studied. Figure 53 shows the results ofload/unload in tension/compression on a felt CC ring. Again,the runs were made at 100 percent P/A.
20
COMPARISON OF RING TESTS - Two 3DQP rings were used forthis comparison. These rings were nondestructively tested byrinq flexure, hydrostatic tension and -ompression, and ringsegmnent tension and compression. The resulting MOEs foundare shown in Table 12. It can be seen from this table thatthe agreement of hydrostatic (pure) tests and ring segmenttests is good.
21gI
,21
SECTION VI
ADDITIONAL EVALUATIONS
The experimental techniques (NDT and NDM) described in theprevious section have now been demonstrated and are operable.Under CCDP additional data on the two 3DCC rings and two feltCC rings from the underground exposure program plus the ringsof each material from the AHCA program will be generated. Thefull program to be run on these rings is shown below and willprovide the final analysis to this program. Of course a portionof this work has already been accomplished and some of thoseresults are included in this report. It is extremely fortunatethat the underground exposure program permitted these refinementsand, thus, a better, eventual analysis of the results of under-ground nuclear exposure.
MATRIX FOR 3DCC AND FLLT CC UNDERGROUND EXPOSURE AND KAMAN SCIENCESEQUIVALENT RINGS
A. Nondestructive Testing (NDT): density, turntable X-ray,ecdy current, circumferential velocity, radial velocity, andracial attenuation.
B. Nondestructive Mechanical Evaluations (NDM).
1. Ring flexure.2. Ring hydraulic compression (buckle measurements).3. Ring hydraulic tension.4. Ring segment compression at 40 percent and 100 percent P/A.5. EME (Kaman test).
C. Cut to three subrings: 0.6 inch height, about 0.35 inch
height, and about 0.35 inch height; remove edge.
D. Prime NDT on each of three subrings.
E. NDM on each of three subrings.
1. Ring flexure.2. Ring hydraulic compression (buckle measurements).3. Ring hydraulic tension.4. Ring segment compression at 40 percent and 100 peicent P/A.5. EME (Kaman test).
22
F. Slice three subrings to in/out: 0.150-inch in and 0.150
inch outer.
G. Prime NDT on three subrings in/out.
H. NDM on each of in/out of each subring.
1. Ring flexure.f2. Ring hydraulic compression (buckle measurements).
3. Ring hydraulic tension.-4. Ring segment compression at 40 percent and 100 percent P/A.5. EME (Kaman test).
II I. Destructive evaluations on center subring (may add a hardtest).
1. inner: hydraulic tension.2. Outer; ring segment compression or hydraulic compression.
J. Destructive evaluations on end subrings.
1. inner: hydraulic tension or ring segment tension.
2. Outer: ring segment compression or hydraulic compression.
N~1DT of remnants.
Notes:
1. Key rings to arcs per other work before step 1.I. Key end point tests are on "center" rings; "edge"rings for additional information if uniformity allright.
23
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ReinforcemTent: Pluton B-1
Matrix: EC201 8.7 in. 0. D.I
Figure 2. AVCO R6300 - Single-Phase, 2D, 20-Degree Angle
Tape-Wrapped, Carbon Phenolic i
25
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V
To, Frige __ _,_,__ _
Bottom Edge __
900 2270"
S SoRI IndexSectiot• A-A
0o
A A
_900__ 2700
1800
Top View
Figure 4. SoRI Indexing ani Orientation System for Rings
Rear Delam -
Bulk Delain ý-
AidC Delan1
Rear Lift
Front Face Crack
Front Radial Recessiort(Bulk Expansion of LateralsToward Front Face)
Rear Radial Recession -=
(Bul~k Expansion of Laterals
Toward Rear I'ace)
Front Yarn Lift Raised or Misoing Yarn promFront Face
Rez~r Yarn Lift Raised or Missing Yarn From
Rear Face
Front Crush.....
