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... Sample Assemblies for Compatibility Test Meltdown Assembly Simulating KIPS Heat Source 2.5.1.2-1... 2.5.1.2-2 2.5.1.2-3 2.5.1.2-4 2.5.1.3-1 2.5.1.3-2 2.5.1.3-3 2.5.1.3-4 2.5.1.3-5 2.5.1.3-6 2.5.1....3-7 2.5.1.3-8 2.5.1.3-9 2.5.1.3-10 2.5.1.3-11 2.5.1.3-12 2.5.1.3-13 2.5.1.3-14 2.5.1.3-15 2.5.1.3-16 2.5.1....3-17 2.5.1.3-18 2.5.1.4.1 2.5.1.4-2 2.5.1.4-3 2.5.1.4-4 2.5.1.4-5 iii TITLE
...) Radiator Weight Sensitivity of Header Weight to No-Puncture Probability FIGURE NO. 3.5.1.2-8 3.5.1....2-9 3.5.1.3-1 3.5.1.3-2 3.5.1.3-3 3.5.1.3-4 3.5.1.3-5 3.5.1.3-6 3.5.1.3-7 3.5.1.3-8 3.5.1.3-9 3.5.1....3-10 3.5.1.3-11 3.5.1.3-12 3.5.1.3-13 3.5.1.3-14 3.5.1.3-15 3.5.1.3-16 3.5.1.3-17 3.5.1.3-18 3.5.1.3-19 3.5.1....3-20 3.5.1.3-21 3.5.1.6-1 3.5.2.6-1 3.5.2.6-2 3.5.2.6-3 3.5.2.6-4 3.5.2.6-5 3.5.2.6-6 3.5.2.6-7 3.5.2.6-8 v
... Section Radiator Leak Single Point Failure Locations SECTION 3.0 FIGURE NO. 2.5.1.4-6 2.5.1.4-7 2.5.1....4-8 2.5.1.4-9 2.5.1.4-10 2.5.1.4-11 2.5.1.4-12 2.5.1.4-13 2.5.1.4-14 2.5.1.6-1 2.5.1.7-1 2.5.1.7-2 2.5.2.6-1... Instrumentation 3.5.1.2-lA 3.5.1.2-1B 3.5.1.2-2 3.5.1.2-3 3.5.1.2-4 3.5.1.2-5 3.5.1.2-6 3.5.1.2-7 iv
... C40 R 2 DO %2 C V 30 R 2 DO x 0 C30 VR _ 2 DO X0 C 1 40 V 2 D0 x 0 C 1 30 V 2D XO * 1 C10 V... 2D 0 C + C60 M 0 D0 + C50 m 2 DO X0 + C50 M 2 D0 x20 Where: 43 1 - v 2. R2 t2 D = Et3 12... (1 -v) Subscripts 0 and 1 refer to the thick wall and thin wall sections respectively M1, V1, VR, GA..., S 1, 1 , 61 and 6R are defined in Figure 2.5.1. 7-2. Ref. 12 S- .150 = 1.05 S.11 = 1.05 - .19 =... 1.02 S.10 74 1 90 S1 bo = 1. 03 C30 C30 C40 40 C50 C50 C60 C60
... 2 1.9 1.8 1.7 1.6 1.5 1.4 1.3 12 1.1 1 -1- ____________________ m e=, LI 1x W QI 2 100 106 112... 118 124 130 136 142 END COVER TEMPERATURE - DEG. F. 148 154 160 FIGURE 3.5.1.3-5 HEAT... '{ --I -1
... Failures Candidate Fibrous Insulation SECTION 2.5.1.2-I 2.5.1.3-I 2.5.1.3-II 2.5.1.3-III 2.5.1....4-I 2.5.1.4-II 2.5.1.6-I 2.5.1.6-II 2.5.1.6-III 2.5.2.6-I 2.5.2.6-II 2.5.2.6-III 2.5.2.6-IV 2.5.2.8-I 3.0 GROUND... 3.5.1.2-I 3.5.1.3-I 3.5.1.3-II 3.5.1.3-III 3.5.1.3-IV 3.5.1.3-V 3.5.1. 3-VI 3.5.1.3-VII 3.5.1....3-VIII 3.5.1.6-I 3.5.1.6-II 3.5.2.6-I 3.5.2.6-II 3.5.2.6-III vii TITLE
... TABLE 2.5.1.6-IV ISOTOPIC HEAT SOURCE ASSEMBLY ENCLOSURE SEAL LEAK SINGLE POINT FAILURES CM1... - Cover material - lower 1 BM1 - Bellows - Pressure... Release Device (PRD) 1 TM1 - Tube material - PRD... 1 SWS - Swageloc seal 1 OR - O-ring -... lower cover 1 HM - Housing material
