Earth Observing System (EOS)/ Advanced Microwave ...

Report 10381Addendum 18 February 1996

Earth Observing System (EOS)/

Advanced Microwave Sounding Unit-A (AMSU-A)

Stress Analysis Report, A1 Module

Contract No: NAS5-32314

CDRL: 113-A1

Submitted to:

National Aeronautics and Space Administration

Goddard Space Flight Center

Greenbelt, Maryland 20771

Submitted by:

Aerojet

1100 West Hollyvale Street

Azusa, California 91702

TABLE OF CONTENTS

Report 10381Addendum 1

15 February 1996

Section

11.11.21.3

Page

INTRODUCTION ................................................................................................................... 1-1Identification ......................................................................................................................... 1-1

Purpose and Objectives .......................................................................................................... 1-1Document Status and Schedule ............................................................................................. 1-1

SUMMARY OF RESULTS AND CONCLUSIONS .............................................................. 2-2

44.14.24.3

55.15.25.35.45.4.1

5.4.25.4.35.4.45.4.5

REFERENCE DOCUMENTS ................................................................................................ 3-1

METHOD OF ANALYSIS ...................................................................................................... 4-1Finite Element Model ............................................................................................................ 4-1

Boundary Conditions ............................................................................................................. 4-1Load Application ..................................................................................................................... 4-1

RESULTS .............................................................................................................................. 5-1

Natural Frequencies .............................................................................................................. 5-1Random Vibration with Q = 7.1 ............................................................................................. 5-1

Panel Flange Beindign Stresses ............................................................................................ 5-2Summary Tables ..................................................................................................................... 5-2

Panel Flange Bending Stresses and Attachment Screw Stresses per RandomVibration Loads ................................................................................................................. 5-15

Lower Baseplate Mounting Bolts and Pins Stresses per 15 G Static Design Loads ............ 5-124Thread Shear Stresses in Attachment Hardware per Random Vibration Loads ................. 5-148

Large Masses Attachment Screw Stresses per Random Vibration Loads ........................... 5-192Lower Baseplate Stresses per Random Vibration Loads ....................................................... 5-254

Table

1234567834

545556565656565757

TABLES

Page

AMSU-A Margins of Safety, Summary of Static Minimum Margins .................................. 5-4AMSU-A Margins of Safety, 15 g's in X - Direction ............................................................. 5-5AMSU-A Margins of Safety, 15 g's in Y - Direction ............................................................. 5-6AMSU-A Margins of Safety, 15 g's in Z - Direction .............................................................. 5-7AMSU-A Margins of Safety, Summary of Random Vibration Minimum Margins ............. 5-8AMSU-A Margins of Safety, Random Vibration in X - Direction .......................................... 5-9AMSU-A Margins of Safety, Random Vibration in Y - Direction .......................................... 5-10

AMSU-A Margins of Safety, Random Vibration in Z - Direction ........................................... 5-11Fatigue Evaluation - Random VIB Stresses Q = 7.1

Qualification Level - 2MIN/AXIS ..................................................................................... 5-13A1-EOS Panel Flange Bending Stress Summary - Random Vibration Loads ...................... 5-16A1-EOS Panel Flange Attachment Screw Stress Summary - Random Vibration Loads .... 5-17A1-EOS Lower Baseplate Mounting Bolts Margins of Safety ............................................... 5-125A1-EOS Lower Baseplate Mounting Bolts Margins of Safety ............................................... 5-126A1-EOS Lower Baseplate Mounting Bolts Margins of Safety ............................................... 5-127A1-EOS Lower Baseplate Shear Pins Shear Tearout Margins of Safety .............................. 5-128A1-EOS Lower Baseplate Mounting Bolts Member Compression Margins of Safety .......... 5-129AMSU EOS-A1 Thread Shear Per Random Vibration Loads ................................................ 5-149AMSU EOS-A1 Thread Shear Per Random Vibration Loads ................................................ 5-150

ii

TABLE OF CONTENTS (Cont'd)


15 February 1996

Table

575757575757575758

59

TABLES (Cont'd)

Page

AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-151AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-152AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-153AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-154AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-155AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-156AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-157AMSU EOS-A1 Thread Shear Per Random Vibration Loards .............................................. 5-158

A1-EOS Large Mass Items Attachment Screw Stress Summary - RandomVibration Loads ................................................................................................................. 5-193

A1-EOS 1356405 Lower Baseplate Stresses - Random Vibration Loads .............................. 5-255

Figure

1234

4 (a)55 (a)66 (a)77 (a)891011

FIGURES

Page

AMSU-A1 Axes and Parts Identification ............................................................................. 5-287AMSU-A1 External Parts Identification ............................................................................... 5-288AMSU-A1 Finite Element Model .......................................................................................... 5-289

EOS AMSU-A1 1st Non-Rigid Body Modeshape at 109.0 Hz .............................................. 5-290EOS AMSU-A1 1st Non-Rigid Body Modeshape at 109.0 Hz Lower Cage Cards ............. 5-291EOS AMSU-A1 2nd Non-Rigid Body Modeshape at 109.0 Hz ............................................. 5-292EOS AMSU-A1 2nd Non-Rigid Body Modeshape at 109.0 Hz Lower Cage Cards ............. 5-293EOS AMSU-A1 3rd Non-Rigid Body Modeshape at 109.6 Hz ............................................. 5-294EOS AMSU-A1 3rd Non-Rigid Body Modeshape at 109.6 Hz Lower Cage Cards ............. 5-295

EOS AMSU-A1 4thEOS AMSU-A1 4thEOS AMSU-A1 5thEOS AMSU-A1 6thEOS AMSU-A1 7thEOS AMSU-A1 8th

Non-Rigid

Non-Rigid

Non-Rigid

Non-Rigid

Non-Rigid

Non-Rigid

Body Modeshape at 109.7 Hz ............................................. 5-296Body Modeshape at 109.7 Hz Lower Cage Cards ............. 5-297Body Modeshape at 116.3 Hz ............................................. 5-298Body Modeshape at 121.4 Hz ............................................. 5-299Body Modeshape at 122.2 H_. ............................................. 5-300Body Modeshape at 122.3 Hz ............................................. 5-301

Appendix

A

APPENDIX

Page

NASTRAN FINITE ELEMENT MODEL ............................................................................ A-1

,°°

111


Section 1

INTRODUCTION

This Addendum 1 to the Stress Analysis Report for the Earth Observing System (EOS)Advanced Microwave Sounding Unit-A (AMSU-A), A1 module, reports the structural margins of safety andnatural frequency predictions for the design following the EOS AMSU-A1 Mechanical/Structural SubsystemCritical Design Review (CDR). This report is an addendum to the June 1995 submittal of Aerojet Report10381. The report has been prepared in accordance with Section 3.4.3 of GSFC 420-05-01, PerformanceAssurance Requirements for EOS General Instruments.

1.1 Identification

This is Addendum 1 to the Stress Analysis Report for the Earth Observing System(EOS)/Advanced Microwave Sounding Unit -A (AMSU-A), module A1. This report is submitted to fulfill therequirements of Contract NAS 5-32314 CDRL 113, Stress Analysis Report, for the EOS AMSU-A1 module.The Stress Analysis Report for the A2 module has been submitted under separate cover.

1,2 Purpose and Objectives

The purpose of this analysis is to show that the AMSU-A1 module exhibits positivestructural margins of safety when subjected to the design loads given in GSFC 422-11-12-01, GeneralInterface Requirements Document (GIRD) for EOS Common Spacecraft]Instruments EOS PM Project.

In addition, the dynamic analysis results are used to show that the A1 module naturalfrequencies are above 100 Hz and that the simplified test and analytical model requirements of Section 3.4.3of GSFC 420-05-01, Performance Assurance Requirements for EOS General Instruments, can be applied tothe A1 module.

Document Status and Schedule

This is the submittal of Addendum 1 to the Stress Analysis Report for the A1 module

following the EOS AMSU-A1 Mechanical/Structural Subsystem CDR, held 7 December 1995. Addendum I ismeant to be used in conjunction with the June 1995 submittal of the Stress Analysis Report for the EarthObserving System (EOS) Advanced Microwave Sounding Unit-A (AMSU-A), A1 module, Report No. 10381.

1-1


Section 2

SUMMARY OF RESULTS AND CONCLUSIONS

The updated analysis of Addendum 1 shows all positive margins of safety for theEOS/AMSU-A1 Unit. Since publication of the June 1995 submittal of the Stress Analysis Report, variousmodifications have been made to the design and analysis. Addendum 1 analysis reflects these changes. A list

of the modifications and added analysis follows:

(1)

(2)

(3)

(4)

(5)

(6)

(7)

The 1356760 Power Control/Monitor Assy was redesigned (new weight 1.62 lb) andmodeled in the NASTRAN model, replacing CONM2 point masses (.37 lb).

The 1331642 Upper Aft Panel was modified to contain two .05 x .50 ribs to helpsupport the Power Control/Monitor Assy. The upper horizontal rib supporting theDC/DC Converter was also notched in three places for assembly purposes.

The 1356784 Transistor Assembly was added as CONM2 point masses (total weight

.50 lb) to the Upper Front Panel.

Natural frequencies were re-calculated per the above three changes, with theNASTRAN lumped mass option used in place of the coupled mass option. All modesremained above 100 Hz, with the 1st mode now at 109 Hz.

Mass properties of the EOS/AMSU-A1 Addendum 1 updated configuration show a

109 lb (49.4 kg) unit.

The random vibration analysis was re-done using a Q of 7.1 to match NOAA test data

of the A1 unit. Factors of safety of 1.25 (yield) and 1.4 (ultimate) were used on "3c"loads. Minimum margin of safety is now +.31 (was +.07 in Ref 1) at the Upper RightFront Support. In addition, a fatigue evaluation was performed at the June 1995report most severe location (cumulative usage factor .14 at Upper Right FrontSupport), with results now showing a cumulative usage factor of .003.

Analysis is included on panel flange bending stresses resulting from panel tensileloads and offset flange attachment screws. Random vibration loads are used. Stressresults required the following design changes:

(a) 1331652 Lower Ai_ Panel - Material change to 2024-T851 aluminum.

MS = +.07 Lower flange to t = .125 - .135 (was .050 - .060)MS = +.12 Upper flange to t = .070 - .080 (was .050 - .060)MS = +.16 Right flange to t = .070 - .080 (was .050 - .060)

(b) 1331650 Lower Right Panel -MS = +.06 Lower flange to t = .100 -.110 (was .040 - .060)

(c) 1331401 Lower Front Panel -

MS = +.13 Lower flange to t = .090 - .100 (was .040 - .060)MS = +.14 Upper flange to t = .060 - .070 (was .040 - .060)

(d)

(e)

1331642 Upper AR Panel - Material change to 2024-T851 aluminum.MS = +. 11 Lower flange to t = .095 - .105 (was .060 - .070)

1331651 Upper Right Panel - Material change to 6061-T6 aluminum.MS = +.08 Lower flange to t = .060 - .070 (was .040 - .060)

2-1

(8)

(9)

(10)

Report 10381Addendum I

(_ 1331447 Lower Right Front Support -MS = +. 18 Lower flange to t = .045 - .055 (was .040 - .060)

Analysis is included on lower baseplate beam cross-sections at panel attachments.Random vibration loads are used. Stress results required the following design

change:

(a) 1356405 Lower Baseplate - Membrane under lower aft panel attachmentthickened from .075 +/- .010 to .200 +/- .010 MS = +.09.

To demonstrate the mathematical soundness of the NASTRAN model, the model is

subjected to the GSFC 422-11-12-01 Paragraph 11.1.4.i Deliverable Model ValidityCheck, where a rigid-body or stiffness-equilibrium check is performed. The model isshown to satisfy this check (see Appendix A).

Analysis added pertaining to the fasteners is as follows:

(a) The mounting screws and shear pins of the EOS/AMSU-A1 unit to thespacecraft mounting surface are evaluated for tensile and shear loadingsalong with thread shear. Loading conditions are the three static design loads,15g_s, independently in the global X, Y, and Z directions. In addition, bearingand shear tearout of the shear pins onto the baseplate are evaluated for the

loading assumption of all shear reacted at the shear pins (no shear atmounting bolts). At the mounting bolts, member compression under preloadand bearing and shear tearout in the baseplate are also calculated. Minimumoverall MS in the mounting fasteners is a +.52 margin in the highest loadedscrew under combined tensile and shear load.

(b) The fasteners mounting the panels to the baseplates and other panels areanalyzed for tensile and shear loading and for thread shear. Thread shearstress calculations also consider the inserts and/or nutplates. Loadingconditions are the three random vibration load cases. In addition, the panels'

offset flange bending stresses are evaluated per the same random vibrationloadings. Minimum MS's are +.06's in the Lower Right Panel lower flangeand the Upper Aft Panel side flange, with a MS of +.10 in the screwsattaching the Lower AR Panel to the Lower Baseplate. The followinglocations are considered:

(1) 1331390(2) 1331652(3) 1331650(4) 1331352(5) 1331414(6) 1331389(7) 1331401(8) 1331642(9) 1331651(10) 1331447

Upper Right Front SupportLower AR Panel

Lower Right PanelUpper Front PanelLower Motor Mount Panel

Upper Motor Mount PanelLower Front Panel

Upper Air PanelUpper Right PanelLower Right Front Support

(c) The attachment hardware mounting the significant mass items to the A1

assembly are analyzed for tensile loads per the loading conditions of randomvibration. Superpositioning of finite element model loads, derived fromrandom vibration analysis, with preload effects, and over-turning momenteffects is performed on the mounted hardware listed below. Minimum MS is+.68 in the screws attaching the 1331165 Bracket to the 1356409 A1-2Receiver Assembly.

