NASA TECH N ICAL NASA TM X-71521 MEMORANDUM (NASA-TM-X-71521) SECOND HEATED JETTISON N74-2054 TEST ON THE CENTAUR STANDARD SHROUD (NASA) 110 F HC $8.50 CSCL 22B Unclas G3/31 34366 , WIt 1i February 1974 February 1974 https://ntrs.nasa.gov/search.jsp?R=19740012431 2020-07-05T07:00:27+00:00Z
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NASA TECH ICAL NASA X-71521 MEMORANDUM · synthetic webbing supported by 6-inch-diameter aluminum pipe frames. The photograph in figure 3 shows the full-jettison catch net in position.
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NASA TECH N ICAL NASA TM X-71521MEMORANDUM
(NASA-TM-X-71521) SECOND HEATED JETTISON N74-2054TEST ON THE CENTAUR STANDARD SHROUD(NASA) 110 F HC $8.50 CSCL 22B
SECOND HEATED JETTISON TEST ON THE CENTAUR STANDARD SHROUD
Lewis Research Center
National Aeronautics and Space AdministrationCleveland, Ohio
ABSTRACT
The second in a planned series of heated jettison tests onthe Centaur Standard Shroud was conducted at NASA Plum BrookStation's Space Power Facility on January 16, 1974. Thefirst 250-second portion of the test sequence involved heat-ing the shroud with a specially-built fixture designed toprovide a simulation of the heating environment encounteredby the shroud during its ascent through the earth's atmos-phere. The two heater halves, which were mounted on a railsystem, were then retracted. This was followed by the jet-tison of the two shroud halves into catch nets positionedat 900 to the heater rails. The condition which made thistest unique compared to the others in the test series was thealignment of the maximum thermal line with the shroud separ-ation plane. Information on the test hardware, configuration,and sequence is presented. Shroud thermal and deflection data
o encountered during the heating portion of the test sequenceis compared with free-skin design temperatures in variousgraphical formats.
i
INTRODUCTION
The Centaur Standard Shroud protects the payload of the Titan-Centaurlaunch vehicle during the ascent phase of the flight. To conserve weight,it is jettisoned as early in the flight as possible, while it is still hot
from aerodynamic heating. Analysis of the possible flight trajectories and
the shroud structure indicated that severe internal stresses could be built
up prior to jettison. Calculations of the edge motion of the shroud duringjettison indicated that the design clearance between the shroud and the pay-
load could disappear, in the worst case.
An experimental program was conducted in the Space Power Facility at theNASA Lewis Research Center to verify the computer model of the shroud jettisonevent. The shroud was heated to simulate the expected 280-second flighttrajectory then it was jettisoned.
A seven-megawatt, radiant heater was assembled in the vacuum chamber ofthe Space Power Facility. The heater was programmed to produce the desiredtemperature distribution with the plane of symmetry aligned with the separa-tion plane of the shroud. Fdllowing the 250-second heating cycle the heaterwas pulled away to allow the shroud to be jettisoned. A special catch net
system was built which allowed one half of the shroud to fall completely freecf the launch vehicle while the second half rotated approximately 160 beforebeing caught. The test was performed in a 20-torr environment.
Deflections of the shroud were measured during the heating cycle withstraingages and deflectometers. Thermocouples measured the aprlied thermalcondition. High-speed motion picture cameras were used to record the motionsof the shroud during jettison.
It is the objective of this report to present a brief description of thetest hardware, the operation sequence and the results of a preliminary dataanalysis.
APPARATUS
The overall arrangement of the test hardware in the Space Power Facilityis shown in figure 1. The seven-megawatt heater was built in two halves thatrolled on rails perpendicular tc the facility rail system. The Centaur shroudwas mounted on a Titan-Centaur interstage adapter. Its location in the 100-foot diameter chamber was chosen to allow one half of the shroud to fall com-pletely free of the hinges before being caught in the net. The other half(the one with the dome) was caught after only 160 of rotation. The Centaurtanks were not used in this test because of the unnecessary complexity theywould have added. In their place, a special structure was mounted on the
1
interstage adapter that allowed access to the inside of the shroud and supportedthe flight truss adapter, equipment module and a simulated pay-load. A photo-graph of the internal structure is shown in figure 2.
Catch Nets. Special catch-nets were constructed using a high temperaturesynthetic webbing supported by 6-inch-diameter aluminum pipe frames. Thephotograph in figure 3 shows the full-jettison catch net in position. The
full jettison net frame was supported by cables attached to 10 disk brakes(five on each side) which served to absorb the energy imparted to that shroudhalf. The catch system was pre-tested using a model of a shroud half to in-sure that it would function properly without damage to the shroud.