... Alloy Diameter of Radiator (ft) 1 4.... 845 7. 525 8. 448 7.416 7. 168 6. 522 TR" n I1- 23.1... 39.5 46.4 59.0 29.3 44. 1 50. 7 64. 8 33. 1 48.3 53.9... 70. 8 \\e ght, Tube-Stringer (ib) 36.9 11.1 9.3 8.3 33.3 10.6... 10.2 9.7 35.4 7.17 7.5 7.1 Weight. Stringer Reinforcement (lb) 8.3
... 1HS - Transient A total of 89 rontry heating cases were evaluated. Results pertinent to KIPS arc... summarized in Table 2. 5. 1. 3-Ill. The parameters that were varied are: (1) initial path angle ( Y. = -8... during normal operation (helium and vacuum). Carpet plots are shown in Figures 2. 5. 1. 3-1 1 through 2.... 5. 1. 3-15 to graphically depict several IS temperatures and ablation as a function of Vi, Ti and hi.... Figures 2. 5. 1. 3-11 and 2. 5. 1. 3-12 are peak surface and PICS temperatures during reentry. Figure 2. 5
... Using equations 1, 5, 6, 7, 8, 9, 10, 11, 12 we arrive at four equations knowns; i. e. , in matrix... form: in four un- -. 21285 18. 46798 18.46798 196. 0034 128. 5947 1274. 812 705. 61"1 7210. 6447... for these equations is: A = 1. 757413 x 10-4p A2 = 9.32796 x 10-6 p0 A3 = 5.25776 x 10-6 p (13) A4 = 2. 023653 x 10...~ p0 5 = 1. 591633 x 10-8 p 0 Figure 2. 5. 1. 7-2 shows the breakdown of the cylindrical portion... the reaction VR the expressions for radial displacements and angular changes at points R and R1
... TABLE 3. 5. 1. 6-lI KIPS GDS IEAT SOURCE ENCLOSURE, GAS SEAL LEAK POINTS Code... 1 OR "O" Ring, Lower Cover 1 TW... Tube/Lower Cover Weld 1 TM Tube Material... 1 CM Cover Material, Lower 1 OR "O..." Ring, Upper Cover -Outer 1 OR "O" Ring, Upper Cover -Inner
... 120 TYP LEGEND - 1 SKIN 2 COOLN-r TL R- h \TR L',If\ 18 PI ( S 3 COOLA.\ V... \IH)l1 1) 2 P1 ( 4 \METEOROID S1{1E 11) 2 P1 CS 5 CIIA.\ I P Wf 9 PLCS 6 \IOU\TI\b 1I( 11 RE 3 11(S 7... ELECT CONTR I I SR 8 PARA'l !( 1 U\,i (I ',ISIOR c0 L- 487 SKIND0 D \ ~ 20 TPS... 5 2 2 3 5 253 088 DIA 2 - 130 1 035 TYP COOLANT TUBE 75R 2 DETAIL D SECTION A A 4 4I I ~... I SYSTEM MOUNT STRUCTURE 5 C -_ -C4 9600 ., 1 --I 6 7 4 SECTION B-B S 1 SECTION C
... A nalys is 2.5.2.6' 2.5.2.6.1 2. 5. 2. 6. 2 2. 5. 2. 6. 3 2. 5. 2. 6. 4 2. 5. 2. 6. 5 2.5.2.6.6 2. 5. 2. 6.... 7 2.5.2.8 2.5.2. 8.1 2. 5.2. 5. 2 FLIGHT SYSTEM RADIATOR Configuration Tradeoff Studies and Analyses... THERMAL INSULATION STABILITY Foil Insulation Fibrous Insulation i 2.5. 1 2. 5.1.1 2.5.1.2 2.5. 1.3 2.5.1....4 2.5.1.5 2.5.1.6 2.5.1.7
... TAIBLE 2. 5. 1.3-1! THEIPhiAL PROPERTIES OF HEAT SOURCE Material (Component) Helium (Gaps) Air... 0.0415 Btu/in3- sec Iridium (PICS) P = 0.8125 lb/in3 Tm = 44500F POCO AXF 5Q1 Graphite (Aero shell... 3000 4000 0 1000 2000 3000 4000 100 500 1000 1500 2000 2500 3000 1.924 x 10-6 4.108 x 10-6 5.209 x 10-t... 8.282 x 10-6 11.416 x 10-6 12.833 x 10-6 3.12 x 10-7 9.5 x 10-7 10.35 x 10-7 1.415 x 10-6 1.570 x 10-6... 2.222 x 10-5 1.968 x 10-5 1.829 x 10-5 1.771 x 10-5 1.51 > x 10-5 1.516 x 10-5 0.00134 0.00111 0.00088