Matrix Spall
Figure 5. Definition of Structure-Change Terms
Transmitting Transadcer
. Specimen
f-Bolding FixtureAlcohol ReeivinLBath Transducer
Trigger
Pulse Oscilloscope
Gen!rator calibrated StopeAttenuator
Figure 6, Ultrasonic Attenuation Setup Using the PulsedThrough-Transmission Technique
29
Moving Crosshead
Loading Pad
Test RingI
Indicators I
Strain
Stationary17 7/ Crosshead
Figure 7. .'hema-c, , i, g PLCAUDx. . Setup Used i'orModulus of Elasticity in Flexure (MOE)Evaluations
30
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36
Note: Matrix eroded and/or melted 270-0-75°
Radial View of Outer Su.face at 00(2x)
Figure 14. Photograph Showing Outer Surfaceof Exposed Ring 83301-305-1 fromAVCO R6300
37
IL
Note: Circuxnferentials(dgeVie straighter and- residual
(5X) porosity lower thanprevious AIIP material
Figure 15. Photographl Showing Typical AVCO3DCP for Rings 1, 2, 4, 6, 9, and 1
38
II•, I / I.I /1!//I
4. 62 6 9
Typical high residual porosity along radials
Axial View - Edge(3,)0
Figure 16. Photograph Showing Typical AVCO3DCP for Rings 83301-200, 83301-202A,83301-305-2, and 83301-305-3
39
Resin starved areasaround radials
Radial View - Outer -;urf.ce(1.5X)
Figure 17. Photograph Showing Visual Resin-Starved Areas Around Radials inRing 2 from AVCO 3DCP
40
Bumped C-190 resulting in localloosiLning of -reinforceme±nt-
si~ze.0,4 inch long
'Al ~
Z, pflt
VWI
YR: wA
4*
pg.Resin starved areas/around radials
Radial VioŽw -Outer Surfac.
Figure 19. Phot~ographi showij-Lrjc Visual Resin-Starved Aire-as ]Pround Radials inRZincj from A%7CG 31DCP
42
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Note: Workmanlikematerial simil~arto AHP 3DC/QPexcept residual.Porosity andw~aviness in circsviere lesforthis mat~erial
77-
a. Axial View
Local areashowing mnaxi-mumporosity
b. Axial View(lox)
Figure 26. Photograph Showing Typical AVCO 3DC/QP forRing 3
49
IllO% s iidit tIIIh!ffdthtII
Axial v~iew(SX)
Extrem'ely llichu~ Si Cresidual porosity
1 2 3 4 U 8along radials and
Axial View
(5X)
F~xtr~me2- ioh residual porosity
Figcure 27. N1otog)-aph ShOV~inq Typi cal AVCO 3DC/OPRin. T8cj3301-20ThB and 83301-305-5
50
Note: MissingjPieces of axial~sand circumrferen-tials typical onouter and innersurf aces
C. Radial View -Outer Surface(2X)
Between Onie Sideof Radial and
Axial -Typi cal for
Inner Surface
d. Radial View Innier Surface(No Scale)
Yiyure 27 Continued.
51
I 1.4
00
4 1-
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E CA41
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0q
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53
High frequency of delaminationsalong circurnferentials-uniforrnly
distributed throughout material
RII 4
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DA V61 r4
raised ai)located 285-15
a.Axi 1 Vic% Bot tomn 1dgc
- Mjý,s:&in se~ctionsof mat.riy ý> nc c'ircum-
e,(n i 'IF; ovel-r~idi a I ; I ocii ecl
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Ax iAl %i( w ll')t ioIIIJAY
(2. lX)j
Yi (JuY-c2 3'ý ~ ~'~oJriS huwinq~ Stl uctura J Change, After Exposurei) Rjnij ]109-35-2 from AVCD 3DCC
62
long circnrnferontialcrack located inbottom edge 0.25 in.from inner edge and a t.at 60-65"
C. Axial View -Bottomn Edge
(2.5$X)I
Front Yarn Li ftLocdted at 300-4'4
d . Radial Vicw -Outer surfacu at 0"(OX)
(.3
1-3/4 in. Discolored (dark)areas located at 75-9Q0 and240-~2550
RaI(dlal Viewv' Outei- Sul face
I iqoic 35 Continued.
644
Missing and raised radialslocated at 0-300
a. Axial View - Botto,-' Edge(2.5X)
Figure 36. P'hotLociralýh• -, howing St~ructural
Chan)ge After Expoos'ire in Hing1109 -35-3 from AVCO 3DCC
Ii
65$
900
Cracking Along Pro-existing CircumferentialDelaminations
C.
Axial View - Bottom Edge(2. 5X)
Figure 36 Continued.
66
Cracking Along Pre-existing CircumferentialDelaminations
e. 3150
Axial View-Bottom Edge
(2. 5X)I
F'iguire 36 Contjiiued.
r- , - - -- -
fH 44J
U ud
(4-)
QC)
(J68
g"
450
Cracking Along Pre-exLstinrg Circumferent ialD\lami nations
3 1
A>IxiaI V i, -w- -, Edc!q(2. 5X)
1jg ( Jm 3C Coni. i m(-c.