2-2

(11)


(1)(2)(3)

(4)

1356010 DC/DC Converter1331610 Detector Preamp1356429 Receiver Assembly AI-1 Components(a) 1348360 PLO Assemblies(b) 1336610 Oscillators(c) 1331592 Bracket and Components(d) 1331582 Bracket and Components(e) 1331595 Bracket and Components1356409 Receiver Assembly A1-2 Components(a) 1331165 Bracket and Components(b) 1331482 Bracket and Components(c) 1331481 Bracket and Components(d) 1336610 Oscillators

Fastener length changes, required because of panel and baseplate modifications, arereflected on the 1356404 Antenna Subassembly Machined - A1 drawing.Modifications are to (1) the 1331652 Lower Aft Panel attachment to the 1356405Lower Baseplate, where -9 (if available) or -10 NAS1352N06 fasteners replace the -6screws, and (2) the 1331642 Upper Aft Panel attachment to the 1331356 UpperBaseplate, where -10 NAS1352N06 fasteners replace -8 screws. All other fastenerlengths remain unchanged.

(12) The following describes added analysis pertaining to the 1336405 Lower Baseplate.

Baseplateadded analysisconsistsof:

(1)

(2)

(3)

(4)

determining the magnitude of the stresses in the thin shell elements underthe lower card cage,hand-calculating the localized stresses in the U-beam cap under the lowerfront panel, the lower aft panel, and the lower right panel,checking the shear stresses in the grooved section at the base of the integralrib,andcalculatingshear stressesinthethreadsforthe insertsand nutplates.

All baseplate analysis is performed using the loadings attributed to randomvibration. Minimum margins of safety are (1) +4.2 under the lower card cage, (2) +.09at the lower aft panel, (3) +17 at the grooved section, and (4) +.33 at the internalthreads of a baseplate penetration containing an MS51830-103 insert for attachmentof the lower right panel to the lower baseplate.

2-3


Section 3

REFERENCE DOCUMENTS

The following documents were used in the preparation of this Report:

422-11-12-01Rev. A

January 1994

420-05-01Rev. A

2 Aug. 1991

422-12-12-04March 1993

Report 935021 Dec 1988

Report10381PreliminarySept 1994

Report10381• June 1995

SPECIFICATIONS

General Interface RequirementsDocument (GIRD) for EOS Common

SpacecrafffInstruments EOS PM Project

Earth Observing System (EOS)Performance Assurance Requirementsfor EOS General Instruments

Contract Documentation RequirementsList for the Advanced Microwave

Sounding Unit-A (AMSU-A) EOS PM Project

Aerojet ReportsStructural Analysis of the AMSU A1Instrument Final Report

Earth Observing System (EOS)/Advanced Microwave Sounding Unit-A (AMSU-A)Stress Analysis Report, A1 Module

Earth Observing System (EOS)/Advanced Microwave Sounding Unit-A (AMSU-A)Stress Analysis Report, A1 Module

3-1

Report10381Addendum 1

Section 4

METHOD OF ANALYSIS

4.1 Finite Element Model

The NASTRAN finite element model prepared for EOS AMSU-A1 in the June 1995 report

(Report 10381) is modified to a new and more refined model. With the primary changes the modeling of there-designed Power Control/Monitor and the inclusion of the Transistor Assy mass, the Addendum 1 modelmore accurately represents the EOS design (see Figure 3). The Addendum 1 model statistics are:

6146i Grids .............................................d

...................... ........................... it

........................==============================================================================

..................523"..: ........_a_.::_ar" Plate Elements H

........................7"_........M_'_:_'_'_'_ ....................................................................................il

The total mass of the model is now 49.4 Kg (109.0 pounds). Appendix A presents a detailed

description of the NASTRAN finite element model, including the rigid-body validity check.

4_2 Boundary Conditions

The model was constrained along the three orthogonal axes at each of the 20 mounting bolt

locations and along the two transverse axes (X and Y in Figure 1) at the 2 dowel pin locations. Theconstraints were imposed using NASTRAN single point constraint cards.

4_ Load Application

For the static loads evaluations, the 15g load was uniformly applied over the entire model.Three load cases were run. Each load case represented the 15g load being applied in one of the axes shown

in Figure 1.

Similarly for the random vibration loadings, the qualification level 9.97 Grins spectrum was

applied along the three orthogonal axes. Three load cases were run. Each load case represented the randomspectrum being applied in one of the axes shown in Figure 1. The Addendum 1 analysis is run with anamplification, Q, of 7.1, corresponding to the highest Q found in NOAA random vibration test results.

4-1


Section 5

RESULTS

The previous submittal of the AMSU-A1 EOS Stress Analysis Report (Report 10381) was

presented in June 1995, prior to the July 26, 1995 initial Critical Design Review (CDR) on the EOS/AMSU-A1 Mechanical/Structural/Thermal Subsystem. With subsequent comments to the July 1995 presentation

addressed, the EOS/AMSU-A1 Mechanical/Structural/Thermal Subsystem final CDR was presented on 7December 1995. Addendum 1 is written to house the additional analysis performed due to the added scope to

the analysis resulting from the action items of the July 1995 and December 1995 CDR's.

5.1 Natural Frequencies

The June 1995 submittal concluded that the minimum natural frequency of the EOS AMSU-

A1 unit was 117.6 Hz, with the mode shape involving the flexing of the lower card cage circuit cards. Modes1 through 4, with mode 4 at 118.6 Hz, all involved lower card cage circuit card and/or cage wall distortion.Mode 5, at 120.6 Hz identified the deformation of the upper aft and top panels.

Pursuant to the June 1995 report release additional information on the 1356760 Power Control/Monitor(PC/M) Assembly, which mounts on the upper aft panel, became available. This data, a weight increase plusa new detailed design layout, allowed the modeling of the PC/M Assembly into the NASTRAN model (inplace of CONM2 point masses). With this addition]modification, along with the addition of the 1356784Transistor Assy via CONM2 point masses on the Upper Front Panel, the natural frequencies were re-evaluated, with results listed below. In addition, the NASTRAN analysis method option was changed from acoupled mass solution to a more conservative lumped mass solution. The new natural frequencies, per theNASTRAN model post rigid-body equilibrium check, are still above 100 Hz (eliminating the requirement of adetailed deliverable model), with the 1st mode at 108.9 Hz, mode shape lower card cage circuit cards flexing.The 1st mode involving the Upper Aft Panel/Power Control/Monitor is mode 5 at 116.3 Hz.

ModeNo.

Natural FrequencyOld PC/M (CONM2)

No Trans Assy

Natural FrequencyNew PC/M Modeled

Wfrrans Assy

1 117.7 Hz i 109.0 Hz............................... p.• ............................ °. ................ . .......... ._ .................. ..• ........... °° ........................ • .....

2 117.7 -" 109.0............................... c ................ °'• .......... °•'° ......... °°°•" ............... '•• ............ ••° ........... °°'° ................. °'"°•°"•°'

3 _ 118 4 109.6..................... •.._•_•_._.••_.•_•_._._••_•_•_.•_•_._._._._•_._._•_._.•._._•M_ ........ . .° ....... o.•...

4 _ 118.7 109.7........•......"_"............i.................""..............................................................................120.6 116.3"......................."............."8"............}........................i26:'§ ........................................................................................121.4

...........""i"............i'"'"..........."'""'""'"''"'"•'"'127.1........""........."".........."'"•'"'"""'122-2..................."" ............................. , ........ _,............................ * .......... °,,•°.• ............. _..•° ................................................. • ..........

: 127.2 122.3• ......... °°°°°°°.°°°•.•° ....... ° .......... • ............ , ......... ° ......

...............'_"............i................................................148.5 146.6

........................................................................................................................................147.2

Figures 4 through 11 depict the new natural frequencies and modeshapes for the 1st 8modes.

5.2 Random Vibration with Q = 7.1

Subsequent to the July 1995 presentation, the need was identified to re-evaluate randomvibration analysis. The random vibration analysis of the June 1995 report was performed using theNASTRAN code with a type "G" structural damping value of 0.04. The critical damping percentage is 1/2 ofthis value, or 2%. For large Q, (Q>10), the amplification or quality factor, Q, is approximated by:

5-1


Q = 1/[2(c/cc)] c/c¢ = fraction of critical damping

With c/co equal to 0.02, an amplification, Q, of 25 was used in the NASTRAN model. A Q of 25was felt to be a conservative value and precluded the use of additional factors of safety in the randomvibration analysis. Stresses derived from the NASTRAN solution were multiplied by an additional 3.0 factorto produce "3c" values.

The random vibration analysis of Addendum 1 is re-done using a Q = 7.14 (NASTRAN type"G" structural damping value of 0.14), corresponding to the largest Q found in test data of the NOAA A1unit. To the stresses derived from the NASTRAN random vibration stress output, a 3.0 factor is applied toproduce "3c_"values, plus an additional factor of safety (FS) of 1.25 on yield or 1.4 on ultimate is alsoemployed.

Random vibration analysis in Addendum 1 is presented similarly to the June 1995submittal. Per structural component, margins of safety (MS) summary tables are given for each direction ofvibration, along with the overall minimum MS table. A fatigue evaluation is performed again at the June1995 report critical location.

Minimum MS attributed to random vibration "3_" loads, per the methods outlined above, is a+.31 at the 1331390 Upper Right Front Support. The fatigue evaluation at the Reference 1 critical location,the Upper Right Front Support, now identifies a cumulative usage factor of only .003, or <1% of the allowedcycles are utilized.

Addendum 1 Tables 6 through 8 list the NASTRAN model random vibration results.

5_ Panel Flange Bending Stresses

Addendum 1 analysis is concerned with panel flange bending stresses resulting from paneltensile loads and offset flange attachment screws. Random vibration loads, multiplied by an additional 3.0factor to produce "3c_" values, and then used with FS's of 1.25 yield and 1.4 ultimate, are more severe thanthe static 15g static design loads with FS's, and are thus used in the analysis.

The method employed for evaluation of a flange is to first determine the highest loaded platefinite element adjacent to the flange of interest. The (tensile) force in the panel perpendicular to the flangeis the primary load reacted at the bolt in the form of a reacted force and a bending moment. This force isreacted in the flange attachment bolt and the bending moment produces bending in the flange. Both flangeattachment bolts and the flanges themselves are evaluated per hand calculation methods. This data issummarized by itself in Addendum 1, Table 54, and is utilized in the overall random vibration minimum MSsummary (Table 5). Note that no static design load flange bending stress calculations are performed, thusthe overall static design load minimum MS summary (Table 1) contains no flange bending hand calculationresults. Minimum margin of safety is at the 1331650 Lower Right Panel with MS = +.06.

5.4 Summary Tables

Margins of safety results, presented in Addendum 1, are the following tables. Tables 1through 8 and 34 are modified June 1995 report Tables. Table 1 is the overall static loading (15g_s in eitherY_ Y, or Z directions) summary table. Tables 2, 3, and 4 present NASTRAN shell and beam results for staticloads in the X, Y, and Z directions, respectively.

Table 5 is the overall random vibration (Q = 7.1) summary table. Tables 6, 7, and 8 presentNASTRAN shell and beam results for random vibration loads in the X, Y, and Z directions, respectively.

Table 34 is a fatigue summary for the June 1995 report critical location at the Upper Right

Front Support at element 2633.

5-2


Tables 54 through 59 are new Tables of Addendum 1. Panel flange bending stresses perrandom vibration loads are summarized in Table 54, with the results of the attachment screws of the panel

flanges in Table 55.

Lower baseplate mounting bolts and associated fastener hardware stresses per static design

loads (15g_s in either X, Y, or Z directions) are summarized In Table 56.

Thread shear results in the attachment hardware connecting the panels to baseplates and

other panels per random vibration loads are found in Table 57.

Large mass item attachment screw stresses per random vibration loads are found in Table58.

Lower baseplate stresses per random vibration loads are shown in Table 59.

The Earth Observing System (EOS)/Advanced Microwave Sounding Unit-A (AMSU-A), A1unit is shown in Addendum I to exhibit all positive margins of safety and is therefore suitable for flight.

Hand written analyses on the above subjects follow the summary tables.