Heater. The heater was designed to duplicate, in time and temperature, thecondition expected in the ascent phase of the flight. The heater contained5910 tungsten filament lamps inside a highly polished aluminum reflector. Adetailed thermal analysis (the approach used is described in ref. 1) andextensive small scale tests were performed to verify the design concepts.The heater was divided into 18 separate control zones, 11 in the cylindricalsection and 7 in the biconic section, to provide the proper circumferentialtemperature profiles. In addition the spacing of the lamps was varied withineach zone to control the vertical distribution of heat. Because the desiredtemperature profiles were symmetrical around the maximum heat line, the 18control zones were further divided into mirror-image half-zones (one on eachside of the plane of symmetry). The arrangement of the control and mirrorimage half-zones is shown in figure 4. The maximum heat line for this testwas at an azimuth of 00 (00 from the shroud separation plane).
Control Systems. Each control half-zone and its mirror image was powered bya separate SCR controller. The 18 controllers were programmed individuallyto reproduce the expected temperature vs time curve for their respective con-trol zones. Abort limits were established to insure that the test would notproceed if any control half-zone or mirror image half-zone deviated more thana prescribed amount from its desired temperature curve.
A PDP-8 mini computer was used to conduct the test because of critical timingof events necessary. The sequence of events for this test is presented inTable 1.
INSTRUMENTATION
Thermocouples, straingages, deflectometers, and high-speed motion picturecameras were used to measure the performance of the shroud during the test.Digital data were recorded every second during the test, using an XDS 930 com-puter. FM analog recordings were also obtained of selected parameters. Thecoordinate system used to define the location of sensors on the shroud isshown in figure 5 and 6. The cylindrical section of the Centaur shroud is acomplex structure composed of a corrugated outer skin bonded to a smooth innerskin supported by circumferential "Z" rings. A sketch of the structure anda typical free skin thermocuple installation is shown in figure 7. Free skinthermocouples were located as far from structural masses as possible to pro-vide the best possible measurement of the thermal environment. Free skin ther-
2
mocouples at station 2626 in the cylindrical part of the shroud, and atstation 2724 in the conic part were used to provide temperature feed backto the power controllers.
RESULTS
The heated jettison test was conducted on January 16, 1974, at anambient pressure of 20 torr. The heater was programmed to produce the de-sired temperature distribution with the plane of symmetry displaced 00from the shroud separation plane (see figure 4). -The light half of theshroud (the one without the dome) was fully jettisoned and fell free of thehinges into the horizontal net. The other half was caught after only 160of rotation.
Time histories of the control thermocouple readings are presented infigure 8 for the 18 control half-zones and the 18 mirror image half-zones.Included also on this figure are the desired temperature histories. Com-parison of desired and measured temperatures shows that excellent agreementwas obtained. The greatest deviation was in zone 10 where a 100 F deviationwas observed in the mirror image half-zone. The instantaneous power appliedto the shroud varies according to the slope of the desired temperature curve.The measured power applied to zone 1 is presented as an illustration in fig-ure 9. The initial peaking power occured because the shroud was cooler thanthe set point when the heating cycle started. The power increased gradually,following the desired temperature curve. Very little power was needed nearthe end of the cycle because the required temperature was actually decreasingslowly.
Circumferential temperature profiles are presented in figure 10 at severalstations and for several times during the heating cycle. Also shown are thedesired temperature profiles. Comparison of the two indicates that very goodagreement was obtained everywhere except at the top of the biconic sectionand at station 2250. The thermocouples at station 2250 are very close to theaft seal bulkhead which probably accounts for their low readings. This is6upported by the fact that a thermocouple at station 2469, where the shroudskin thickness and the lamp spacing were the same as at station 2250, agreedvery well with the desired curve. These deviations were observed early duringthe heater checkout tests and were deemed acceptable.
The shroud deflected during the heating cycle because of temperaturegradients of as much as 900 F in the "Z" rings. The deflection was measuredwith potentiometer type deflectometers. Circumferential plots of theirreadings at several stations and at several times during the test are pre-sented in figure 11. For reference purposes the desired temperature curvesare also included in figure 11. Examination of these data indicated that theshroud assumed a pinched cross section with the narrow part at the shroud sep-aration plane. The tendency for the shroud to pinch this way is resisted bythe joint between the two halves. Consequently, when the shroud is separatedthe first motion is expected to be inward. Edge motions of the shroud wererecorded by high speed motion picture cameras. At the time of this writing,the cameras data had not been fully analyzed and could not be included. How-
3
ever, it was observed that the first motion of the shroud edges was inward(about 31 inches) toward the payload. In addition to the cameras some shortwooden sticks mounted in foam blocks were installed to indicated invasion ofthe payload envelope by the shroud. First inspection indicated that the pay-load envelope was not invaded.
Examination of the camera data also revealed small objects (tape-likein appearance) being blown off at high velocity from the Super*Zip near thehinge in Quadrant II (at approximately 1000 azimuth).
CONCLUSIONS
A successful heated, jettison test of the Centaur Shroud was performedin the Space Power Facility on January 16, 1974. The shroud was heated tothe desired thermal condition with the axis of symmetry displaced 00 from theseparation plane. Initial observations indicated that the shroud's firstmotion was inward but that it did not invade the payload envelope.