(,9 1
Front yarn liftI occ-ted300-0-600
70
a. Aial Vicw(5x)
Note:ResidualPorosityto about12 mils
1). RadiJal Vi~ew
(5X)
Figure 37. Photographs Showirg Typical Sandia Felt CC
71
01 0
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en -4 0
'-- u - L r
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M H4
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5- 0-'4 , 4)C) 41 '
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72
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77
Note: Bottom edge was slightly more porous at 275-0-450 location.
a. (00
Axial View - Bottom Edge(2.5X)
Fiýgure 42. Photographs Showing Stxtictural Changje iAfter Exposure ir,Ring 9N-2 from Sand~ia Felt CC
78
AP,
4W-~ .4
'44*
"AA
It-, -_* _ '.&
b. 00'1(Ce-ntered)
RadJial View-Outer Surfacc 15X)
-~~~ -f-Z .
-. 7.
C. 1800,Radial VieCw-Outer Surface (5X)
Note: Material i~n Outer Surface at 270-0-90"-was slightly discol-ored (dark,), andtexture was rougher.
I'igure 42 Cartf inuud.
79
Note: Nosignif~icantstructuralchange suchas crackinxg.
a. 00Axial Vic~w - Bottom E"dye
(2.,5X)
20 mil voids
240-2550 anO, 270"
kAxil View - ottuiii Edge( 5X)
Fi cu r e4 3.1 Ih,- t(- qra Ijh ; S hv m, nj n st-r;c i. u ra I Change AfterExpos ire in Rizin 9P-'-? from ,Sar~lia Felt- CC
80
outer edge at 3150
iI
C. 3150Axial View - Top Edge
(2.5X)
ligure 43 Continued.
0 0
ld 0 (13
o D .>, r-4 (r-4 04 4-J it C
U) looLflV 0,4- 0
r-0 Q)(d -1 - ,
>01
r-i ) DQ
m Fo
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Q)
d-,I X rd
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0
82
_ IL• •UIPPER Pusti Roj
HRDWARE
SALIoGENT SLEEV,•
/ - kSSEMBLY SUPPORI SCREWCUIED RETRACTED Fil RUN
- PIECESZ CA
I IN,
FOR DISASSEMBLY --WINDW TYPICA
IN 0.600 mh.
ILATERAL SUPPORT SCREWRETRACTED FOR ASSEMLY o,12 1., i
QSPECIMEN FRONT 'ijVIEWLOWER 3R I P
GRIP HoHLD-DowNHARDWANE 'j V
LOWER PUSH ROD
FIGURE 44, CURJED SPECIMEN CO•PRESSION TEST FIXTURE
83
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Zi~. '44 ¶'1' 11i i:7; i~, b~i ijjj n i ~ ___________ .
+1 t I
Load
Strap Attached Here With
LateralSupportAdjustment
Bolts
Used W•enMode of Testis Compressivej 4 -Used when Modc A
Figure 50. Schematic of Ring Segment Tension/Compre(sssion Fixture
89
IIC.-1
tD i
hir
00 LA0
LU-
- 0
03 90
z LAJ
C-0
N XJ
S LLU
I .14
ISd (1NI sSS~1j
- -il _-91
2:1C:C)
UCD
FF-
C)Ld:(C C)
LU -'~~-.
C CC:i f--:) C)
r-4I-
LUJ
LO LL.
CD-
cc a, Lfi
92/
W 0 041 (1 3 LD
EU
0)
m 0r04J
4-) m
UU
I i•-I• ,--u l
I-U]U I
o o
> 41
0 0v _u
93sd 014
93~
E I uoIvn~Guodwo
W1 EllT. 110~.241 P
EU u*F~u~uU2~ V1-11 -A 4
a V -3) r.I Vn crinu ____________ __-0 n i
v ciA inini u oTj ______ ____________
0n - - I--'04 Ex t
to .1 -,.- tn, rn
'4-13 -TO- a4-' Cn - -
-, "d -x '-4
-C ijd o 'NA' u- -' x, v
______4_ 1 SUO
& 6 J~ ~ ~~~' *~i
0 __
0 S~UI~nU~ N i L4__ __ __ _ __ _ __ _
o inT~XVin i
pri
Lo 0
U)~ C4s In-4~
'-5 01 1
'4.4 .'-4 I4I
CDEU Min ms I -imH 1 CL4
co mI co w. o .m .