5-3


ITEMNO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

23

24

25

26

TABLE 1

AMSU-A1 MARGINS OF SAFETY

SUMMARY OF STATIC MINIMUM MARGINS

DESCRIPTION

BASEPLATE ASSEMBLY, LOWER

PARTNUMBER

1356405-1

SHELF, RF, UPPER

SUPPORT PANEL, LOWERRIGHT FRONT

PANEL, SIDEWALL, RIGHTLOWER

PANEL, SUPPORT, RIGHTFRONT UPPER

PANEL, MOTOR MOUNT LOWER 1331414-1

PANEL, MOTOR MOUNT UPPER 1331389-1 ALUM/7075-T651

PANEL, FRONT, LOWER 1331401-1 ALUM/6061-T651

PANEL, AFT, LOWER 1331652-1 ALUM/2024-T851

BASEPLATE, UPPER 1331356-1 ALUM/6061-T651

PANEL, FRONT UPPER 1331352-1 ALUlVVT075-T651

PANEL, AFT WALL, UPPER 1331642-3 ALUM/2024-T851

SHELF, RF, LOWER 1331556-1 BE/SR-200E

1331491-1 BE/SR-200E

1331447-1

133 1650-4

1331390-1

1331651-1JPANEL, SIDEWALL, RIGHT-UPPER

_PANEL, TOP 1356866-1 ALUM/6061-T6

PANEL, SIDEWALL, LEFT 1356626-1 ALUM/6061-T6

MOTOR ROTOR SHAFT 1333645-1 303 CRES ACOND

SHIELD, WARMLOAD, LOWER 1331445-1 ALUM/6061-T6LEFT

SHIELD, WARMLOAD, LOWER 1331405-1 ALUM/6061-T6RIGHT

SHIELD, WARMLOAD, UPPER 1331647-1 ALUM/6061-T6LEFT

SHIELD, WARMLOAD, UPPER 1331646-1 ALUM/6061-T6RIGHT

CARD CAGE ASSY (LOWER) 1331600-1 ALUM/6061-'1"6

CARD CAGE ASSY, UPPER 1331162-8 ALUM/6061-T6


CALIBRATION SOURCE ASSY,WL ILOW)CALIBRATION SOURCE ASSY,WL (UP)

,BEAM SUPPORT

1331380-1

133138_2

1331_6-1

MATERIAL/ YIELD ULTIMATEALLOY (PSI) (PSI)

ALUM/6061-T651 35000

ALUM/7075-T651 66000

66000

35000

58000

35000

66000

58000

50000

50000

ALUM/6061-T651 35000

ALUM/6061-T6 35000

ALUM/6061-T651 35000

ALUM/6061-T6 35000

35000

35000

26000

35000

35000

35000

35000

35000

35000

16000

ALUM/6061-T6 35000

ALUM/7075-T6 66000

ALUM/7075-T6 66000

MAXIMUM' STRESS (PSI)

42000 4925

75000 3055

75000 1944

42000 4198

66000 5346

42000 5136

75000 4706

66000 3104

70000 3018

70000 2182

42000 3451

42000 10092

42000 6313

42000 830

42000 627

42000 1383

73000 600

42000 3085

42000 2633

42000 2735

42000 2832

42000 1896

42000 3665

30000 2057

42000 896

75000 942

75000 4606

MARGINS OF SAFETYYIELD ULTIMATE

4.69 5.09

16.28 16.54

26.16 26.56

5.67 6.15

7.68 7.82

4.45 4.84

10.22 10.38

13.95 14.19

12.2.5 15.57

17.33 21.91

7.11 7.69

1.77 1.97

3.44 3.75

32.73 35.14

43.66 46.85

19.54 21.01

33.67 85.90

8.08 8.72

9.63 10.39

9.24 9.97

8.89 9.59

13.77 14.82

6.64 7.19

5.22 9.42

30.25 32.48

55.05 55.87

10.46 10.63

"SEE FIGURES 1 & 2

5-4

Report 10381

Addendum 1

ITEMNO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

23

24

TABLE 2


15 g's IN X - DIRECTION

DESCRIPTION

3ASEPLATE ASSEMBLY, LOWER

PANEL, MOTOR MOUNT LOWER

PANEL, MOTOR MOUNT UPPER

PANEL, FRONT, LOWER

PANEL, AFT, LOWER

BASEPLATE, UPPER

PANEL, FRONT UPPER

PANEL, AFT WALL,UPPER

SHELF, RF, LOWER

SHELF, RF, UPPER

SUPPORT PANEL, LOWER,RIGHT FRONT

PARTNUMBER

1358405-1

1331414-1'

MATERIAL/ALLOY

ALUM/6061 -T651

ALUM/7075-T651

1331389-1 ALUM/7075-T651

1331401-1 ALUM/6061-T651

1331652-1 ALUM/2024-T851

1331356-1 ALUM/6061-T651

1331352-1 ALUM/7075-T651

1331642-3

1331556-1

1331491-1

1331447-1

PANEL, SIDEWALL, RIGHT 1331650-4LOWER

PANEL, SUPPORT, RIGHT 1331390-1FRONT UPPER

PANEL, SIDEWALL, RIGHT- 1331651-1UPPER

PANI=I TOP 1356866-1

PANEL, SIDEWALL, LEFT 1358626-1

MOTOR ROTOR SHAFT 1333645-1

SHIELD, WARMLOAD, LOWER 1331445-1LEFT

SHIELD, WARMLOAD, LOWER 1331405ol:tIGHT

1331647-1SHIELD, WARMLOAD, UPPERLEFT

SHIELD, WARMLOAD, UPPERRIGHT

CARD CAGE ASSY (LOWER)

CARD CAGE ASSY, UPPER


1331646-1

1331600-1

1331162-8

1331162-8

1331380-1

1331 350-2

1331406-1

CALIBRATION SOURCE ASSY,iWL (LOW_

25 CALIBRATION SOURCE ASSY,WL IUP)

26 BEAM SUPPORT

ALUM/2024-T851

BE/SR-2OOE

BE/SR-200E

ALU M/6061 -T651

ALUM/6061 -T6

_.LUM/6061 -T651

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061 -T6

303 CRES ACOND

ALUM/6061-T6

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061-T4

ALU M/6061 -T6

ALU M/7075-T6

ALUM/7075-T6

YIELD(psi)

35000

660O0

660OO

35O00

580O0

350O0

66OO0

58OOO

500OO

5O0O0

35OOO

35OOO

35OO0

35OO0

350O0

35OOO

26OO0

35OOO

35OO0

35OOO

35OO0

3500O

35OOO

16000

35000

66O00

66OO0

ULTIMATE MAXIMUM(psi) STRESS (psi)

42000 1728

75000 3055

75000 1944

42000 2OO4

66000 3284

42000 3019

75000 4072

66000 3104

70000 3018

70000 372

42000 1436

42000 2526

42000 3805

42000 830

42000 434

42000 1363

73000 82

420O0 3085

42000 2633

42000 2735

42000 2832

42000 456

42000 769

30000 370

42000 322

75000 _4

75000 4006

MARGINS OF SAPP"I _'

YIELD ULTIMATE

15.20 16.36

16.28 16.54

26.16 26.56

12.97 13.97

13.13 13.36

8.27 8.94

11.97 12.16

13.95 14.19

12.25 15.57

106.53 133.41

18.50 19.89

10.08 10.88

6.36 6.88

32.73 35.14

63.52 68.12

19.54 21.01

252.66 634.89

8.08 8.72

9.63 10.39

9.24 9.97

8.89 9.59

60.40 64.79

35.41 38.01

33.59 56.92

85.96 92.17

133.01 134.97

10.46 10.63

*SEE FIGURES 1 & 2

5-5


ITEMNO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

26

TABLE 3


15 g's IN Y - DIRECTION

DESCRIPTION




PANEL, FRONT, LOWER

PANEL, AFT, LOWER

BASEPLATE, UPPER

PANEL FRONT UPPER

PANEL, AFT WALL, UPPER

SHELF, RF, LOWER

PARTNUMBER

1356405-1

1331414-1

1331389-1

11331401-1

1331652-1

1331356-1

1331352-1

1331642-3

1331556-1

MATERIAL/ALLOY

ALU M/6061-T651

ALUM/7075-T651

ALUIVl/7075-T651

ALUM/6061 -T651

ALUM/2024-T851

ALUM/6061 -T651

_,LUM/7075-T651

ALUIVl/2024-T851

BE/SR-200E

SHELF, RF, UPPER 1331491-1 BE/SR-200E

SUPPORT PANEL, LOWER 1331447-1 ALUM/6061-T651RIGHT FRONT

PANEL, SIDEWALL, RIGHT 1331650-4 ALUM/6061-T6LOWER

PANEL, SUPPORT, RIGHT 1331390-1 ALUM/6061-T651FRONT UPPER

PANEL, SIDEWALL, RIGHT- 1331651-1 ALUM/6061-T6UPPER

PANEL,TOP 1356866-1 ALUIW6061 -T6

PANEL, SIDEWALL, LEFT 1356626-1 ALUM/6061-T6

MOTOR ROTOR SHAFT 1333645-1 303 CRES ACOND

SHIELD, WARMLOAD, LOWERLEFTSHIELD, WARMLOAD, LOWER

!RIGHT

SHIELD, WARMLOAD, UPPERLEFT


1331445-1 ALUM/6061-T6

1331405-1 ALUM/6061 -T6

1331647-1 ALUM/6061-T6

1331646-1 ALUM/6061-T6

CARD CAGE ASSY (LOWER) 1331600-1

CARD CAGE ASSY, UPPER 1331162-8

1331380-1CALIBRATION SOURCE ASSY,WL (LOW)CALIBRATION SOURCE ASSY,WL (UP)BEAM SUPPORT

1331380-2

1331406-1

ALUM/6061 -T6

ALUM/6061 oT6

ALUM/6061 -T6

ALUM[7075-T6

ALUM[7075-T6

YIELD(psi)

35OO0

660OO

660OO

35000

58OO0

350O0

660O0

580O0

50000

5OO00

35OO0

350O0

35OOO

35OO0

350O0

35OO0

26OOO

35OO0

35OOO

35OO0

350O0

35OOO

35OO0

35OO0

560O0

66OO0

ULTIMATE MAXIMUM MARGINS OF SAI-I= I Y

(psi) STRESS (psi) YIELD ULTIMATE

42000 4925 4.69 5.09

75000 1066 48.53 49.25

75000 1017 50.92 51.68

42000 4198 5.67 6.15

66000 5346 7.68 7.82

42000 5136 4.45 4.84

75000 4706 10.22 10.38

66000 1171 38.62 39.26

70000 1612 23.81 30.02

70000 623 63.21 79.26

42000 3451 7.11 7.69

42000 10092 1.77 1.97

42000 6313 3.44 3.75

42000 703 38.83 41.67

42O0O 278 99.72 106.91

810 33.57 36.04

600 33.67 85.90

42O0O

73000

42000

42000

2377 10.78 11.62

847 32.06 34.42

365 75.71 81.1942000

42000 601 45.59 48.92

42000 1896 13.77 14.82

42000 1179 22.75 24.45

42000 746 36.53 39.21

75000 501 104.39 105.93

75000 1044 49.57 50.31

*SEE FIGURES 1 & 2

5-6


ITEMNO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

23

24

25

26

TABLE 4


15 g's IN Z - DIRECTION

PARTDESCRIPTION NUMBER

BASEPLATE ASSEMBLY, LOWER 1356405-1


PANEL, MOTOR MOUNT UPPER 1331389-1

PANEL, FRONT, LOWER 1331401-1

PAN E L, AFT, LOWE R 1331652-1

BASEPLATE, UPPER 1331356-1

PANEL, FRONT UPPER 1331352-1

PANEL, AFT WALL,UPPER 1331642-3

MATERIAL/ALLOY

ALUM/6061-T651

ALUM/7075-T651

ALUIVVT075-T651

ALUM/6061-T651

ALUM/2024-T651

ALUM/6051-T651

ALUM/7075-T651

ALU M/2024-T65 1

SHELF, RF, LOWER 1331556-1 BE/SR-200E




PANEL, SUPPORT, RIGHT 1331390-1 ALUM/6061-T651FRONT UPPER

PANEL, SIDEWALL, RIGHT- 1331651-1 ALUM/6061-T6UPPER

PANEL,TOP ALUM/6061 -T6

: PANEL, SIDEWALL, LEFT

MOTOR ROTOR SHAFT

SHIELD, WARMLOAD, LOWERLEFT

SHIELD, WARMLOAD, LOWERRIGHT


1356866-1

1356626-1


1333645-1

1331445-1

1331405-1

1331647-1

1331646-1

ALUM/6061 -T6

303 CRES ACOND

CALIBRATION SOURCE ASSY,WL {LOW)CALIBRATION SOURCE ASSY,WE (UP)BEAM SUPPORT

ALUM/6061 -T6

ALUM/6061-T6

ALUM/6061 -T6

ALUM/6061-T6

CARD CAGE ASSY (LOWER) 1331600-1 ALUM/6061-T6



1331380-1 ALUM/6061-T6

1331380-2

1331406-1

ALUMf7075-T6

ALUM/7075-T6

YIELD(psi)

35OOO

66OOO

66000

350OO

58OOO

35OO0

65OO0

580O0

5O00O

500OO

35OOO

35OOO

35OOO

35O0O

35000

35OOO

26OOO

35OO0

35OOO

35OO0

35OO0

35OOO

350OO

16000

35OO0

66OOO

66OOO

ULTIMATE MAXIMUM(psi) STRESS (psi)

42000 4310

75000 548

75000 942

42000 2434

66000 3650

42000 3940

73000 2_0

60000 1406

70000 2843

70000 2182

42000 1258

42000 5422

42000 5075

42000 445

42000 627

42000 816

73000 600

42000 1939

42000 744

42000 2093

42000 602

42000 1588

42000 3665

30000 2057

42000 896

75000 942

75000 2671

MARGINS OF SAM= I Y

YIELD ULTIMATE

5.50 5.96

95.35 96.76

55.05 55.87

10.50 11.33

11.71 11.92

6.11 6.61

22.57 22.92

32.00 32.53

13.07 16.59

17.33 21.91

21.26 22.85

4.16 4.53

4.52 4.91

61.92 66.42

43.66 46.85

33.31 35.76

33.67 85.90

13.44 14.47

35.63 39.32

12.38 13.33

45.51 48.83

16.63 17.89

6.64 7.19

5.22 9.42

30.25 32.43

55.05 55.87

18.77 19.06

*SEE FIGURE 1

5-7

Report 10381

Addendum 1

ITEM

i NO/

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

18

19

2O

21

22

23

23

24

25

26

27

28

TABLE 5


SUMMARY OF RANDOM VIBRATION MINIMUM MARGINS

PART

DESCRIPTION NUMBER


PANEL MOTOR MOUNT LOWER 1331414-1


PANEL, FRONT, LOWER 1331401-1

PANEL AFT, LOWER 1331652-1

BASEPLATE, UPPER 1331386-1

PANEL, FRONT UPPER 1331352-1

PANEL AFT WALL,UPPER 1331642-3

SHELF, RF, LOWER 1331556-1

SHELF, RF, UPPER 1331491-1

SUPPORT PANEL, LOWER 1331447-1RIGHT FRONT

PAN EL, SIDEWALL, RIGHT 1331650-4LOWER

!PANEL SUPPORT, RIGHTFRONT UPPER

PANEL, SIDEWALL, RIGHT-UPPER

PANEL TOP

PANEL SIDEWALL LEFT


SHIELD, WARMLOAD, LOWERRIGHT




1331390-1

1331651-1

1356866-1

1356626-1

1331445-1

1331405-1

1331647-1

1331646-1

1331600-1



CALIBRATION SOURCE ASSY,

WL ILOW}CALIBRATION SOURCE ASSY,

WLIUPIBEAM SUPPORT

REFLECTOR ASSY (LOWER)