REFERENCE
1. Hemminger, Joseph A.: Computer Simulation of Temperatures on the CentaurStandard Shroud During Heated Jettison Tests. Paper presented at theSeventh Space Simulation Conference, Los Angles, Calif., Nov. 12-14,1973.
Table 1.SEQUENCE OF EVENTS
Event Test Time
Start all recorders. -10
Verify recorder start. - 8
Start heating cycle. OVerify heaters started. 50 to 80
Color movie lights on. 160
Color cameras on. 165
Safe zone heaters. 250
Start heater retract. 250
Turn on movie lights. 272
Check heater clear. 272
Start cameras. 272 to 275Arm seal pyro. 275Fire seal pyro. 276
Verify seal pyro fired. 277Arm instrument disconnects. 277
Fire instrument disconnects. 278
Verify instrument disconnects fired. 280
Arm Super*Zip for shroud jettison. 280
Fire Super*Zip. 281
Safe all systems. 295
Stop all recorders. 300
5
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Figure 1. CSS in jettisoned position (view looking north).
Figure 2. Photograph of internal structure.
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PFLO N- HUiWR 06 TIIE VS E IIO-'--ZOE 09 FST. PT.B16 13 10 10 857 Figure 8.17
10n00 tH- H I -- Id I +$ I Hp I f fH - +---- -- --1 t HA I I 1 o. 10000
08. B I ---l-- I I- - I- -l----4l- Control -I-I -- -- I-i+--I-- +-+- +- -- t- - -i I-- 00 8
-Io. B -- - -- 4 Control hermocouple - I. I : 1-- -100.00
5 Design Temperature6 Data Thermocouple
-2'0t 0 H I--t I I :---1 t :I I I I , , , , I I I I I t. I-I I I I I I If I I I I I -l- -t -- l -I- I I - I I I I I -200 :- 1 "
S- (s 50.e13 I . C10 O. 20n.1 0 .00 3 0, 00 35c. Or I f,- ,11. 3Time (seconds)
lIF C':. I'1 RIUN 483. 0 DEG SEt!. I 1HE tIED 11- I ISON TIME DfiY FIR MIH SC MillIF'.C1 ll.; :. R 08 TI f: VS TEP'-ZONE 09 - FST. P1.016 13 .I 10 85/ Figure 8.18
- -. - l -I I I- I I I F I I I I I t f-I I I - - I I I I I I l- - - -- - I --I I--I I --- 1----i I-I I I I I I I -2I0.00tlData Thermocouple i--f '---- H' - I il 3. CID -U
irror Half-ZoneF Design Temperature -- H- I -1000ee
--.. H- +- G. Data Thernocouple
--2 : I--I I -1 1-i I -I I I- i I 0 C T i2 T 1 t- I AII II I200 0. '"00 1 0 3 50 1 i:50 ) 20 i. -:. 00 00.O Oi 4 t :.00
Time (seconds)
' T C t.T RUN '1.. - DFG - I HER 1 D I1-1 1i so4 TIME lIY HIR NIH SI.C 1111 IPL0OT HlliIL'.:R 06 I llMC- VS IEM i'2-OE 13 - FST. Pl.0l16 13 10 10 85,' Figure 8.25
2 (739T) 4 (126T) s(Design) 6 (127T)
. .' 50.000 1000 50. 00 200.00 2 .. 0 300.00 350. 00 400. 00 450. 00500.0 l - I-- IiI - -I I- -- I -- I - I i-1-1-I
- I :--1 -I-- I I -- I I I 1-- I-I I -l -I I I f-I- I1 I I - I 5-0. 00
400.00 -I- I -I -I -I I - -- - - I --- I - -I - l --- I--I I I I- -H -- I - I -I I I --- -- I 00.00
3 0. N000 -H 1I-II I + -t lF+-- - - 4--- - - -- I F - 1--I-I I 1- 200. 00
1 I00.-00 -f---|- I H -A - - - I----- -- +-- - -- I-I-----
--.- I- - - . + - -- --- - - - 100. 00
Control Half-Zone
2 Programmer Signal Temperature- 00 -I I 1:-4--+- I 4 Control Thermocouple - 1 I-I---l--I-I-- -I -- I-- I- -I-I-I I I f- -160. 0
5 Design Temperature6 Data Thermocouple