... C31 C =1 C41 1 C51 C61 Equating slopes and deflections at point R1 allows us to solve... for M1 and V1 in terms of VR. The results are: M1 = 2., 15936 x 10-2 VR in. -lb Rin. V1 = -... where K =2. 02946 x 104 lb (14) in. Differentiating equation (1) and using... the results of (13) we have for the slope at r = L + b (dy ) = 1.7574x10 po r=L+b The radial... displacement of point R is then 6R =" L) r +b = 1.12859 x 10-4 p0 (15) where
... TABLE OF CONTENTS (CONTINUED) 3. 5. 1 3.5.1.2 3.5.1.3 3.5.1.4 3.5.1.5 3.5.1.6 3.5.2.6 3.5.2.6.1 3.... 5. 2. 6. 2 3.5.2.6.2.1 3. 5. 2. 6. 2. 2 3. 5. 2. 6. 2. 3 3.5.2. 6. 3 3.5.2.6.3.1 3.5.2.6. 3.2
... TABLE 3. 5.1.3-IV KIPS ELECTRItAL HEATER CARTRIDGE THERMAL TEST PROGRAM Electrical Heater... Burn-tn400*F/2000*F, Vacuum Setup & Checks Quantity (6) Test A1 Steady State - Argon - 1800*F - 1 Week (168 hrs) Test... A2 Thermal Cycle . Vacuum 1 - RT-1800*F - RT - Dwell 5 minutes - 30 Cycles Test A3 Life - Vacuum 1 h...) Test Bi Steady State - Argon - 1800 F - 1 Week Test B2 Steady State - Vacuum - 1800'F -1 Week Test... Fixture C Burn-in400*F/2000oF, Vacuum Setup & Checks Quantity (6) Test C1 Steady State - Vacuum - 1800*F -
... TABLE 2.5.2.6-r1n FAILURE MODE AND EFFECTS ANALYSIS CRITICALITY RANK C x ( = FE RANK 1) FM LIKE.... CO'.'PONENT & FUNCTION (FM) CAUSES FAILURE EFFECT (FE) CONSIDERATIONS 1.... Experience data and Q. C. controllable 5 1 1 1 100 { 500 1. 1 1.2 1.3 P ' ator Provides for waste heat... (high emissivity and low solar absorptivity Conlr 1 ies. Coolant 'lamfolds ani Conn ctimt' Iuhes 90... uclds - maximum length - approyimatcly 1.5" Appror -Latcly 150 ft of 0. O65 I. L tuwng Approcimately 25
... 2.5. 1. 7 Structural Analysis The analysis of the KIPS IISA housing subjected to an axial load... involves an integral structure composed of a cylinder and rib stiffened end cover (Figure 2.5. 1. 7-1... = 42 x 30 = 54.21 psi 0 1 x (2. 72)2 The methodology of the analysis assumes... (L + b - r)4 + A5 (L + b - r)5 (1) where: A1, A2, A3, A4 and A5... are constants to be determined. L, b and r are defined in Figure 2. 5. 1.7-1. Equation (1) satisfies
... 0 3. 5. 1.3 Thermal Environment of Heat Source 3. 5. 1.3. 1 Analyses Electrical Heat Source... 15.0 Instrumentation Cable 1.8 EHSA Internal Joule Heating 10.2 (excess... flow path characteristics assumed for the calculations are given in Table 3. 5. 1. 3-I. Actual.... 3. 1. 3-1 to 3. 5. 1. 3-5 as graphs of the parasitic heat loss vs significant component temperatures
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