REFLECTOR ASSY (U PPER)

1331380-1

1331380-2

1331406-1

1365777-1

1365777-1

MATERIAL/ YIELD

ALLOY (PSI)

ALUM/6061-T651 35000

ALUM/7075-T651 65000

A LU M/7075-T651 66000

ALUM/6061 -T651 35000

ALUM/2024-T851 58000

ALUM/6061 -T651 35000

ALUM/7075-T651 66000

ALUM/2024-T851 58000

BE/SR-2OOE 50000

BEJSR-2OOE 5O0O0

ALUM/6061 -T651 35000

ALUM/OO61 -T6 35000

ALUM/6061-T651 35000

ALUM/6061-T6 35000

ALUM/OO61 -T6 35000

ALUM/6061 -T6 35000

ALUM/6061-T6 35000

ALUM/6061-T6 35000

ALUM/6061 -T6 3500O

ALUM/6061 -T6 350OO

ALUM/6061-T6 35000

ALUM/6061 -T6 3500O

ALUM/6061-T4 16000

ALUM/6061-T6 35000

ALUM/6061-T6 35000

ALUM/6061-T6 35000

ALU M/7075-T6 65000

ALUM/7075-T6 66OOO

ULTIMATE 3 SIGMA MARGINS OF SAPk'f Y'

(PSI) STRESS (PSI) YIELD ULTIMATE

42000 25654 0.09 0.17

75000 39937 0.32 0.34

75000 43788 0.21 0.22

42000 24692 0.13 0.21

66000 43374 0.07 0.09

42000 17148 0.63 0.75

75000 43260 0.22 0.24

66000 43774 0.06 0.08

70000 6641 4.85 6.31

70000 7067 4.66 6.08

42000 23766 O. 18 0.26

42000 26502 0.06 0.13

42000 21390 0.31 0.40

42000 25894 0.08 0.16

42000 2215 11.64 12.54

42000 3432 7.16 7.74

42000 5487 4.10 4.47

42000 6192 3.52 3.84

42000 7674 2.65 2.91

42000 8641 2.17 2.39

42000 6810 3.11 3.41

42000 11730 1.39 1.56

30000 3076 3.16 5.97

42000 4729 4.92 5.34

42000 3537 6.92 7.48

42000 9174 2.05 2.27

75000 9393 4.62 4.70

75000 14595 2.62 2.67

*SEE FIGURES 1 & 2

5-8

Report 10381

Addendum 1

ITEMqO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

18

19

20

21

22

23

23

24

25

26

27

28

TABLE 6


RANDOM VIBRATION IN X - DIRECTION

DESCRIPTION




PANEL, FRONT, LOWER

PANEL, AFT, LOWER

BASEPLATE, UPPER

PANEL, FRONT UPPER

PANEL, AFT WALL, UPPER

'SHELF, RF, LOWER

SHELF, RF, UPPER

SUPPORT PANEL LOWER RIGHT FRONT

PANEL, SIDEWALL, RIGHT LOWER

PANEL, SUPPORT, RIGHT FRONT UPPER

PANEL, SIDEWALL, RIGHT-UPPER

PANEL,TOP

PANEL, SIDEWALL, LEFT

SHIELD, WARMLOAD, LOWER LEFT

SHIELD, WARMLOAD, LOWER RIGHT

SHIELD, WARMLOAD, UPPER LEFT

SHIELD, WARMLOAD, UPPER RIGHT




CALIBRATION SOURCE ASSY, WL (LOW)

;CALIBRATION SOURCE ASSY, WL (UP)

BEAM SUPPORT


REFLECTOR ASSY (UPPER)

PART MATERIAL] YIELDNUMBER ALLOY (psi)

1356405-1 ALUM/6061-T651 35000

1331414-1 ALUIVV7075-T651 66000

1331389-1 ALUM/7075-T651 66000

1331401-1 ALUM/6061-T651 35000

1331652-1 ALUM/2024-T851 58000

1331356-1 ALUM/6061-T651 35000

1331352-1 ALUM/7075-T651 66000

1331642-3! ALUM/2024-T851 58000

1331556-1 BE/SR -200E 50000

1331491-1 BE/SR-200E 50000

1331447-1 ALUM/6061-T651 35000

1331650-4 ALUM/6061 -T6 35000

1331390-1 ALUM/6061-T651 35000

1331651-1 ALUM/6061 -T6 35000

1356866-1 ALUM/6061 -T6 35000

1356626-1 ALUM/6061 -T6 35000

1331445-1 ALUM/6061-T6 35000

1331405-1 ALUM/6061 -T6 35000

1331647-1 ALUM/6061-T6 35000

1331646-1 ALUM/6061 -T6 35000

1331600-1 ALUM/6061-T6 35000

1331162-8 ALUM/6061-T6 35000

1331162-8 ALUM/6061-T4 16000

1331380-1 i ALU M/6061 -T6 35000

1331380-2 ALUMJ6061-T6 35000

1331406-1 ALUM/6061-T6 35000

1355777-1 ALUM/7075-T6 66000

1355777-1 ALUM/7075-T6 65000

ULTIMATE 3 SIGMA MARGINS OF SAFETY(psi) STRESS (psi) YIELD ULTIMATE

42000 3474 7.06 7.64

75000 9108 4.80 4,88

75000 7155 6.38 6.49

42000 8328 2.36 2.60

66000 6324 6.34 6.45

42000 8112 2.45 2.70

75000 21998 1.40 1.44

66000 5937 6.82 6.94

70000 5630 6.10 7.88

70000 1859 20.52 25.90

42000 1254 21.33 22.92

42000 5096 3.59 3.92

42000 10314 1.71 1.91

42000 3530 6.93 7.50

42000 1034 26.08 28.01

42000 3432 7.16 7.74

42000 5487 4.10 4.47

42000 6192 3.52 3.84

42000 7674 2.65 2.91

42000 8841 2.17 2.39

42000 1913 13.64 14.68

42000 4113 5.81 6.29

30000 3076 3.16 5.97

42000 1745 15.05 16.19

42000 3537 6.92 7.48

42000 9174 2.05 2.27

75000 9393 4.62 4.70

75000 14595 2.62 2.67

*SEE FIGURES 1 & 2

5-9


ITEM'NO.*

I

2

3

4

5

6

7

8

9

1o

11

12

13

14

15

16

18

19

20

21

22

23

23

24

25

26

27

28

TABLE 7


RANDOM VIBRATION IN Y - DIRECTION

DESCRIPTION




PANEL, FRONT, LOWER

PANEL, AFT, LOWER

BASEPLATE, UPPER

PANEL, FRONT UPPER

PANEL, AFT WALL,UPPER

SHELF, RF, LOWER

SHELF, RF, UPPER

SUPPORT PANEL, LOWER:tIGHT FRONT

PAN EL, SIDEWALL, RIGHT 1331650-4LOWER

PANEL, SUPPORT, RIGHT 1331390-1FRONT UPPER

I PANEL, SIDEWALL, RIGHT- 1331651-1i UPPER

PAN EL,TOP 1356866-1

PANEL, SIDEWALL, LEFT 1356626-1

SHIELD, WARMLOAD, LOWER 1331445-1LEFT

SHIELD, WARMLOAD, LOWER 1331405-1RIGHT

SHIELD, WARMLOAD, UPPER 1331647-1LEFT

SHIELD, WARMLOAD, UPPER 1331646-1RIGHT




CALIBRATION SOURCE ASSY, 1331380-I

WL {LOW)iCALIBRATION SOURCE ASSY,WL {UP}BEAM SUPPORT

REFI PCTOR ASSY (LOWER)


PART MATERIAL/ YIELD ULTIMATE'NUMBER ALLOY (psi) (psi)

1356405-1 ALUM/6061-T651 35000

1331414-1 ALUIvV7075-T651 66000

1331389-1 ALUM/7075-T651 66000

1331401-1 ALUM/6061-T651 35000

1331652-1 ALUM/2024-T851 56000

1331356-1 ALUM/6061-T651 35000

1331352-1 ALUM/7075-T65 1 66000

1331642-3 ALUM/2024-T851 58000

1331556-1 BEJSR-200E 50000

1331491-1 BE/SR-200E 50000

1331447-1 ALUM/6061-T651 35000

ALUM/6061 -T6 35000

ALUM/6081-T651 35000

ALUM/6061-T6 35000

ALUM/6061 -T6 35000

ALUM/6061 -T6 35000

ALU M/6061 -T6 35000

ALUM/6061-T6 35O0O

ALUM/6061 -T6 350OO

ALUM/6061 -T6 35000

ALUM/6061-T6 35OOO

ALUM/0061 -T6 35000

ALUM/6061 -T4 16000

ALUM/6061 -T6 35000

1331380-2 ALUM/6061-T6 35000

1331 406-1 ALU M/6061 -T6 35000

1355777-1' ALUM/7075-T6 66000

1355777-1 ALUM/7075-T6 66000

3 SIGMA MARGINS OF SAFETYSTRESS (psi) YIELD ULTIMATE

42000 9435 1.97 2.18

75000 1989 25.55 25.93

75000 5487 8.62 8.76

42000 8653 2.16 2.39

66000 10845 3.28 3.35

42000 17148 0.63 0.75

75000 14627 2.61 2.66

66000 3939 10.78 10.97

70000 3960 9.10 11.53

70000 2517 14.89 18.86

42000 6177 3.53 3.86

42000 19551 0.43 0.53

42000 21390 0.31 0.40

42000 2557 9.95 10.73

42000 1125 23.89 25.67

42000 2047 12.68 13.66

42000 5085 4.51 4.90

42000 1212 22.10 23.75

42000 5757 3.86 4.21

42000 8175 2.43 2.67

42000 5276 4.31 4.69

42000 4554 5.15 5,59

30000 915 12.99 22.42

42000 2434 10.50 11.33

42000 2199 11.73 12.64

42000 4638 5.O4 5.47

75000 4368 11.09 11.26

75000 8229 5.42 5.51

*SEE FIGURES 1 & 2

5-10


ITEMNO.*

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

18

19

20

21

22

23

23

24

25

26

27

28

TABLE 8


RANDOM VIBRATION IN Z - DIRECTION

PARTDESCRIPTION NUMBER




PANEL, FRONT, LOWER 1331401-1 _

MATERIAL/ALLOY

ALUM/6061-T651

ALUM/7075-T651

ALUM/7075-T651

ALU M/6061 -T651

PANEL, AFT, LOWER 1331652-1 ALUM/2024-T651

BASEPLATE, UPPER 1331356-1 ALUM/6061-T651

PANEL, FRONT UPPER 1331352-1 ALUM/7075-T651

PANEL, AFT WALL,UPPER 1331642-3 ALUM/2024-T851

SHELF, RF, LOWER 1331556-1 BEJSR-2OOE




;PANEL, SUPPORT, RIGHT 1331390-1 ALUM/6061-T651FRONT UPPER

1331651-1PANEL, SIDEWALL, RIGHT-UPPER

I PANEL,TOP

PANEL, SIDEWALL, LEFT

1356866-1

1356626-1

1331 445-1

1331405-1


ALUM/6061 -T6

ALUM/6061 -T6

ALUM/5061-T6

ALUM/6061 -T6

ALUIVl/6061 -T6SHIELD, WARMLOAD, LOWERRIGHT

SHIELD, WARMLOAD, UPPER 1331647-1 ALUM/6061-T6LEFTSHIELD, WARMLOAD, UPPER 1331646-1 ALUM/6061-T6:tIGHT




1331380-1

1331380-2

CALIBRATION SOURCE ASSY,

'WL (LOW)CALIBRATION SOURCE ASSY,

WL (UP}BEAM SUPPORT



1331406-1

1356777-1

1355777-1

ALUM/6061 -T6

ALUM/6061 -T6

ALUM/6061 -T4

ALUM/6061-T6

ALUM/6061 -T6

ALU M/6061 -T6

ALUM/7075-T6

ALUM/7075-T6

YIELD(psi)

35000

660O0

660OO

35000

58000

350O0

65000

58000

50OO0

5000O

35OO0

350O0

35O00

35000

35OO0

35OO0

35OOO

35OO0

35OOO

35O00

35OO0

35OO0

1600O

35000

35OO0

35000

66000

66O00

ULTIMATE 3 SIGMA(psi) STRESS (psi)

42000 9666

75000 1620

75000 199 2

42000 4539

65000 6204

42000 7146

75000 5564

66000 2586

70000 6841

70000 7_7

42000 2641

42000 10_5

42000 9174

42000 926

42000 2215

42000 1852

42000 1872

42000 1719

42000 4911

42000 2202

42000 6810

42000 11730

30000 2161

42000 4729

42000 3137

42000 4452

75000 1998

75000 3825

MARGINS OF SAI-I= I Y

YIELD ULTIMATE

1.90 2.10

31.59 32.07

25.51 25.89

5.17 5.61

6.48 6.60

2.92 3.20

8.49 8.63

16.94 17.23

4.65 6.31

4,66 6.08

10.02 10.81

1.79 1.99

2.05 2.27

29.24 31.40

11.64 12.54

14.12 15.20

13.96 15.03

15.29 16.45

4.70 5.11

11.72 12.62

3.11 3.41

1.39 1.56

4.92 8.92

4.92 5.34

7.93 8.56

5.29 5.74

25.43 25.81

12.80 13.01

*SEE FIGURES 1 & 2

5-11


Tables 9 through 33 not re-evaluated in Addendum I.