-200. ' - - -I I I I I I I I- : I Ii -II-I I I I -( I -- -1 I I - --I-I i1 -I- I -- I- I- I -I I- I I II i !-I I I 2 - 0 .I00
100 000 10 00 150. o - 200. CI +0. Io I00 00 50. 0-F ' H 01
Time (seconds)
SPI CSs5 ST RUN 4', 0 DEG SKEI HE ED .!ETT IISN TIME DnY HR IIHN SEC MILL
'1.0T lI. IR 08 1II1F VS TEMI-ZONE 13 FST. PT.016 13 10 18 85? Figure 8.26
k j SO 00-0e 00+ 00, 0oOA(0.1A 0 0 2051 f 00 alto. 00 3Y 0040. k' 4 0
S'.1-' 1 ' T RUN ,18, DEG SK: I.1 HEfltED J-l1 ISON TIME T:TY FIR i111i SEC MiI IFI.hI . -:tR 14 TIIME VS EMIi--ZONE 14 FSV. PI. 016 13 10 18 857 Figure 8.27
-v ej ra - --I+ I+ -. 4- -A4I- I -1-1-+.- -.--- A Programmer Signal Temperature F+-+.--I - --- -: - F- -I-I I ----- I I - -1 - 0o. 0C Control ThermocoupleD Design TemperatureE Data Thermocouple
• - .C -II1 I -- 1 - I I 1 ! , --I I , I - I-1 - I -: -I - 0 u
SF ::-. ' LT RUN 13. 0 DF.G SFI'..l HEALED JETIISON TIME DflY HR MIN SEC MILLPLOT :: .:IR 06 TIl1[ VS ItHIf-ZONE 15 FST. PT.016 13 10 10 857 Figure 8.29
2 (741T) 4 (136T) 5 (Design) 6 (137T)
. . 50 L00 100.00 150. 08 200. t0 250.08 308.08 358.00 400.00 45. 005 .00 L I :- I I 11- I I-i I I i i -I I I - - I --I-: I 1- I- 1- I1l 1-1- -1I-- -- I -- -H F --IH i -1I4 +1 --I 5ea.402
400C. eO00- ++ - 1 1 -IfA I F-HI--- H---- f-- H- 1 -"-+-.FF F-1 1 1 -1- I I I - -H------1- +- I-- 1 + -- + - - 4. 0'
-1o. F I- --1- --- --I-I-l -1, 4 Control Thermocouple [+--1- - - -- 4 I :-- -A -I-- I I I - 0o.ea
5 Design Temperature6 Data Thermocouple
,i T, I , ,i ,1 1 -i i i i T :-I I I I i I -2 (.s cel50!51.0 00 150. CO 20 10 2 , 00 :0l0 [IL 350 S. 00 0 .03
Time (seconds)
;- C '. T RUH -I,.. O DE G S'l-i, HEI lED JET. IISON TIME IrY HR lMI: SEC Ml I.fLOT NFi; R 18 3 i VS I EM ZONE 15 FST. PT.016 13 11 10 857 Figure 8.30
7 (Design) 8 (172T)
5.; :: 50.008 100.80 150. 0 20. 00 250.00 300.00 350.00 400. 0O 450.00500.++t 1 C-' I- I- d I IA - I - I -- 1- I i ,- 1 -- 1 I -L- I I II-- I I I I -I- I I- I I I +( -+I I I1 1- It 1- 500.00
500. 1 - I : 1-I l 1 1 -- 1 1 1 1 1-i- I I I I -- I I I - I -- I 4- II-I-I I -1 -i --I-f - - - I I I- I-+-1-- 1 I-- -++ ft I--- --- 1]-- I >-t---: -l-l-I- 1- 500.00
400.00 r - - I-- I -I - I ---- I- l-I--t-+ I I--I- + l----t I -f- 4I-+1t H-Hi-- - I- -~ -H - -I+-I .I-H-- - I-f --.--- t-I-+ + - -I-i---I--- 1-! +-tt -I--I- I I---I. 400.00
- rrvu.I} Ttfi IfF ~TillIbIIlif-lG G G G EFFfTlIlW
Control Half-ZoneA Programmer Signal Temperature0. l- I- I-I- FFI--I - -+ -- 1-I C Control Thermocouple -I- - -I---I I- -l--I-.- -I-I ID Design TemperatureE Data Thermocouple
:50 • 000 1 .0. O 3 150 00 2F10. 0 2:7 . 00 300.6 ._ 1 E r -1 .
Time (seconds)
'1 US'; I T RUN 41.3, 0 DEG SKI. I HEIIED JLTTISON TIME DNY HR 11111 SEC MI.LPL 01 Hi.:;:I R 16 1 li11 VS TEHI" ZONE 18 FST. PT.016 13 10 18 857 Figure 8.36
-100. 8 1 I-3-- I- -I -- I-I--1 - - F Design Temperature -- ------ I I-+-- -l--- I-f-----F---II-- +--F-I--I---I --+l100 O0G Data Thermocouple
-200. 01 1-lI il- !-. 111 ! - l I l I-I:-AI+-1II 111 I-ll I - + i I-- 1 A III I14 t-1- . IT Il - I fI i I f- -230 CO. IO 50 800 100. 00 150. 0 200. 00 200. 00 300.00 3500 400 00 45u. 00
Time (seconds)
Figure 9.