-in A
.0 0 0 0
>N 0'' ' N -- N~~1
QI 0'Z4 L)I-4 n i
s aI Q-'-4 Ifn
in' ...... I n 04
(0 w
0 40 I
4< 044 ol w" Id D09 t'
4J -- .4. 744 .4030. 4 i% 1: 0.0 4 .40
-. 4 .O H.10 iL 0 I 4 0u
C4 1
o 4) 4 1 oik-H1
Ln 04
4)C "4 (4I.- 0 wO V) - .C i )0a i g .
DI o -. .>)4-~~~~~~~~~~~4~ ý c c0 0 .0 t ~ 4 0 0 mi 0 444 4 0 0'0.20.( ~~ 04.4020 4.02 04C'.4X404.'0 o4n'i )02 0 214 02 .240
4' 00oo>0 ., 0
'(0i 4 '-
Ud Wi -Gc 4i)14i- 4 4
r 0
140 4: 44
4) Ij N)~ 00
C. 04 -4.1V) L)- 00- -4 0-- .4 a4 . - a4.4 an -4 a, -' o ,. ý r''4 i.4- 0
141 r> C44 ~ ~ '. ~ 44 N 10 '4 iN 04 - N' 4 N' 41 H ) 0 .4 ~ flf-0----------0---0- 0
go 04
-4~~~~ ~~~ w4444.4 4-. . '.44-.44-'o~.t-.4-'4-oC-40)4000 ~ ~ ~ ~ ~ ~ ~ ~ ~ I w0' 04000 0~04400000 .- 40-ED ______- -v.- a, H a, 0)Im4-44 0w. F404-441 14444. 4 440~ 40 O4. 4 cN 4-- ~~~~~~~~~~~~~4 0440c' 44 0~ '4 4O~40''4'O4a 2*j 4400 c o t ' 44000444 o - . 4 4ua
440
HO0 w )
cr, (Q 40
'4 .444.4lCH. c4-4'4-44 0 0____________ m______*' 1).
95))
T~ABLE 3
NOT ANP1 N)IITOR kISUI•S ON AVCL )Mp 0 INGS llE'ORE UND9kGk UND NUCLLAR EMPO-pkE
Radial Ultr e
k Axlal Vloity Radial Velocity Trln~amialmc ThiicknelSiA Orientation (ad&" (tn,/BsT' ) | (ad ~d db) J Prefile Visual/X-ray, Liquid
142.4. __ . icA ~ 5 r O E Wtr ().n h) 4 Peneiran~t. Result,0 .0365 0.166 36'.5 .nkqr ... l t
S 0.36 7 0. 2I ! H3DCp reporte,' in!13ý o 3b9 0.)640 23 H
IU0164 0.. 362" ML-Tr .72-160.0.1633 I ,in
223 0.371i 0.163B 2.5 2 Pinfor•eeawt was wOrkeanly270 0.3735 0,1641 2?7 placd.315 0 !3687 0.16436 25 3. Material in Rings 1,2,4,6,9,Meand 0."13 0.0016 1.4 and 11 had lower porosity
.a end straighten ciýCz tha&n" 1,| 04 0,3695 0,1595 29.1 "HP mtarsal, Figure 15.
40 0.360 ,.1615 2" . Rings '3
0 305-300n905 0.36s0 0161"13 0.3650 0.1646 27 93301-202A, 8301-305-2, and9P3652 1646 26 |3301-305-3 had extremely
ISO 03675 0.1642 285 high remsdualz porosity along
220a 30 162! 28.5 radials, Figure 16.
315 0. 3719 001638 Before-EXpOaure VariationsaM. It0 0.16.7 2
4 d 0 .002 C.. 0 . 0 .6 1
45 1. Resin starved arasi arouo,d90radiate on otsr lurface by135 vision at followingI 10 locationm:225 So08 Oriep. Location from
270 (D.9.. Bott- Edge315 (in.)S4,, 0 £ 36-45 (.5 1 1.645 70 300 0.690 170 - ..5 bott-07op130 Fig~r. 17 sh-a typical1202-5 2. Vol-ue oriented low-aboorp-
'15 flue .1igrument. by aixal -MeAn X-ray located at SoRi
ad 15-655 and 70-1051.i.4i3 0 0.3562 0.1639 25 3. Sirmgle 0.9 inch long Io-
45 0. 3549 0. 1706 23,5 abiSOptiv alignmlnt at90 0.3539a 0.161" 22 S00 tC' by axialIX-ray13S 0.3571 0.ir• 24.F 4, Top outnr edge had beenS190 0,3563 0.1715 23 b-ep.cO remulting loal225 0.3516 0.1625 22 *atri /reinforcent inte--
270 0.3690 0.1714 23 face failure, Figure 19.315 0.3665 0.1748 25.5 Bumped area easured 0.4Mean 0. 353 r. 1600 23.5 inch.