5-12


FATIGUE EVALUATION

RANDOM VIB STRESSES Q = 7.1

QUALIFICATION LEVEL- 2 MIN/AXIS

UPPER RIGHT FRONT

SUPPORT PANEL

BAR ELEMENT 2633

STRESS @ 1 SIGMA

STRESS @ 2 SIGMA

STRESS @ 3 SIGMA

EFFECTIVE FREQUENCY

REQ'D CYCLES/STRESS

CYCLES @ 1 SIGMA

CYCLES @ 2 SIGMA

CYCLES @ 3 SIGMA

TOTAL REQ'D CYCLES

MATERIAL 6061-T6

MIL-HDBK-5F FIG 3.6.2.2.8, R = -1.0

ENDUR LIMIT @ 100000000 CYCLES

FATIGUE SUMMARY

X-STRESS @ 3 SIGMA

X-STRESS @ 2 SIGMA

X-STRESS @ 1 SIGMA

Y-STRESS @ 3 SIGMA

Y-STRESS @ 2 SIGMA

Y-STRESS @ 1 SIGMA

Z-STRESS @ 3 SIGMA

Z-STRESS @ 2 SIGMA

Z-STRESS @ 1 SIGMA

CUMULATIVE USAGE

ALLOWAB LE USAGE

X-LOAD Y-LOAD Z-LOAD

3438 7138 3058

6876 14276 6116

10314 21414 9174

217 184 283

X - LOAD Y - LOAD Z - LOAD

17707.2 15014.4 23092.8

7161 6072 9339

1171.8 993.6 1528.2

26040 22080 33960

STRESS REQ'D ALLOWED

LEVEL CYCLES CYCLES

10314 1171.8 100000000

6876 7161 100000000

3438 17707.2 100000000

21414 993.6 524552

14276 6072 28348265

7138 15014.4 100000000

9174 1528.2 100000000

6116 9339 100000000

3058 23092.8 100000000

TABLE 34

USAGE

FACTOR

0.00001

0.00007

0.00018

0.00189

0.00021

0.00015

0.00002

0.00009

0.00023

0.03286

0.80000

5-13


Tables 35 through 53 not re-evaluated in Addendum 1.

5-14


5.4.1 Panel Flange Bending Stresses and Attachment Screw Stresses per RandomVibration Loads

The following pages contain a detailed analysis of panel flange bending stresses andattachment screw stresses per random vibration loads.

5-15


ITABLE 54 A1-EOS PANEL FLANGE BENDING STRESS SUMMARY +RANDOM VIBRATION LOADS

COMPONENT

UPPER RIGHT FRONT SUPPORT

LOWER AFT PANEL

LOWER RIGHT PANEL

UPPER FRONTPANEL

LOWER MOTOR MT PANEL

UPPER MOTORMTPANEL

LOWER FRONT PANEL

UPPER AFTPANEL

UPPER RIGHT PANEL

LOWER RIGHT SUPPORT

PART NO. FLANGE MAT'RL Fty MIN t STRESS FSPSI IN PSI

1331390 ALL 6061 -T6 35000 0.065 19776

1331652 LOWER 2024-T851 58000 0.125 43374

UPPER 2024-T851 58000 0.07

RIGHT 2024-T851 58000 0.07

1331650 LOWER 6061-T6 35000

1331352 LOWER 7075-T6 66000

UPPER 7075-T6 66000

RIGHT 7075-T6 66000

1331414 LOWER 7075-T6 66000 0.05

TOP 7076-T6 66000 0.05

1331389 LOWER 7075-T6 66000

RIGHT 7075-T6 66000

TOP 7075-T6 66000

1.25

1331401 LOWER 6061-T6 35000

UPPER 6051-T6 35000

1331642 LOWER 2024-T851 58000 0.095 41836

UPPER 2024-T851 58000 0.05 37944

SIDE 2024-T851 58000 0.05 43774

1331651 LOWER 6061-T6 35000 0.06 25894

1331447 LOWER 6061-T6 35000 0.045 23766

1.25

41264 1.25

39339 1.25

0.1 26502 1.25

0.04 43260 1.25

0.04 <43260 1.25

0.04 22730 1.25

39937 1.25

15947 1.25

0.05 33345 1.25

0.05 43788 1,25

0.05 <33345 1.25

0.09 24692 1.25

0.05 24476 1.25

1.25

1.25

1.25

1.25

1.25

MS RANGE t

IN

0.42 .065-.075

0.07 .125-.135

0.12 .070-.080

0.16 .070-.080

0.05 .100-.110

0.22 .040-.060

>.22 ,040-.060

1.32 .040-.060

0.32 .050-.060

2.31 .050-.060

0.58 .050-.060

0.21 .050-.060

>0.58 .050-.060

0.13 .090-.100

0.14 .060-.070

0.11 .095-.1050.22 .050-.060

0.06 .050-.060

0.05 .060-.070

0.18 .045-.055

5-16


TABLE 55 A1-EOS PANEL FLANGE A'I-FACHMENT SCREW STRESS SUMMARY - RANDOM VIBRATION LOADS

3OMPONENT PART NO. TYPE MAT'RL FLANGE Ftu LENGTH NO. FORCE STRESS FS MSPSI IN BOLTS LB/IN PSI

UPPER RIGHTFRONT SUPPORT

1331390 NAS1352N06 _,LLOY STEEL LOWER 160000 6.5 3 86.4

NAS1352N06 _LLOY STEEL AFT 160000 6.2 3 70.65

20605 1.4 4.55

16072 1.4 6.11

LOWER AFT PANEL 1331652 NAS1352N06 _,LLOY S/EEL_ LOWER 160000 10.563 8NAS1352N06 ALLOYSTEEL UPPER 160000 8.498 6

NAS1352N06 ALLOY STEEL RIGHT 160000 8.77 7

716.4 104119 114 0.10

213.39 33267 1.4 2.44

206.82 28521 1.4 3.01

LOWER RIGHTPANEL

UPPER FRONTPANEL

1331650 NAS1352N06 ALLOYSTEEL LOWER 160000 19.29 15

1331352 NAS1352N06 ALLOY STEEL LOWER 160000 10.575 7

NAS1352N06 ALLOYSTEEL UPPER 160000 10.575 7

NAS1352N06 AIIOYSTEEL RIGHT 160000 11.5 8

317.64 44963 1.4 1.54

73.227 12177 1.4 8.39

<73.227 <12.177 1.4 >8.3837.665 5960 1.4 18.18

LOWER MOTOR MT 1331414 NAS1352N06 ALLOY STEEL LOWER 160000 10.562PANEL

UPPER MOTOR MT 1331389 NAS1352N06 ALLOYSIP'I=L LOWER 160000 10.563 6_ANEL

NAS1352N06 ALLOYSIP'IzL RIGHT 160000 6.245 3

NAS1352N06 AIIOYST_F-'L TOP 160000 10.563 6

6 89.52 17346 1.4 5.59

76,713 14866 1.4 6.69

99,525 22804 1.4 4.01

<76.713 <14866 1.4 >6,69

LOWER FRONT 1331401PANEL

NAS1352N06 AllOYSTEEL LOWER 160000 10.563 8

NAS1352N06 ALLOY STEEL UPPER 160000 10.288 7

209.49 30446 1.4 2.75

93.741 15165 1.4: 6.54

UPPER AFT PANEL 1331642 NAS1352N06 ALLOY,STEEL LOWER 160000 11.7 9NAS1352N06 ALLOY STEEL UPPER 160000 9.8 7

NAS1352N06 AllOY STI::EI SIDE 160000 11.6 8

383.49 54875 1.4 1.08

111.12 17124 1.4 5.67128.721 20544 1.4 4.56

UPPER RIGHTPANEL 1331651 NAS1352N06 ALLOYSTEEL LOWER 160000 8.783 7

LOWER RIGHT 1331447 NAS1352N06 ALLOY STEEL LOWER 160000 6.5 3SUP PORT

128.472 17743 1.4 5.44

50.532 12051 1.4 8.48

5-17


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5-39

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5-120


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.° .

"I

_ ?..oo_ -i = +, Z_(o

0

5-121


_(,, .'_ _,,4 --- _ & , ¢Jo ,.,e,

_t,.3 _.mJOC) t_

w ....

#,'s , ooqo8¢i_o_?_ pcj_

.... ! "

L,t-- 1P_ - =,

R_-

,t- -I = ÷_.5

i'

_,,) 0 P._'r _,,,,O,d,¢>,,¢_ 5,L_-,_2,u

t..o¢¢¢- (>--'_e,_a"¢ $_ P,_p..-r

vS,,u_ %'R" t._o-,K>_

__:_ _'_i" _-_

5-122

Report10381Addendum l

¢N v_

X(D b a1 r

I

r_.m

i

>:

5-123


5.4.2 Lower Baseplate Mounting Bolts and Pins Stresses per 15g Static Design Loads

The following pages contain a detailed analysis of lower baseplate mounting bolts and pinstresses per 15g static design loads.

5-124


i°!5Z

m

_a: , __._i_.,_o__._ _

ffl

--I,

U

_ _ _. _ _ _ ,_ o _. _ _. _. _. _. _ _ _ _ _ .. o "

k.-

_, _ ",2':"_ _ "- ....

,__ _. _,o,__ _.,._,o_,_,,__

'_. '_.L_.._.._.._..'_.._. _..'_.._ _..'_.. _.._../_.._..'_.._.. _.

R,I

O X

5-125


o

n-

"1-

2

JJB

5

d

-r N_)_-

v/3

JJ

o o o !d o 5

_'1'_ _" '_" _'_" '_" '_'_" '_ _" _''_" '_'!_ "_" '_'_" _;" '_"

_._. _-- ._.._._ ._. _ _0 ._._. _._. _ _

8 8!_8 8;88 _8 OO_8_8 8 _8 °oi88

5-126


5-127


5-128


5-129


s._- o-q_ .

i)

I= i_ I,';,"S,G

7)

5-130


0')z[:L

tlJrr

tDklJb--

_.JO..LIJ¢D

rn

t',-

J

i

I.Ls

ov-:

I/

! i

L Ii I

i i

!

,- L.