Power history for heating zone no. 1 power controller.
t
Si'F ESS I;T RUN VS. 0 DEG S5.C I[ L it TISON TIME D:Y HR FMIN SEC MNI..PLOT NU :': R 01 111 VS FPO O: : ZlUN 1 (I S.M.7:6) FSf. PI.IIG6 13 10 10 857 Figure 9
i
5.M 1 5 000 30I 00 . 350. 00 40".( 4r'. 000.r i-i- l: I-- F l I--I.l I - I : I - 1I : .- -- I I : - 1 j-- ; . - - I- - -I : $r.0p7 1 _ * .
.i -I -I I--H--- -l i I- .- -I--- I--I
.-- I-I- 4 0.800
S 0- -0 I- i-I l---I- F
-I--- -- - I 1 - 2II 0 0
-InO .0- I -+ 4 { --1 - I - I- -I --- 00 00
:4 0 i t 2 I--I-I-I -Fl-i-- $ - -3 .n 3 0Sti
0 i0.0 -f--I--- - +i --I M --. { -i --- j If- -- -i-f H- i-I I ±og. 00
r+ N +f.
r ON. K vI - : i :- (Ii tF! 1 J 4-' 1"1 1- 1-1 1 1- 00-I CA --- I --. !-I I -:-I- I I I I I I I - IT 1
Design and data thermocouples circumferentialtemperature distributions.
I
L:'I L:' I'.T RUN 3. El UhL '1' ', III f1 1 11 U 11 11 ' 1IV N TIMIE l f':Y li: MiH SEC Hi1IF,01 it I-.' R 0:'? f. iI VS 111E i T;' 2' . .TI 1E 10 FST. P .U16 13 1 10 St,, Figure 10.1
i (Design) 2 (Data)
. 50. 0010 100. 00 150.00 200 0 2'..00 300.0 0 .350 00 400n0 4: 005C10.) 03 -II I I I I : I- I II I I I I I-HI--- : I t-Il- I I I-- -F - I: l - I1-E f F I- 1 I - I I --+ li -t-I- -- It - I - ,00 0
400.09 -- 1 -I- --I I I H I F-I --- - -- I 1-- -I I-f -I I-- - +4 -- -I-I - 1--I-I-I -+ - -I---II----+- I- I++- -- I- 1 I-F-+ - I- -- - F I -I - 400. 88
- .0.000 - I-I I 1- 1 1 1-I-I-I -I - t -I--- - I ------ 1---- I - F- 1II-I-- - -I - 1-- ---i - - +(- - --- IF-I- - - t -I-- F-t- I-+-- - -I- ,
I - 20000
1. 010.A0 1 -I- I : I 1 I1- + F -lA-I1,
I I -+-14--, - I I 1--H- f- --- -I - -I- I I----I--I- I I -- - 1- l-- l I---I--)-I-F --- -t I I-H -- -I- -- --- -- -I- +-t-I--,-- '- I--I .0+
oo 0u. ::'-O I- I I I -- I I 1 I----I-I-I -- I-t f-I I I-I '-I I I- 1 1 I-I----I- 1 -- I- - -I--I -- I -- II I I - I 0000
4: I t Ht hI fII II I-Ilf 2 I 1 +1
F I- I -I 1 - II1- I-F1 H IIA iI. II00Q J.50 rli 20l. I-- 300. C 4 0 t W0 i. t h
Azimuth
I- :.,;: T RUN <-S. D[-.G SKI l !HE L F- I .1 II 1- TIME 11 FP Y r 11 i S[:C M11.,.OT NI-_":ih R 82 All VS 1 l".' STIn 22F.1,TIME 151 FSI. P '.116 13 11 10 857 Figure 10.2
i (Design) 2 (Data)
. C.: :. ,0 00 100. 10o 1508. 2008.00 250. 00 300.80 30.08 40. 00 45.. 00-0. i-' I : I I I- FI - II --1 1 1 - 1 I I I 1- 1- 1 1 --11 1 -t III I - 50 0..0