ad 0.0064 0.0049 1.3
96
':ABLE• 3 CONTINUED
SORS0.I Orivnteto(r ladlned Frc"fite ViO.uai/-ry'. Liquid
F1e9 No. '.a fora ... Before Lfter (InchI Peantrant Results
•1~~~~ 1.03 .611J 0 )646 3,•in,:t~lrved areas sround
45 0619 0.16 23 rd nDO 0}68 ¢1172uSerfalr by visi-n at
10 0 68 0 1617 3.O1 .~B .W6s 23 Ollowine Iocatio~n.,
ISO 0.3673 0.1664 22 8R -ocatim2• .I 0.169a 25 Surface Orieaw. from bot•tom
270 1.1700' 0.17• 6 24M o- Eg i.
315 0.3735 0.1675 ,5Outer - 30 1.4
2M8an 0.397 0.1670 3 outer 20 - .30 .
0.0065 CIO00
IG ,0• 0,0•. nnar 70 0.3 - 1.1
23701-20 1,316 0 2362 0.1571 31 Ouat 160 - 1u0 t, r45 Q.2 073 0.1802 I 9 2.0.32 inch low-absorptive,
940 0.2034 0.1991 30. o1e
035 0.2r9 0.02o tad at Sol 20 by
I0.2810 0.160 2 ax X-ray
225 0.2832 0.20024 I1 .i
260 0.250 0.1931 31 1. 225in steved areas aro.nd2705 0.284 0.19 I radials, Pigure 1, on out2.3ean 0.2841 0:1914 25 a3.s ifaca by vllson located I370 0221.; 0.1893 21 295-10 5.5-1,9
Ii .15 0.2800 0"107520 52 Part througn-thickneda lOw-
40.0003 0.0052 1.2
3231.205-2 'I 3)6 0 0.2822 0.1906 2 t1d SeR4 10-45 -.
s45 0.285' 0.1170 53. sinle throug9-t0icknes0 1:-2.0 0.2855
290 0.2915 0.1851 ebslstved a2s 295-310
35 0.2900 0.,1510 2S Pattr9g-hcneslw
2d0 0.2 55 0.1852 3. lrdi.1l by aiaio Xo-rae sor-
315 '8, 0.1904 29f6. y iso
N~. 0 2981.10 2. 5-15" end 1 inch, firo bottOm0. ",0022 I 0,0033 1.5 *d1e 0
.1023 ý0.:8 '1 2 . Shiough throuhknes cnes low-
S83201-305-3 1,321 0 0,3775 0.9132.Truhtikeal-45 09380i 0.1813 39 absorptlve alignaente along
90O 0.2 055 0.1.75 27 radials at SoRI 135 , 1•00 .
2535 0.281) 0."19025 O . Rsnd starved a ria s X-ray. t
225 0,2613 0.1876 1 Miaing matri26
3270 0,703 0.18960 2nircemea t in outer *urfaos
315 0.2141 0,1 bv lo cateted So~l I65-200• nd
i Ite0n 0.2802 0.5-12 28 from bottor a.e to •.7 inch
ae 0L.002004 2.0 above botto1 edge by vision.
2. Volume oriented low-abeorp-
tive a elgn ment .a long
15 0 1 0 -S45* by axial X-ray.2 3301-200: N at .we r
S83303-202A3 No sufWc
V3301m30e-2ori nw aborptive
alignmenta by axial x-ray lo-cated SoRI 310-330-,
13301-305-3: No flawsDesignated Exposure Location:
O 1A ny* 2: SoRlI 2701* 4: See Note 2
03301-200: SoR0 3225
83301-202A: SoRI 90"
W3301-305-7: Sol 135183301-305-3: SOR! 90g
After-sxposaza Structural Change
Seo Note 1
Notes:1. No after-hit I'DT - Application redirected.
W Iork stopped and applioat.on redirected oan this ring after unexpected failure of 3DC/OP linge in
flyer plate testing at Kamen.