T'-0 _'-0

!I

I

I

>-

5-131

EOS AMSU-AI STATIC ANALYSIS

LAUNCH SHOCK LOAD GX-15

POINT ID. TYPE

1 G

4 G

7 G

9 G

12 G

15 G

17 G

21 G

85 G

105 G

127 G

147 G

169 G

189 G

254 G

257 G

261 G

263 G

266 G

269 G

271 G

275 G

FORCES OF S I

T1

-1.258689E+02

-8.93G213E+01

• -1.555324E+02

-1.198174E+02

-1.117775E+02

-1.049295E÷02

-5.776802E÷01

-1.129670E+02

-3 954858E+01

-8 667003E+00

-1 453382E+01

-i 358557E+01

-2 319088E+01

-8 034056E+00

-4 417500E+01

-9 000320E+01

-5 496064E+01

-1 035119E+02

-1 022560E+02

-9.576151E+01

-5.261£57E+01

-7.635905E+01

T2

-1.925428E+01

-3.449354E+00

-1.639825E+01

-2.323261E+00

-1.102563E+00

2.3578COE-01

-5.988444E+00

5.7391_8E+01

5.255445E+00

-1.759135E+01

-7.860929E+00

1.389905E+01

-2.135475E+01

3.189130E+01

1.340856E+01

-5.570083E+00

9.612906E+00

-7.489269E+00

-2.693850E+0G

-3.327263E+00

6.668529E+00

-2.395988E+01

EOS AMSU-AI STAtiC ANALYSIS

LAUNCH SHOCK LOAD GY-15

POINT ID. TYPE

1 G

4 G

7 G

9 G12 G

15 G

17 G

21 G

85 G

105 G

127 G

147 G

169 G

189 G

254 G

257 G

261 G

263 G

266 G

269 G

271 G

275 G

FORCE

I_ o =-'r" #-IP,_ S,

NGLE-PO INT

T3

-1.583812E+02

-4.321259E+01

-1.604990E+02

-5.753431E+01

-1.990412E+01

1.884999E+01

1.526645E+02

2.055744E+02

-5.809161E+01

1.121176E+02

0.0

0.0

-7.277608E+00

9.530946E+01

-2.712557E+01

-3.113841E+CI

-1.239343E+02

-3.609636E+01

-1.180209E+01

5.448496E+00

8.500832E+01

6.002437E+01

S OF SINGLE-POINT

T1 T2 T3

-4.922646E+01 -5.776447E+01 -1.086544E+02

-4.347932E+01 -1.792556E+01 -4.098786E+01

" -8.491455E+00 -1.087068E+02 -2.630446E+02

1.610494E+01 -4.199586E+01 -7.578282E+01

8.147963E+00 -2.741898E+01 -6.838016E+01

1.503447E+01 -2.332141E+01 -7.976778E+01

-2.994038E+01 -1.656991E+01 -2.166770E+02

8.626559E+01 -1.640731E+02 -3.082957E+02

-3.598199E+00 -6.635413E+01 -7.431519E+00

-1.125033E+01 -1.246174E+02 -8.174689E+01

3.137108E+00 -5.558894E+01 0.0

-3.884206E+00 -1.303475E+02 0.0

6.632992E+00 -5.031898E+01 3.664951E+01

8.759583E+00 -7.864672E+01 1.907108E+02

3.523089E+01 -5.222286E+01 2.000888E+01

2.078536E+01 -1.434851E÷01 7.093593E+01

1.390133E+01 -2.838523E+02 2.983871E+02

-1.958684E+01 -3.764598E+01 9.571375E+01

-7.217860E+00 -2.524164E+01 6.485027E+01

-1.238178E+01 -2.386706E+01 6.723901E+01

6.803258E+01 -2.047393E+01 2.224868E+02

-9.297598E+01 -1.839245E+C2 1.837866E+02

5-132

Report10381Addendum l

MAY Ii, 19_5

CONSTRAINT

_%Y ii, 1995

CONSTRAINT


EOS AMSU-AI STATIC ANALYSIS

LAUNCH SHOCK LOAD GZ-15HAY 11, 1995

FORCES OF SI NGLE-POI NT

POINT ID. TYPE T1 T2 T3

1 G -1.938496E+01 -1.031298E+01 -5.532035E+01

4 G -2.114051E+01 -5.205739E+00 -3.193669E+01

7 G " -2.123874E+00 -2.408677E+01 -1.992273E+02

9 G 2.555438E+01 3.230314E+00 -6.137473E+01

12 G 8.647001E+00 4.380313E+00 -4.614014E+01

15 G -2.639420E+00 8.850567E+G0 -4.880497E+01

17 G -4.054764E+01 4.674185K+00 -1.398236E+02

21 G 6.168258E+01 -5.916256E+01 -5.882284E+01

85 G -1.630356E+01 -1.521022E+00 -5.358508E+01

105 G 7.041644E+0C 4.292433E+01 -1.235561E+C2

127 G -3.645182E+00 -8.849172E-01 0.0

147 G 1.124046E+01 -1.528708E+00 0.0

169 G -1.144201E+01 -1.275482E+01 -5.711489E+01

189 G 3.653283E+00 -4.854662E+01 -1.712159E+02

254 G -7.883881E+00 1.581296E÷01 -1.267313E+00

257 G -2.067689E+01 -5.077182E+00 -6.299686E+01

261 G 7.427674E+00 5.385385E+01 -1.468824E+02

263 G 1.966401E+01 -3.097493E+00 -6.651685E+01

266 G 3.598240E+00 -8.165441E+00 -3.99C044E+01

269 G 8.849655E+00 -1.037084E+01 -4.03C9i7E+01

271 G -5.964692E+01 3.574720E-01 -1.547499E+02

275 G 4.807593E+01 5.663111E+01 -4.568103E+01

_.._o_0

"T" 0

"r" ,,..'r a.

CONS TRA I NT

5-133

g


F=, = FL-_ .k_, F+., |

F L = N?.,L ¢,_

.q=__coy,._C> e' =..._1=_ ,..0. = _,_tP OF "r_l_P..,_L..-_ = . _ _.,,_ -z.,;.-=- .'z.s" .+."_= -t-.o0 r

i.., "¢÷"¢'_& ""[ _,F.., _PD_,'_ o_l.,_ P,e.OP

J_ • _-_ _-_,_ I.E.I _

V'_= _ _t-t%_,, __ • GI qZ_c_o

-t : -qH_l •

5-134


w'_: _ _, -

"I"E,_ &tOAJ

5(.., I=6 uJ

c_

¢-I:.- r-I _-I

_,,, _.'_q,r. :. • "aoH

R. -- ,___

_,_ _ _'__..- . __._. : ._$_j

P_, S.H_A£ IQI,.,'rI1_'r'IE,

5-135


31t

5-136

ALLO't STaSL- P,_S. P_e-


"_'_",_,,-_,u._ ,__,j_ _] .%_

_._.__

._- I! '_.... --_"-_

V,FWPSCALE: 2/.I

PEF

I]'EMS 28 AND 48

ilj .040.035

---r !•38l

3750 .... 28

- _'3745A_u ITEM

O86-561,1NL" 2R IttRLI C*N[" WALL;ItCM5 I AND 28 _. ,d

VIEW NSCALE : 2/I

15" _:2" / L,_ .5939"_

.062-_\_" ' /_3_- 2 ONLY

.o3_-_\\ I /,__L \-,\ .

R F Utt _"----_ _ ..230

• ,o,.,.,

,\J .

.375

5-137


qB_"_--- L.@

di.-- ._c_¢oo 6,. - o. ¢,,&

_ u-rl ¢v,,A-,r_ _f =" I,_

_, - _,_ ,_ _.5_ _i

• \_

a_ _---r'_

"L"1_O _

5-138


_,-- (.a,__.._,') =

_c7 ---

#

-- ÷ Z,'_

, -- : _17_'3 ps,:..

V_5=

5-139

UL.T_ATG ,_

Report 10381

Addendum 1

EOS AN-SU-A± $_ATIC A_qALYZ£3

LAUNCH_SHOCK_LOAD GX- 15

POINT ID. TYPE

1 G

4 G

7 G

9 G

12 G

15 G

17 G

21 G

85 G

105 G

127 G

147 G

169 G

189 G

254 G

257 G

261 G

263 G

266 G

269 G

271 G

275 G

FORCES OF

T1

0.0

0.0

0.0

0.0

0.0

0 0

0 0

0 g

0 3

0 0

-9 848364E+02

-6 203901E+02

0 0

0 0

0 0

0 0

0 0

0.0

0.0

0.0

0.0

0.0

S I NGLE-P O :

T2

0.0

0.0

0.0

0.0

0.0

O.0

O.0

0.0

0.0

0.0

-I. 957444E_-00

I. 957444E+0C

C.0

0.0

0.0

0.0

0.0

0.0

0.0

G.0

0.0

0.0

T3

-i. 485400E+02

-3.155964E+01

-1. 606117E+02

-5.649572E+01

-1. 992761E+01

1. 712983E+01

1. 595522E+02

1. 940879E+02

-8. 084093E+01

1. 166457E+_2

0.0

0.0

-2. 474701E+01

1. 065255E+02

-1.44858_E+01

-3. 174564E+01

-1. 137115E+02

-3. 900265E+01

-1.144709E+01

5. 779668E+00

8. 338869E+01

5. 000587E+01

EOS .%/MSU-AI 3TA'_'IC A,_Ab_,bi;_

LAUNC H__SHOC K_LOAD_G Y = 15

POINT ID. TYPE

1 G

4 G

7 G

9 G

12 G

15 G

17 G

21 G

85 G

105 G

127 G

147 G

169 G

189 G

254 G

257 G

261 G

263 G

266 G

269 G

271 G

275 G

FORCES OF SINGLE-POI

TI T2 T3

0.0 9.0 -7.765912E+01

0.0 0.0 -3.411418E+01

0.0 C.0 -2.643308E+02

0.0 C.0 -8.226789E+01

0.0 C.0 -7.924261E+01

0.0 0.0 -8.992119E+01

0.0 0.0 -2.211956E+02

0.0 0.0 -2.993695E+02

0.0 0.0 -1.207610E+01

0.0 0.0 -1.094637E+02

8.818773E+00 -6.744928E+02 0.0

-8.818773E+00 -9.307338E+02 0.0

0.0 5.0 4.529426E+01

0.0 0.0 2.281156E+02

0.0 0.0 1.687144E+01

0.0 0.0 7.181385E+01

0.0 0.0 2.525800E+02

0.0 O.0 9.802837E+01

0.0 3.0 7.032902E+01

0.0 0.0 7.296421E+01

0.0 0.0 2.327888E+C2

0.0 C.0 1.808551E+02

5-140


EOS AIZSU-AI STA?IC ANALYSISLAUNCH SHOCK LOAD GZ-15

POINT ID. TYPE1 G4 G7 G9 G

12 G15 G17 G21 G85 G

105 G127 G147 G169 G189 G254 G257 G261 G263 G266 G269 G271 G275 G

FORCES

T10.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.

-I. 271475E+01 2.1.271475E+01 -2.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 0.0.0 3.0.0 0.0.0 0.0.0 O.

OF SING

T20 -50 -30 -20 -60 -40 -40 -i0 -50 -50 -1596414E-02 0596429E-02 00 -50 -10 20 -60 -10 -60 -30 -30 -10 -4

LE -P 0 I

T3179372E+01265757E+01059886E+02171374E+01586i98E+01759489E+01.416723E+02.164100E+01.265801E+01.266990E+02.0.0.745068E+01.748955E+02.310870E-01.460750E+01.454034E+02.695461E+01.945700E+01.842529E+01.582297E+02._75319E+01

5-141


• 1gO-32UN F .C._$ SCREW, SUPPl. I ED BY I NSTALLAT I Off CONTRACTOR

FLAT WASHER, CRIES.44000 X. 195 10 X.060 THK

ISOLATCR,,435(]) X .2150 Till(

MIN

ISOLATOR, O-IOCR.SgO OD X .310 THKNOM.C(3tdOINED CONIXICTANCE

FOR ISOLATORSAI_BOLT IS ,031g Btu/hr "F

VIEW ]3SCALE: 2/1

I _-" ;05 .22 ITEM 26 /-¢.069-.07_ II'IRLI ONE WALL

/_ (_s'-_3-_ '',-_ F /ITEMS I AND _6._ll//_ _o-7%_.-,_,H_ooN_,_,

/

/|

(.ooo_,_--ll-- _,,E._ooo>

5-142 VIEW I-i,20 PL

SCALE : 2/1


P Re..,-o _,0

F/A v_,G, o--_(,, 2.

fV_r__-- I _aO00 "-! ÷ I,_1,4 x'_(,,2.qO

__=--_ . ol'> ._'_w..Oo _ --- ,,_'_"_

I"=/A = _= :

_,I IZ.5-143

_..D ._-_


I ,,4 -t. _v-t_ I- _ ; _" Z.(o leo_.A-x'orC

A-- "_/4(._'_-.7-e__} = .o_ _=

l_

.oEb

i .z'_ ..x.) _97._

i"._..A'?'OA OD _--_o -?-- (.,o'_o ") = . _o ¢%'x-i _,J

A = "_/__._o_-.__ --., _, ,,_

_f_'x_ _ -_0__ --- ÷__,,_

5-144

F/R-- I-_,. = _e, zo eel, Z._'4


,m_ ,rob "IP

|,_ "_S (dLO

t|

e._--" -HOH e.

"P.,= - _SO

m

,",T,,= 1 ,"t x "Z.'_

5-145

Report 10381 'Ad.dendum 1

_'_,,A% I _v_._ ,_,_.

_--_ __.._C_ Fv_ A

A- (- _g=,)(._-_m) : .)_e_. ,_-

i,_ i "t'1-i

-I=

_J--

5-146

,_0 oO


/.-e. = • IC_O

, _,_-_,,_"

= o _ ,,.a"T

5-147


5.4.3 Thread Shear Stresses in Attachment Hardware per Random Vibration Loads

The following pages contain a detailed analysis of thread shear stresses in attachmenthardware per random vibration loads.