420.00 "I-1-1-f I I I - I ---1---F I I1- -1-1 -1 - 1 1 FI f -I + I 4 -t- 1-1F-I 1-1 -H - 1 1 1- -i -I 1- 400.00
+ I2 -. 1 --I-1- 1 F I -F - I-I 1- - -I- I I -1-- 1 - 1F-II- I I -I--i- I -I---1 F---I---I-+ - 1- ----- --F--I-
- -- 1 - - I---- - I- -----I --- I - 00.0
1. 0, -II III I 1- I1 - I -I - 1 I - I ---- -- - I- -- + - + - -+---- - --- . -I - .00.-000'3 -- t F- II- I I -:F- FH-I- .- I -I-- -I- -I-F --- F-I I---F- F-I-F -I-f.-1- I -H I--I-I 1-- - - -f-I--I l-H -I-l-- l-t-I - t-- --- - -- -- +--F I--F- --I -lf- -I-I 1 - I I- --00.000
-1I -- ll I .1 - tI F - -I F I- I I -I-I- -I F I F- -F --I-F- I F F I- F I -- 1 -- l- I-- --tFl --I I I -- l I I -I -200.00
'tap (zS. .rT pLIM .!-. 1 DE G So. I HI t D A: 1 lbIll TIIil P Y ip HI l I .SFC 1111 IFfl HiM' R 02 WIl VS IL' S A 2- .J I.TIME 'I FST. fPI .16 13 10 10 8,s Figure 10.3
1 (Design) 2 (Data)
:!-I 000 1 n00 is i 2- ' 100 300. 00 3 h 'l, . 4 .. 0{i IJ {~- ! 1< I:- 1 my W20
4C0. :-1 P 1 F-1 H il 1 400 00
300. I I I I - I -I I I I I I I - 1 1 - 300.0_. I I I -1 H : I .- :- P t-+ --1 - -1- too. 00
2_2I2--
I't- I- i 1 1 I :-I - I ;- N-... I. t 0{ 1 i I t - -I I v- i I : I l-O- -I --I- { I-----I- I -1- 1000
-00.- -l- -l I I- 1 1 I I- I. I- 1- I I 1 1 -A I - 1 + 1 1- 1{ -1 I I 1 F- 08 00
.00.." t: - I I I-HI I I- I : I -I- -1- I-I I I I- -I -- I I I - i t t i - I --t- -I I i.- - - - H - I--I I - I- - t1- 1 :f-I. .I: 0o
l- ' N 1 I 'I I N I -I I-I -l- -- I "- --I -I I -I |- I -II'I -I -0 1 1- 1 0 1
..
. .- "- , -I J 1 1 1 1 I I 1 1 11 . I"I I - I I5;i t li. 00 150 t0 21- 51 2-". 00 300.00 3S 0 t '. 13 '1 .00
Azimr:uth
'bI C . I LT RLIH 18. 0 DLG 51 I. HEl- J .1 IIIS ON TIHE llY HiR 111 SFC 11111.
Pt IU i ;.: R 02 A. TH VS L t T;' . 2- . .TIME 241 FST. P .0 16 13 li 10 85e Figure 10.4
108.00 HI - --i " "- + -0 I-+ -1--4-- 11 F i --- - - i-+ - +H-- --I+ +-1- 4-+ -i- + + 1- 00.00
0000 I--- iI -I I I-I - HI- -- I - -I --- -1 -1 - -- I- - +- -- I--1- --- -I-H- I - i I- -I- ---- I-I I - .0000
-10 -1 -I - I- I- I - I-f +1+I 1-- I -1 II ---1 1--I---- 1 A I-H--I t-iI1- - 00.00
- I - I - *-: :- I| : 1 I20 I--.I-i I I I-I-I '1 1-10 1IH - -20005" 0'i) 10-. r0I 15 10 2 00 2". 00 3<00.00 350. -100. _-I 00
F L-, RUN IS. 0 DEI. 1.1 I R lAll D II ISUN TI 1 I 1, :YH' ' il lIN SEC 11II L1 ; .,: R 0 2 fIM VS I TP ' ... TIMV 2b F;1. F'PI.1 6 13 10 18 85i' Figure 10.
1 (Design) 2 (Data)