3. Trimethylpentane wav used an the liquid peretzant.
97l l
S-_ _ _
MU7 A210't*UIaMR XM8WnAC0IO SW7 ON&L VCG ADCfA0' O£26 "M £WMWm"NM WCL6M hDOM1 VI
.5"k Dsosty Ax-al %adecww 000"a %-.-awa . ... a5~.5 ~ 24~fL id Peunetrant'
to1 UU.N am~ .i- In ~ kar to Afll'
iNo 9-.. &JU. PAL-.¶-72lbfl2321 16.0164 a-Alm N *.sopt rw.1dualZN CU.m 3.W (1 oaltl A"d .&vines&an5 a. *AURP in cirs's W- lass vot
.5 .ai, mAmas ek2s1 64.223.2i 3.146 2
ov ~ IL. Rirt-orce,ýý L lay .q3AM 2"ffM ~ i 1.. workam like.
22 036 UIZa an Retsida mso~tnr~sl26 1.2972 A.3 422 t.9st Xials and laoný
6.633AD 4.Ol1. raials. 17. ewl highbSeem35- GAMA 3.~ U2363, 21 r. O.Ls" matrialysg
00.M21 2.167 V22 7 adb1. 4.423. 6191 29
Ms e.N .2686 ts 3. 4is*Aa§ pCe of axia1AJ.31 6.1754 O.iS a2 nd tire$ On immar *:d
RAW.261 12 21 OubwZ marfaaes.. ?Lours
225 :-U's9 :.- i'"6 22 21C.
none 244 10-M 21.
~~~~~~~~~t so .iJ.. s 6~6 i~ ~ ~ - ~ide of rad-
.Cse telyin . ,.
w~bol31 ing irsadi alnsis%
axia dsirection,-~5
2. ~ ~ ~ ~ ~ ~ fa-Epsr soStructM.muaia ..a1a. IL~e M
q_ - -- I__ ______
Va98e k LWI ewvrc.41n ~w
NOT MSD *I4? POR JNNSFECTIat RLSULTS ONl AVC 3DCC RINGS BFRU I~ FE 'LISUI ICERKPRR
ing N. "fr* Le addLjvk Vist formlty/ Liud stiu
5 1.31-1 :31:3 ..2"1'0' 0: ý2 21 ei-k-n 1kR 2151 10 ,I
270. 0 IT . 1,, 2 reprt d in e~~.i1, ý22. rtm-T - 2.-0 16 I* 0, ue 1I Spa7le4.et574.2o26s17r19
Ken 0.3," 0 6 .2,4 : 4. 22 Th.ra11 enc of .4wnc'c along
kh? '. und 30.oUno d I Ap. ,C: -Outrr 1 dnj4 :b8 ,'
1. Oc asinau,. Nfront :radilsf
Sato r! olud. atto'
I55 Ond I 2-A30 Figraa
"No Nparri flows. ichn
Otd - 55-170, Igon, ofL~OR Ivin'* -xo~r I i i L ± _
99~ioa
4OP
:A1,y
?,Cpl~t4
bestf.~=1t a.A~i~~ A~ ~A~~ ~d'4n h1~
01 - mu ?-(~L
t~~fl42 ~ 5Zd)82 **tr *SAM. t~ %Mk .1.t hi*Mn andOit aa4.ad Y"radittiMmia tikmw
ii~ ~ ~ ~ ~ ~~~A& 46) am.un .m 8.a .ai. fwtdS h),Fiua
235r , wiga I.110 &.1.AIM ga.37Im A2.1 2J0 ace at D0-'-305 Fig 360.
fad U-0012 0. no12 ,0" .OOP -.O3A 1.7 .2.4 6. n. a
.Amd isiminifl( *On of mai3,1mbetwomn *Wal aim boaed nleatV.omt, adg.W at 0-b.
qs Yctp 249.04 Caax'aI~yindicat~ions of.oa ),n gthin pza-anisUtittj
I 0 16a..e0cam'1attly aroundrinq with aeer*.t.? oCcurinq
and It0-7. Vgr.1
V'. Outear £u.fgat w Tfount garr "i,. oae
tlgura W9" 34 1
so .amrpner't OL~etutC3 chimgo
I o ta6u at 315',a
I ~ -_______ __ gAt
JOtýoo;
TABLE 6
MDT AND MONITOR INSPECTION RESULTS ON SANDIA FELT CC RINGS BEFOR AND AFTER UHUZRGROUND EXPOSURE
"" Radial Ultra AfterBulk Deosity Orien- Axial Velocity Radial Velocity Transmissio*n Thickness
ti ng Igm/cm ) tat!on' (in./uaec) | (n./sec) (Added lh) Profile Viau-l/X-ray/Liquid Penetrant'No. Bufore After (Deg) Before After I Before After Before After (inch) Results
9N-2 1.313 1.814 0 0.1153 I0.1131 I0.1197 0.1117 52 49 See note 3 flerkground.- 0.1135) - (0.1162) -- --
45 0.1157 0.1136 0.1221 3.1166 51.5 ;r.5 Uniform and typical Felt CC.90 o.1157 0,1161 0.1171 0.1cq 51.5 49 rFasidual porosity to approx.135 0.2174 0.1145 0.1145 0.1163 51 49 12 mile. Figure 37a anJ b.