5-148


TABLE 57 AMSU EOS-A1 THREAD SHEAR PER RANDOM VIBRATION LOADS

I I I I1331650 LOWER RIGHT PANEL TO 1356405 LOWER BASEPLATE

LOADCASE

RANDOM

Y

INT/EXT PRELOADTHREADS

LB

INTERNAL 399

.216-28UNF-2B

BASEPLATE

6061-T6

EXTERNAL 399

.216-28UNF-2A

MS51830-103INSERT

CRES 303

INTERNAL 399

.138-32UNRC-3A

M $51830-103

INSERT

CRES 303

EXTERNAL 399.138-32UNJC-3B

MS1352N06-6SCREW

ALLOY STEEL

APPLIED APPLIED JOINT TOTALLOAD LOAD STIFFNESS LOAD

LB FS FACTOR LB

408 1.4 0.565 722

408 1.4 0.565 722

408 1.4 0.513 692

408 1.4 0.513 692

SHEARAREASQ. IN

THREAD ALLOWABLE MARGINSHEAR Fsu OF

PSI PSI SAFETY

0.0355 20330 27000 0.33

0.025 28869 48000 0.66

0.0344 20117 48000 1.39

0.0287 24112 96000 2.98

5-149



I I I I1331414 LOWER MOTOR MOUNT PANEL TO 1356405 LOWER BASEPLATE

LOADCASE

RANDOMY

INT/EXTTHREADS

INTERNAL.216-28UNF-2B

BASEPLATE

6061-T6

EXTERNAL

.216-28UNF-2A

MS51830-103

INSERT

CRES 303

INTERNAL 399

.138-32UNRC-3A

M$51830-103

INSERTCRES 303

EXTERNAL 399

.138-32UNJC-3B

MS 1352N06-6

SCREW

ALLOY STEEL

PRELOAD

LB

399

399

I I IAPPLIED APPLIED JOINT TOTAL SHEAR THREAD

LOAD LOAD STIFFNESS LOAD AREA SHEARLB FS FACTOR LB SQ. IN PSI

158 1.4 0.602 532 0.0355 14990

158 1.4 0.602 532 0.025 21286

158 1.4 0.56 523 0.0344 15200

158 1.4 0.56 523 0.0287 18219

ALLOWABLE MARGINFsu OFPSI SAFETY

27000 0.80

48000 1.25

48000 2.16

96000 4.27

5-150

Report10381AddendumI


I I I I I1331447 LOWER RIGHT FRONT SUPPORT PANEL TO 1356405 LOWER BASEPLATE

LOADCASE

RANDOM

Y


LB

INTERNAL 399

.216-28UNF-2B

BASEPLATE

6061 -T6

EXTERNAL 399

.216-28UNF-2AMS51830-103

INSERT

CRES 303

INTERNAL 399

.138-32UNRC-3AMS51830-103

INSERT

CRES 303

EXTERNAL 399

•138-32UNJC-3B

MS1352N06-6

SCREWALLOY STEEL

I I IAPPLIED APPLIED JOINT TOTAL SHEAR THREAD

LOAD LOAD STIFFNESS LOAD AREA SHEARLB FS FACTOR LB SQ. IN PSI

110 1.4 0.606 492 0.0355 13868

110 1.4 0.606 492 0.025 19693

110 1.4 0.565 486 0.0344 14128

110 1.4 0.565 486 0.0287 16934

ALLOWABLE MARGINFsu OFPSI SAFETY

27000 0.95

48000 1.44

48000 2.40

96000 4.67

5-151



I I I I I1331652 LOWER AFT PANEL TO 1356405 LOWER BASEPLATE

LOADCASE

RANDOMY


LB

INTERNAL 399

.138-32UNJC-3B

MF1331-06ANCHOR NUT

A286 STEEL

EXTERNAL 399

.138-32UNRC-3ANAS1352N06-8

SCREW

ALLOY STEEL

APPLIED APPLIEDLOAD LOAD

LB FS

946 1.4

946 1.4

JOINT

STIFFNESSFACTOR

0.434

0.434

FACTOR

0.362

0.362

TOTAL SHEAR THREAD ALLOWABLE MARGINLOAD AREA SHEAR Fsu OF

LB SQ. IN PSI PSI SAFETY

974 0.0341 28557 84000 1.94

974 0.0208 46817 96000 1.05


652 0.0341 19117 84000 3.39

652 0.0208 31341 96000 2.06

1331642 UPPER AFT PANEL TO 1331356 UPPER BASEPLATE

RANDOM

X

LB

INTERNAL 399

•138-32UNJC-3B

MF1 331-06

ANCHOR NUT

A286 STEEL

EXTERNAL 399.138-32UNRC-3A

NAS1352N06-10

SCREW

ALLOY STEEL

LB FS

499 1.4

499 1.4

5-152


ITABLE 57 AMSU EOS-A1 THREAD SHEAR PER RANDOM VIBRATION LOADS

i I I I I1331651 UPPER RIGHT PANEL TO 1331356 UPPER BASEPLATE

LOADCASE

RANDOMY


LB

INTERNAL 399.138-32UNJC-3B

MF1331-06

ANCHOR NUT

A286 STEEL

EXTERNAL 399.138-32UNRC-3A

NAS1352N06-10

SCREW

ALLOY STEEL

I J I IAPPLIED APPLIED JOINT TOTAL SHEAR THREAD ALLOWABLE MARGIN

LOAD LOAD STIFFNESS LOAD AREA SHEAR FSU OFLB FS FACTOR LB SQ. IN PSI PSI SAFETY

161 1.4 0.322 472 0.0341 13829 84000 5.07

161 1.4 0.322 472 0.0208 22672 96000 3.23

1331389 UPPER MOTOR MOUNT PANEL TO

RANDOM

Y

LB

INTERNAL 399

•138-32UNJC-3B

MF1331-06

ANCHOR NUT

A286 STEEL

EXTERNAL

.138-32UNR_3ANAS1 352N06-6

SCREW

ALLOY STEEL

1331390 UPPER RIGHT FRONT

LB FS FACTOR

207 1.4 0.505

399 207 1.4 0.505

SUPPORT PANEL

LB SQ. IN PSI

545 0.0341 15993

545 0.0208 26219

PSI SAFETY

84000 4.25

96000 2.66

5-153



I I I I I1331401 LOWER FRONT PANEL TO 1356405 LOWER BASEPLATE

LOAD INT/EXTCASE THREADS

RANDOM INTERNALY .138-32UNJC-3B

MF1331-06

ANCHOR NUT

A286 STEEL

PRELOAD APPLIED APPLIED JOINT TOTAL SHEAR THREADLOAD LOAD STIFFNESS LOAD AREA SHEAR

LB LB FS FACTOR LB SQ. IN PSI

399 277 1.4 0.457 576 0.0341 16898

EXTERNAL

.138-32UNRC-3A

NAS1352N06-6

SCREW

ALLOY STEEL

TABLE 57 AMSU EOS-A1 THREAD

I1331401 LOWER FRONT PANEL TO 1356405

399 277 1.4 0.457 576 0.0208 27703

SHEAR PER RANDOM VIBRATION LOADS

I I ILOWER BASEPLATE

RANDOM

Y

INTERNAL 399 277 1.4 0.586 626

.216-28UNF-2B

PANEL6061 -T6

EXTERNAL 399 277 1.4 0.586 626.216-28UNF-2A

MS51830-103INSERT

CRES 303

INTERNAL 399 277 1.4 0.541 609.138-32UNRC-3A

MS51830-103

INSERT

CRES 303

EXTERNAL 399 277 1.4 0.541 609

.138-32UNJC-3BMS1352N06-6

SCREW

ALLOY STEEL

0.0355

0.025

0.0344

0.0287

17641

25050

17698

21213

ALLOWABLEFsuPSI

64OOO

96000

27000

480OO

480OO

96000

MARGINOF

SAFETY

3.97

2.47

0.53

0.92

1.71

3.53

5-154



I I I I I1331389 UPPER MOTOR MOUNT PANEL TO 1331356 UPPER BASEPLATE

LOADCASE

INT/EXT PRELOAD APPLIED APPLIEDTHREADS LOAD LOAD

LB LB FS

INTERNAL 399 134 1.4.216-28UNF-2B

BASEPLATE

6061 -T6

EXTERNAL 399 134 1.4

.216-28UNF-2A

M $51830-103INSERT

CRES 303

JOINTSTIFFNESS

FACTOR

0.601

0.601

0.561

0.561

RANDOMY

TOTAL SHEAR THREAD ALLOWABLE MARGINLOAD AREA SHEAR Fsu OF


512 0.0355 14415 27000 0.87

512 0.025 20470 48000 1.34

504 0.0344 14658 48000 2.27

504 0.0287 17569 96000 4.46

INTERNAL 399

.138-32UNRC-3A

M $51830-103

INSERTCRES 303

EXTERNAL 399

•138-32UNJC-3B

MS1352N06-6

SCREW

ALLOY STEEL

134 1.4

134 1.4

5-155



I I I I I1331352 UPPER FRONT PANEL TO 1331356 UPPER BASEPLATE

I ILOAD INT/EXTCASE THREADS

RANDOM

Y

PRELOAD APPLIED APPLIEDLOAD LOAD

LB LB FS

INTERNAL 399

.216-28UNF-2B

BASEPLATE

6061 -T6

EXTERNAL 399.216-28UNF-2A

MS51830-103

INSERT

CRES 303

INTERNAL 399

.138-32UNRC-3A

MS51830-103

INSERT

CRES 303

EXTERNAL 399

.138-32UNJC-3B

MS 1352N06-6

SCREW

ALLOY STEEL

111 1.4

111 1.4

111 1.4

111 1.4

JOINT TOTAL SHEAR THREAD ALLOWABLE MARGINSTIFFNESS LOAD AREA SHEAR Fsu OF

FACTOR LB SQ. IN PSI PSI SAFETY

0.605 493 0.0355 13888 27000 0.94

0.605 493 0.025 19721 48000 1.43

0.566 487 0.0344 14156 48000 2.39

0.566 487 0.0287 16967 96000 4.66

5-156



I I I I I I1331390 UPPER RIGHT FRONT SUPPORT PANEL TO 1331356 UPPER BASEPLATE

LOADCASE

RANDOM

Y

INT/EXT PRELOAD

THREADSLB

INTERNAL 399

.216-28UNF-2B

BASEPLATE6061 -T6

EXTERNAL 399

.216-28UNF-2A

MS51830-103

INSERT

CRES 303

INTERNAL 399

.138.32UNRC-3A

MS51830-103

INSERT

CRES 303

EXTERNAL 399.138-32UNJC-3B

MS1352N06-6

SCREW

ALLOY STEEL

APPLIED APPLIED JOINT TOTAL SHEARLOAD LOAD STIFFNESS LOAD AREA

LB FS FACTOR LB SQ. IN

187 1.4 0.586 552 0.0355

187 1.4 0.586 552 0.025

187 1.4 0.541 541 0.0344

187 1.4 0.541 541 0.0287

THREAD ALLOWABLE MARGINSHEAR Fsu OF

PSI PSI SAFETY

15561 27000 0.74

22097 48000 1.17

15716 48000 2.05

18837 96000 4.10

5-157


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5-191


5.4.4 Large Masses Attachment Screw Stresses per Random Vibration Loads

The following pages contain a detailed analysis of large masses attachment screw stressesper random vibration loads.

5-192


5-193


'%';_% % Oq_ l.;_3-r

e-,'P.%'_

¢_oe. -,to,

COMPONENT GRID LOAD

DIRECTION

LARGE MASS 65050 XYZ

DC/DC CONVERTER 1408 X

_ ._ ...... yZ

1400 XYZ

....... __x

X-RESPONSE

RMS GRMS Q

RESPONSE OF LARGE MASSES O=7.1

- I Y-RESPONSE

RMS GRMS Q

3897 10.09585 1.0

0 0 0.00 0 0.0

6940 17.97927 1.8948 ! 2.455959 0.2

1338 3.466321 0.3

3911 10.13212 1.01239 3.20_45 0.33503 9.07513 0,9

3742 9.694301 _ 1.0 __

0

38970

111642_2832

86339981825

_ 843

0 0.0

10.09585 1.00 0.0

2.891192 0.311.02073 1.17.336788 0.7

2,235751 0.210.35751 1,04.727979 0.5

2.,e_9_ 0.2 ]

__-_]__-E._.3iZ11._o,__.I__1.1 .

___1 .... 1....

Z-RESPONSERMS GRMS Q

0 0 0.00 0 00

3as7 To.osss- i _-

3074 7.96373 0.8787 2.03886 0.25789 14.9456 1.5

3000 7.77202 0,8785 2.03356 0.2

5616 14.54_2 1.4-...

.__3_s 7._4O,il .... o.e1235S3iP-

1318__

5-194


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_'_. = z,-¢t. = "lq_..'T __%

_'-Ot k3-r- _ W.__.T c._4

l'' , , , I,_u'r' .D._? .,._S_._%i /.,__.oOb

5-195


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5-196


5-197

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5-198

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5-199

_'m:.-,r.=,_r._ _...P+_m"+_ ,me" ,_+'t'_':r,,_.C_S,,,.ST Report 10381Addendum 1

• I

COMPONENT

DETECTOR PREAMP

I, GRID LOAD I X-RESPONSE

DIRECTIONII RMS I GRMSF Q

999 X I J 9362 1'24.25389.11 2.4Y I I 3219 18.3393781 0.8!

.... Z I | 1045 ]2.707_$4| 0.3 J

_-.l...j_- _ I I:_4a_:-i+ l

.....................z1+m _--7-I----_-:I_+.+:I++_]+._-_W_]" " - Y I I ,_-F_9 +-_+_--I

++-oo+..... _-- Tr-mm-T;+.m.-.-._r-+:+--i

IY-RESPONSE i Z-RESPONSE

RMS I GRMS I O _ RMS GRMSI(:3

618 11._010,,3_ l 0.2 709 J I._79_ @_2

3327 8.6191711 0.9 580 1.50259 I 0.1

"1.7875651 0..2__ . , 37 ___.___9.6______5_ _

.72S 1.+m___+_+0:._; :"i4_ _77"[ -"0.--:_--3402 8.8134721 0,9 1390 3.60104 I 0.4

- I-_@- 3.m7_,41 0.3 " 1600 ' 4.145081 0-4 '-_

_3s_.._]9.__.1243sL_.)# ! 657__ 1.7_7_. o._2 j

5-200


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5-201

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5-202

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5-203


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5-204


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5-205

•Report10381Addendum1

5-206


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5°207


COMPONENT GRID LOAD X-RESPONSE Y-RESPONSE Z-RESPONSEDIRECTION I RMS. I GRMS I Q RMS GRMS ! Q RMS i GRM_ -'_-

- --- _.-----,. . L =-..L_-_ _ ...... _....... ,._ ' .... _ -_ - .... .....