II L 3U U . O 0 I . 2 l !1 ,' 2 .2 0 0 3 .iu t :- ' " , 5 0 I, l t ( 4 . , 0 3
VI 0.-I I oI 0 1- i - I i1 : o . 1o f
300 C11. ..
- I I I: - I - ' I I- -I i -I I ISI i I i i- I i
1111 11 j Pi
S[.. .1', -t t +' - I -I I I 2 0 0 .0 0
2
2
. I 4 I- I I- I--I- I- --I I I -± .0000
80:0 -i I 1 :-l -(1 .1 I-n :- iI I-: ( I 1-- I1 noo.0
.s. . .I ' I n2 1 :7I l , 0, ,3 i 0 0 3,t, 0. . '1 . 110. . . . . . ... . . . . . . . . . . . . . . . . . . . . . . I- I I I I I I I - . . , I . . . - ,- b -:'
' C T RUN 48. 0 DEG SKI:I HERIED .IIISON TIE MY HR MIII SFC MII.L
HOrT ;;R 04 AIM VS TErP STA 2511I..TIME 100 FST. PT.016 13 10 18 857 Figure 10.6
' C'.-. :'T RUIN I., 0 DEG SK LhL IH It:l) JI. l ISON TIME DRY HR MIM SEC MIIL.KF IH -:.; R 04 nA. IN VS TEMI STA 22,l .n:TI1ME 250 FST. pfr. 116 13 10 10 857 Figure 10.9
3(Design) 4 (Data)
C.. 50.S 000 100.00 150 00 2.0 20. 0 300.00 3500 4A. t 40 ,0 005 L0. I I I: 1- I I -I I I I -- ,- - -I i l-II! 1-i -I- I.i F t II '-- I I - 5(0 00
4v. 0 3i: I I- 1) i- 1 ---1- -1 I - -- i I-I -- I -4 I -+- ----- H--- 40.0
z111. 3 - -F F--i--I- 1 1 ,-- 300
20 00 1-1-1 t- I I I I-- 1 I-H-- 1 F- --- I 1 -I -- - - )- - -- -- 20000
100 .3 I - I - I--I--I II I - -1-1 ---- I-I-I - 1 I-- -i -I- - -- F -f- I -- I- -- t--I-- -I - - 1I 100.00
S- -1 -1 1 1 000
-10 I I I- 1-I -1 1 1 1 I i4+1--1 4I-
A I I 1 1 -4-I- 4--I--- f 1 I -
I- I- - 1 I - - 0 21-0
Sf 00 300i 3 03
.I.'F R.;: ; 'T RLQII ':13. .l DEG SI HEA II i) If T-IS1ON T IIE L I)Y ItIR NIM SEC 1i II
OT .. R 4 . . II VS IEM STA ? . .TIME 2?i FT. PI.016 13 10 10 857 Figure 10.10
F , -:T RUff 41. 0 DUG II -iU H I IL0 I I IIISO.N TIME D:fY HR MIN SEC MILLI'l F 1 .:R 06 f;li VS t .10 A .-- .0.TI'E 11,,-i FST. PT.016 13 10 1 857 Figure 85CO.
TF CtS I.T RUN 4, DG S -6L HEllED JETI SOM TIME )fY I.IR MIH SEC tllI LFI.-T f:;:i.' R 06 lIl VS IErli' STA 23b5.0,1TIlE 150 FST. PI.016 13 1FI 10 5 Figure 1012
5 (Design) 6(Data)
'. .. I 5. 800 1 00 150. O 200. 10 250.00 300.00 350.00 400.00 458.00
5610 3 -+1 I - -I I-- - -I- - - l 1--I-I-I I - I --- tH I- - - - I - -I-I -I- I - 500. 00
200.00 - I- -- I A -I-I- ---I --- -- It-t- I----m- --t-I
- l-- ---- ---+-----+--i- -4--11 200.00
140.00 I1+ e- l I 4 -+ 1 - i t - -t-H -++--l+ I-I --- I---+A -I f -- 400.08
.-0'B -- FF I -I 1I--I .-- - I II--I---- I- - H---t-----t t -- 1-- I-- I- - -- I--I -I- I-- t--I- - t-- I+- --i - - I-- t I - 00
-A- - -HF I .80000
1 10000 -I- -- I- I-I I I--I -I--- -- I I- I-I1 -- I l--I-Il--I-- IA -I- --- - - . - --- -- --+-[ 1--+-I- - ----- -- I-H - I I .- 00.00
-1.0. ( I-I--I I I I I-I -4--I .I-I : I I--f- 1 I I-I--I-if t I - l--I - -I- --- I-I-I I I--I--I--I- I--H--I-- IF I- - -I .I I-I -100.00
--. -I I 1 I I I -I I II I I I I I l- : I I-I I I I I I-I I : : I I I-I- I-I I I I I I--I-I , I I I I-I-.-.--I 1 I I--II- I
I II I-TI I I I i i i 1--:M I 1 - I - 1.100. o" ' : . 10 r .. rV - o 201 *. 1 216. 00 300. 00 3: . 00 -IL). (1I -I .00
Azimuth
'Ff '. .T RiN 4 .. 0 D G S [GI H[ HIlD JIFl IlSUN TIME I;Y H-R illm c- MilPLOr il:, i R 6 IiN VS 1L0f' STA 2.Ab .[".TIM'IE 2'1I FSTr. P lt1 6 13 I1l 10 85' Figure 10o13
-. ',F CS, 1 ST RUN 48. O DEG Si I.I HEAirD l ILTT IISON TIME L~Y HR MIN SEC MILLFPLO.T U R 06 ARIM VS EMNI-STA 2. .3..TIIE 250' FST. PT.IG16 13 10 10 85 Figure 10.14
iB-- - 1-- --- --- I t- - - l -I -I--I--I- I -- --- I- --- l-- - l--l- I -l----H - -- --I--1--I- :- -4- -- -I-f- t - - ---- I- 10.09
2-00 00 ti- -I- I I I - -f I I I I --- -I I I -H- --I -- I I--II I - ----- l-+ - I -I-H- -+- I - H-I- I I I-I-- I ---I . ---I -I-- l -I-f-I-I - -- 100.00
.!'F S I ST RUN 43. 0 DEG hW t IEAlIFI)D .IETTISON TIIE DAY HIR 'II SEC MIII.PLOT Illl:11R 06 A.-ll VS TEII' STA 2S'35.0.TIME 2;'5 FST. PT.016 13 10 10 857 Figure 10.15
SlF S'. i ." RUN -18. 0 DEG SkJ.1 HEAID TIl ISON TIME D'Y HR MIIH SEC MI.L-FLUI HII.;.!; R 10 A-,'I[ VS TEMr' SIA 2b5i?...lIME 150 FST. PT.016 13 10 18 85? Figure 10.17
20 .0 CI -III-I- I I -1 I - -I-I --f - -- - -I i - I -I -- F -I "----I--I--I --I-- -I---I +I -14- -II- --- I- I-I- I -I- - i---- - --- - -I .