180 0.1164 0.1131 0.1181 0.1199 51 49.5225 0.1171 0.1147 0.1212 0.1194 5ý 49.5270 0.1fl6 0.1166 0.1204 0.1077 52 49115 0.1166 0.1155 0.1177 0.1100 52 49Mean 0.1165 0.1146 0.1188 0.!1t6 51.5 45
ad 0.0009 0. 0013 0.0025 0.0038 0.4 0 ,2
I hbeforr- Exposure Variations:
1. Skew low-absorptive alignments
by axial X-ray located at !10 -125* 18ORt 30 -45")_and_1'0-
36.
2. Single 0.15 inch long Veiiallow-aboorptive alignment byaxial X-ray - extends from outersurface and located at 255'(SoRI 1751).
9P-2:Single 1/4 x 1/2 inch low-absorptive area by axial X-raylocated n. r inner surface t.ndat 2250.
10o1
IThOLE 6 CONTINUED
Radeil Ultra After
Bulk Density Orien- Axial Velocity Radial Velocity Trane Msaion Thickness
Ring (gm/cm') tetion' (in./wevc) (in./jisec) (Added db) Profile Vieual/X-ray/Liquid
No. Before After (Dag) Before After before After bafox. Aftea (ipch) Penetrant Results
-* - --.--.-- - __ _ T_ _
9P 2 1.031 1.,30 0 0.1109 0.1097 0.1180 0.1173 5215 s0 See note 3 SoRI Designated Exonsure £ ]J.ctlonz
45 0.1157 0.1089 0.116s 0.1114 51.5 61 I90 0.1146 0.1123 0.1136 0.1208 52 50.3 9N-2, SoRl 0.
135 0.1150 0.1134 0.1158 0.1186 52 50.5 Afte:-Expoaur• Structural Chanqe:180 0.1163 0.1150 0.1143 0.1171 52 51225 0.1176 0.1136 0.1154 0.1182 52 51 No significant structural change270 0.1173 0.1126 0.1161 c.1249 52 51 revealed. Material located on315 0.1136 0.1127 0.1235 0,1095 52 50.5 tie bottom edge at 275 - 0 - 45"Mean 0.1150 0.1123 0.1167 0.1177 52 50.5 was slightly more porous aý.pear-*d 0.0020 0.0020 0.0031 0.0044 0.3 0.4 ing, Figule 42a shows bottom
edge at 0*. Also, materiallokated in outer surfaca at270 - 0 - 90° was slightlydiacoloted (dark), and texturewas rougher, Figure 42b end C.
9P-2;A. Bottom Edge;1. No signifiCant 'hang- such as
cracking, Figure 43a.2. Porosity slightly higher due
to 20 mil and smaller voidslocated 270-0-90'.
3. 20 mil voids in surface(located
240-25
5-) and 2100,
Figure 43b.B. Top Edg.t1. No significant change such as
cracking.1. Entire edge showed streaking
discoloiatioli (dark) with moatappArent sccuring at 345-0-tO"
3. Single 80 mil chiip in outeredge at 315', Figure 43e.
C. Outer Surface:Material removal and discolor-ation located at eupoAure zone
approx. 270-0-90'. EffectsIr --- nt-- nucut fr=. tý-F •
dow.n to app~rox. 0.10 inch xobottom edge resulting in aridge of virgin appearingmaterial rýnnin• along thebottom edge, Figure 4Od and e.There was no significant change
in porosity or surface texturein the exposed zone.
D. Inner Surface;
No structural change revealed.Notes;
1. 9N-2 exposure • was at SoR! 260'. All other monitor data were measurd at 45- incrementsstarting at Soes 270- except as noted.