* 10.00r -I-I--II-I- - -I- - I I-I- l-I- -f--I --I - I-I-- I--------- -I-I-- I----I- -l f-- ---- I--I-- I I-- - I--I -I- I -I- -- I- - l-,--I-- f -f-I -I---f-I +--I---l-l--,I - 00.60
-100. 03 -i I I I I H I I I I I I I I I - -- I I I I - - I -- I i+ I- I --I I I-I I I I - -10 .--10.3 *:--, I I-- 1 - -I F 1
I t 2 $ 1i
003 100. no 150. 00 2n1. 3 2 1. 00 300. 1 i -i . o
Azimuth
F C. 1 ; RUN 13. 0 D[l; SK L .I HEO II L) ,.lTTISON TIlE DAY HR MINl SEC IL..IPLOT IH;:'t R 10 A ,,I VS IEP -STA 2!-b:. .TIME 200 FST. PT.i16 13 1A 10 857 Figure 10.18
.0800 --- - I--I--I t- I - -- I I I-- --I - I -t -- t-- I - I--+--- + I 4 - -I--f -t --- 1--I- -t-- 1--I--I----I-F - -I- 1--+ --- -1-1 -- - -t - -- + --- I -I -t
---H- . 00000
-00. 00 - I I : I -H I -I--I I I-I-I-I - I-Il I-I-I--I I I ------- l--- I 1---- -I-I- I-----I-i-- - - - l- - I I----I- I-l I-I--I -I I II 4-- - 1--F-- I 1-I--b -108. 8
-- z21:n : - 1 I I I I I -I I i I -l I I I 1 -1 -I II I -t -I I l 1 l -- I 1-I I -+ I---- I- I I -I--I -- I I I-Hi I-I I I Il I-I; -; I I I - -2 0. 00
"I'F CS IST RUM 48. 0 DEG SE-tl HEATED JETTISON TIME DAY HR -MI SEC MILLFLOT IlU:::R 12 ATIM VS EMl '-STA 262.-, TIME 1011 FST. PT.016 13 10 10 857 Figure 10.21
B (Design) c(Data)
0 .. 1 50 0 00 100.08 150.00 200. 00 250. 00 300. 00 350.*00 400.00 450. 00500.00 I-I--I : I I I --- I I i I -I-- I I I I I--I ---t- f- -- - 1- 1 I- -+-I- I I- I ---t 1-I I --- t- ---- I I- 500.00
40.0 -I---I-II i I- t-I 1 -l II +-+-I--f I - I----I + -I- -I-I - - I--I4 - ++ --- I -I --- - -I-I--I--I- --- I- -+-I --- 400.00
c to
±
2 .00 C-+f-41 -1 f1 F I J.+-+---- 14 1-+-I- ---+-I-+-- -- -- 41- 1- - -- H-+----------- - +-- 208.00
--- +-I--I--I I-4----I- -I -I-- --- I--I- - - --- - -f--[- - -- 0 - 4--I -I f-f 1 1 001000013 I--f- 1 I -i ij -4 : -l f F 1 -1 -1++ - 100.00
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100.00 1. C ?i30 300. 00 350. 00 0 '1. 00Azimuth
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F CSS [ST RUN 48. 0 DEG S.EI. HEWlED JI11TISON TIME DALY HR MI SEC MILL
PLOT HUVFiI-R 16 -1 1fl VS JTis' STA 2792.f.TIME 200f FST. PT.016 13 18D 16 85; Figure 10.33
r (Design) c (Data)
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Plir tI: R 16 ri: VS t-ll' STA 2?92.O,TIME 250 FST. PT.016 13 10 10 857 Figure 10.34F (Design) c (Data)
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Azimuth
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PLOT NIl::: :.R 18 071? VS IEMP STA 2R:2fl.-,TIME 100 FST. PT.016 13 10 10 857 Figure 10.36
H (Design) I (Data)C : 5. 000 100.00 15. 00 20088.00 250.00 300.00 3508.00 400.00 450.00
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N (Design) 1 (Data)
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SPF CSS-FST RUN 48, 8 DEG SKEW HJT, TIME 150 SEC TIME DAY HR MIN SEC MILLPLOT NUMBER 06 AZIM VS DEFLXIOB,D TEMP-STA 2459 FST. PT.016 13 18 18 857 Figure 11.7
s Design £ Deflectiontemp.
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s Design c Deflectiontemp.
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