2. Trimethylpentane was used as the liquid penetrant.
3. Thickness profiles based on average valusa from measurements at 15-degree increments located1/4 inch from top and tottom edger and at center of rings:
Ri ng 1 2 7 " -2 W 0 0 . 3 1 5 3 30 . 3 4 51. .3 0, 0.6 * 59N-2 0.499 0414 0.4977., 0.4977 0.4975 0.4975 04974 D.4972 .4077 0.4983 0.4991 10.4991 0.4990
9P-2 0.4992 040090 0.4970 0.4961 0.4962 0.0968 .4975 .4970 .4967 0.4966 4.4974 0.4974 0.4992
102
0
-0 4 r4 mF pm r m e n p
1 4 o o~~ ooo .-iw Cr-4 -.... ' .. 10wMý
i.' ~ ~ ~ ~ ~ ~ 9 r oz f----t -, F--r-r f -r Ww-t ~
12 M ri
0~-~ ~ ~ n -. 4~.4.4 '~w.~ In..O 1 ŽI -rM~~
4) ______)___
4j -h m -" W
0~ 4 909 m ao gp% c 'ý '4h m m o a-mo q Nlo G N(0a 0 0 :
oD Go m am-4 m(
-0co ~~aoaio oo-0 ~000 o~~~
H ~ ~ ~ c Iý c! It 1aNWA IAOý~C -I7%
4) 0t , a
go IjOD -4 aooa]
o4 w-4 0000 ( 04
W__ &_ _ '41 ___ __
a)0 0 IC1 vU &~
43,.A M 0
o i i I4
103
w 4j
-6 u
do a , o.U a0 o
r. r
IIi04
TABLE 9
FELT CC CURVED COMPRESSION TEST RESULTS
[Fixed End Test]
Specimen G E E CI
psi 10 6 psi 106 psi in./in.
1-I 6530 1.22 1.08 0.02903-I 7520 1.34 1.10 0.03042-1 9170 1.29 1.11 0.0378
(Supported)
1-C 6570 1.27 0.97 0.02823-C 6300 1.10 0.97 0.02752-C 8350 1.23 0.97 0.0284
(Supported)
2-0 7000 1.27 1.27 0.03063-0 6820 0.91 0.85 0.03301-0 9220 1.27 0.96 0.0430
(Supported)
Averacies
Inner 7740 1.28 1.10 0.0324Center 7073 1.20 0.97 0.0280Outer 7680 1.15 1.03 0.0355
Supported 8910 1.26 1.01 0.0364Unsupported 6790 1.18 1.04 0.0298
Note:
E = Initial Modulus
ES = Secant Modulus at 1/3 o0.01
°0.01 Stress at = 0.01 in./in. Strain
Specimens run with lateral support had approximately60 percent P/A Stress.
105
TABLE 103DCC CURVED COMPR•ESSION TEST RESULTS
(Fixed Exid Test]
Speuimen o IE
psi 106 psi loa psi in./in.1-I 6780 2.28 -0.00203-1 6360 10.7 -0. 00083-0 9820 6.58 0.0018(Supported)
4-1 6450 6.20 5.9 0.00164-0 6200 6.9 - 0.00115-1 7420 7.2 - 0. 00125-0 12,450 15.4 -0.0016
(suppor ted)
Note:
EI = Initial Modulus
Es = Secant Modulus at 1/3 in.0[
a 0.01 Stress at = 0.01 in./in. Strain
Specimens run with lateral support had approximtely60 percent P/A stress.
106
TABLE 11
COMPARISON OF CLIP-ON vs STRAIN GAGE DATA IN COMPRESSION FORCURVED FELT CC SPECIMEN 3-1-UNSUPPORTED
Strain (p in./in.)
Stress (psi) Clip-Ons S.G. Convex S.G. Concave S.G. Avg. S.C. Bend
0 0 0 0 02000 1920 1225 3285 2255 10303000 3800 2045 6486 4265 20204000 6760 2912 1.1,275 7093 31815000 10,780 3629 18,865 11,247 7618
107
cf ) Lflifr- u -4 W O
F) . '. .' I
IID
* II ~I-m ONAD -4 mlIrti3
tm- w040 N 1r
(1 n0)r
"qt LW -M ..
Hv- rj.-I ~ 1~I-¶) ~Mf. l~f Ln m) U) N w n
4: m0 m~ (nl~ rl) enTV) M
lid ja0M- 0 rqk 0)m " % )"
K-4 4 in ('J'm.Q M
ID XU 4 )-4t~ý4
ti& -.4
-T M M 3 nt))N VVr
V) U)flU) U-o a) ~ ~ 0r- 0 0
M 'E-4 U E--iE-4 U E-4 UE-'0) UfLn lJ m U) w m w ) m Jc)U(:
S .H
.100
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