PI,,,,O _ ,1_1_____._. 735 _ _. _X J j 4591 L11.89378L_l.2 L = 915 L2.370_o6 0.2 ; ! '1,._10 _ 3.96964 ! 0.4._ Y [ f 1688 '4.373057l 0_1---[-_3_B,._9---1994,5596 '- "10 ' '--1385- ,-'_n,'

- _ ...................... t-+ ....... ' ___ _ • . .._ 0.4...... • . ___8___ Zl_ 0,2 _ 755=-_._9 :-_-3_'_3-t957098: _.o.........._ ...... __ ...........__....__'. __._........_ _ . ; :

...... _ .... _-----Y-'----i-1648_ 4.26943__,_ 0.4 !__ 41_64 i_10.78756_.. 1.1 ' 1 2573 6.6658 0.7

......"........; --_--_---8+-7-!-_=_--_mi-o_:___i_._____2=______o._ , i __ I.S

...... _ ___ Z j 1188_3+07772' 03_--_-I-7-56--11:_5497 02 ! -3621 ,-938083' u,

, r---- -_._ .... .... ;;.... -_---- ,--_, : ..... _ ,...... _- " __- . -t "_ + 0.9

1 804 ! X+____+ _ 4428 , 11+++4715+" 1 I_ + 1117 i2.893782i 0.3 i ' 2687 i696114'

.... _-...... i .....Y____.__13.$2._.'350_2____ 0.3-ii 4160--I0.77"I'_-1.I i i 21Y0-!5.62176 I 0.7

__._......_. _z____ 11z0_3.031_0_-03---__-_5_21_0.2 Y÷-S,2-__32_5-"os_.3

"r = .. -z FL&

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5-209


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5-210

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= '_(.=,.S =Is,


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5-211

t_J


r i i I ] ' RESPONSE OF LARGE MASSES 0=7.:1 I I ._

_t'O--"[l'_t"_"l_ Y I 1189 13.080311j 0.3 i ] 3972 [10.29016_--___-i-352_]_-3:50259! 0"3

I I Z 1614 4 1813471 0 4 ' 7R ¢; 1 g61865-r--_-.2-- _ 4_6--T i1_-1 .... i:-

........ -:___ x _ 4,_0:______.,_ 11__3.0_0_0.3_!--_,8-:-,_._: 0.,....... --_--------- Y I i 1188 .... _3.07772 I 0.3 _-i 42_-[__I--___.--1988--T-5..150_:, 05 "

_. Z , 1613 4178756 04 ', ' _-q, 23_34 02 --_ ;...... _ ;| 1R

....... _[. .... !.... _ ....... ,_._.._I c.. ,.___ . . _4_ o. _ . _76L16._1;, .._

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;:: "t:.z. ,z. "


= _b_,_

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_bIkJ

5-213

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--_-I=,,_ -- . .......... -1.0 ' _ 1568 _ .,___b_l__J__O_...__._++ 1963 5+08549: 0.5

jlC..___'T_-O'IV_ 1196 t3.098446 O.m_3 _25_1__1224093J______J_.2 i I_--14---- 6.51295: 06

..... -7-__ -i_-_-_7.......... - ...... _..................... _ +....... , o++K [ Y 1 1191 130854921 0.3_--471_, +J_I-'E_._I_--"I--I_-- i _r-_3 - -_.4-171 I 0.7-

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5-217

Addendum 1i !

i _ ' RESPONSE OF LARGE MASSES Q=7 1 _

COMPONENT GRID LOAD I X-RESPONSE ] [ Y-RESPONSE Z-RESPONSE

........ _____+__ _.4____L_o.3A_,__413o ilO..__e___:_!._ ,' _ _: r_.419_'9 0.2

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5.4.5 Lower Baseplate Stresses per Random Vibration Loads

The following pages contain a detailed analysis of lower baseplate stresses per randomvibration loads.

5-254

Report 10381

Addendum 1

TABLE 59 A1-EOS 1356405 LOWER BASEPLATE STRESSES - RANDOM VIBRATION LOADS

STRESS LOAD LOCATION MATERIAL 3s STRESS Fty/Ftu FS MARGIN OFCATEGORY CASE PSI PSI SAFETY

STRESSES UNDER

LOWER CARD CAGE

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LOADCASE

LOCATION MATERIAL 3s STRESS Fty/Ftu FS MARGIN OFPSI PSI SAFETY

RANDOMY LOWER FRONT_ 6061-T6 18594

ATTACHMENTS PANEL 18594

RANDOM Y LOWER AFT 6061 -T6 25654

RANDOM Y

STRESS LOADCATEGORY CASE

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PANEL 25654

LOWER RIGHT 6061-T6 8737

PANEL 8737

LOCATION MATERIAL

35000 1.25 0.51

42000 1.4 0.61

35000 1.25 0.09

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35000 1.25 2.20

42000 1.4 2.43

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Appendix A

NASTRAN FINITE ELEMENT MODEL


NASTRAN Mathematical Validity Check

To demonstrate the mathematical soundness of the NASTRAN model, the model is subjectedto the GSFC 422-11-12-01 Paragraph 11.1.4.i Deliverable Model Validity Check, where a rigid-body orstiffness-equilibrium check is performed. Using NASTRAN Solution 3, a DIAG 64 ALTER 126 DMAP is run.The NASTRAN Executive Control Data Deck consists of:

ID AMSU1,RANDOMTIME 60SOL 3$DIAG 64$COMPILE SOL3,SOUIN=MSCSOUALTER 126

VECPLOT, ,BGPDT,EQEXIN, CSTM,,,,/RBGLOBAL/GRDPNT=O//4 $VEC USET/V1/'G'PF'PCOMP' $PARTN RBGLOBAL,V1]RBFF,,$0 $TRNSP RBFF/RBFFT $MPYAD KFF,RBFFTJKFFR/$MATGPR GPL,USET,SIL,KFFR/PF'/H1.E-2 $DIAGONAL KFF/KFFD/OPT='SQUARE'/POWER=. 1. $MPYAD KFFD,KFFRJKFFRN/$

MATGPR GPL,USET,SIL,KFFRN/PF'/HSMALL=I.E.5 $ENDALTERCEND

A NASTRAN correspondence on the rigid-body check describes the requirements of the test.

"The basic function of this check is to multiply through a cross product the free stiffness

matrix by the model rigid body matrix. The matrix which results from this multiplication can be thought ofas the internal forces which must be applied to the structure to overcome any model internal constraint to

achieve the desired rigid body motion. This matrix is titled the KFFR matrix. The smaller the magnitude ofthe numbers in the matrix, the less internal constraint present in the model. The DMAP will print anyvalues larger than 1.0E-2. In an attempt to evaluate the effect of any internal constraint, the KFFR matrixis divided by the diagonal stiffness term of each respective row. The resulting matrix is considered'normalized' and is titled the KFFRN matrix. A satisfactory KFFRN matrix will generally have termsless than 1.0E-5." " " "

Thus terms of the KFFRN matrix need be less than 1.0E-5.

The NASTRAN EOS/AMSU-A1 finite element model has been checked and modified toconform to GSFC 422-11-12-01 Paragraph 11.1.4.i requirements. All terms of the KFFRN matrix are lessthan 1.0E-5. There were, however, modifications to the model required to reach satisfactory equilibrium.These corrections consisted of:

(1)

(2)

(3)

Using large field data transfer from PATRAN to NASTRAN. This eliminatedtruncation errors at several GRID cards and out-of-plane elements.

Modifying GRIDs slightly to insure all GRIDs of an element lie in a plane (i.e. PowerControl Module and the Warmload Housings ).

Constructing several massless, stiffless, CBAR elements in the Reflector Shrouds.

Upon making the above changes, the KFFRN matrix became null. A check of the 1st ten non-

rigid-body modes before and after the model modifications demonstrated no significant change in naturalfrequencies or mode shapes. A comparison table of _before changes" and "after changes" follows.


ModeNo.

Natural Frequency

Before ChangesNatural Frequency

After Ch_ges1 i 108.9 Hz .-" 109.0 Hz

............................ @ ................................................................

2 i 109.0 i 109.0........................................ _ ........................... °°* ............................ T" .......................................................... ° .......

3 109.6.......................................•_...................................... i 109.6. . ................................................................. . ...... ,° ............

4 i 109 7 _ 109.7

5 - 115.9 " 116.3...................._.................:'.......................i'_'i':_.......................?............................................................................................................:.........................................................._............................,1.2.1.:4.........................

7 : 122.2 i 122.2.................... °................ °..._ .............. ,., .............. .., ....... ° ................ ._" ..o...° ........................... °................................

8 i 122.3 _ 122.3...................._.................".--".......................i;i'_'_.......................-............................i¥_?_"...........................

10 i 147.2 i 147.2

The NASTRAN finite element model of the EOS AMSU-A1 module is shown in its entirety inFigure 3 and again in Figure A1 in this appendix. Figure A2 is a section view of the model, showing thecomponents modeled in the interior (i.e. shelves, card cages, warmload structures). Elements and grids arehighlighted in the piece part models of Figures A3 through A58 that are combined to form the A1 modulemodel. The following components are identified:

Component ! FiguresLower Basep.late ! A3-A6

__]_Z_Z__.._.i_9_Z_Z_To_. Panel All-A13

"'_;er"'_i_ei_............................................................................"_/i¥_i'_"......................."f/_7"_ei'_" ...................................................................,"........"X'i'_::_i'_"........................"_w_'7"'_'"i_ei ................................................................"_5"_'_ .........................::_:_-'_'"_e_ .................................................................._:_'_ .........................::::::::::::::::::::::::::::::::::::::::..................................,.........._:_._ ..........................p.._._._......_.o._..L._j...........".............................T........:_DX_i.........................Lower Motor Mount P_'el ......................................"_2"-'X3"_i........................

............. ...................................................................................... _.... ....................................... . ........

-q_--m..._..._°._r..._..°._.L..P.._._........... A35-A37Loft Panel/Beam Sup.p.ort ...................i ........"_'8"-'A3"9 ........................

.... ,°° ........ ° ....... °°.,..° .............................................. . ........... °._ ....................................... _ ..........

Lower Rig..h..t Panel A40-A42

'____ ................................................i.........x_:__ .........................

U_er ...l_.:g..h.tFront Su_t}.ort i A47..,......**,°.....°.....**°.. ...... ,°......,... .... . ......°**°.° ...... ....°. ....... ***T'......,.....**.... ...... ,°....., ......... °....°,°**.,

Lower Left Shield................................................................. i A48

Lower Rig..h.t Shield ................................ i .........A'4"9....................................__ __ ..........................................................x_................................._ _a;_;__ia...............................................i........x_..................................

,.U,,.p.p.er...C,.,,,_,.d,....C,.,age..,_semb.l.y,............................A53

Lower Reflector Assemb.ly.. ........"AS_...................................

,....I_.....w...e..r.....W...armload . StructureA56

._.P.e.r..._'!._::ZZZZ:;;:;;'"Z;;..............._........"_'c_'_X_'_"............Upper Aft Panel w/PCM .................... i ........"_8 ..................................

Addendum 1 shows only the components modified from the June 1995 submittal. These areFigures A23-A25 (Upper Aft Panel), Figure A30 (Upper Front Panel Bars, Beams, and Masses), and newFigure A58 (Upper AR Panel w/PCM).

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4+ TITLE AND SUBTITLE

METSAT Advanced Microwave Sounding Unit-A2(AMSU-A2), Stress Analysis Report, A1 Module

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This addendum supplements Report 10381, dated June 1995, to include a new and more refined finiteelement model.

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4. Title and Subtitle

Integrated Advanced Microwave Sounding Unit -A2

(AMSU-A2), Stress Analysis Report, A1 Module

7. Author(s)

W. Ely

9. Performing Organization Name and Address

Aerojet

1100 W. HollyvaleAzusa, CA 91702

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This addendum supplements Report 10381, dated June 1995, to include a new and more refined finiteelement model.

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53-86

GENERAL INSTRUCTIONS FOR COMPLETING SF 298

The Report Documentation Page (RDP) s used in announcing and cataloging reports. It is important that thisinformation be consistent with the rest of the report, particuary the cover and title page. Instructions for filing ineach block of the form follow. It is important to stay within the lines to meet optical scanning requirements.

Block 1. Agency Use Only (Leave blank)

Block 2. Report Date. Full publication date including day,

month, and year, if available (e.g., 1 Jan 88). Must cite at least

the year.

Block 3. Type of Rebert and Dates Covered. State whether

report is interim, final, etc. If applicable, enter inclusive report

dates (e.g., 10 Jun 87 - 30 Jun 88).

Block 4. Title and Subtitle. A title is taken from the part of the

report that provides the most meaningful and complete

information. When a report is prepared in more than one volume,

repod the primary title, add volume number, and include subtitle

for the specific volume. On classified documents enter the title

classification in parentheses.

Block 5. Funding Numbers. To include contract and grant

numbers; may include program element number(s), project

number(s), tasks number(s), and work unit number(s). Use the

following labels:

C Contract PR Project

G Grant TA Task

PE Program WU Work Unit

Element Accession No.

Block 6. _,l.tJ).g[L_. Name(s) of person(s) responsible for

wdting the report, performing the research, or credited with the

content of the report. If editor or compiler, this should follow the

name(s).

Block 7. Performing Organization Name(s) and Address(as),

Self-explanatory.

Block 8. Performing Organization Report Number. Enter the

unique alphanumeric report number(s) assigned by the

organization performing the report.

Block 9. Sponsoring/Monitoring Agency Name(s) aqrl

Address(es) Self-explanatory.

Block 10. SDonsodn_Monitodng Agency Reports Number. (ff

known).

Block 11. Supplementary_ Notes. Enter information not included

elsewhere such as: Prepared in cooperation with ...; Trans. of

...; To be published in ... When a report Is revised, include a

statement whether the new report supersedes or supplements

the older report

Block 12.a Distdb_on/Availabili .ty Statement, Denotes public

availability or limitations. Cite any availability to the public.

Enter additional limitations or special markings in all capitals

(e.g., NOFORN, REL, ITAR).

DOD See DoDD 523024 "Distnbu#on Statement on

Technical Documents

DOE See authontias.

NASA - See Handbook NHB 22002.

NTIS Leave blank.

Block 12.b Distribution (;(;_

DOD Leave blank.

DOE Enter DOE distribution categories from the

standard Distribution for Unclassified

Scientific and Technical Reports.

NASA - Leave blank.

NTIS Leave blank.

Block 13. _ Include a brief (Maximum 200 words)

factual summary of the most significant information contained in

the report.

Block 14. Sul_ect Term& Keywords or phases identifying major

subjects in the report.

Block 15. Number of Page& Enter the total number of pages.

Block 16. Price Code. Enter appropriate price code (NTIS

only).

Block 17 - 19. Security_ Classification& Self-explanatDry. Enter

U.S, Security Classification in accordance with U.S. Secudfy

Regulations (l.e., UNCLASSIFIED). If form contains classified

information, stamp classification on the top and bottom of the

page.

Block 20. Limitation of Abstract, This block must be completed

to assign a limitation to the abstract. Enter either UL (unlimited)

or SAR (same as report). An entry in this block ts necessary if

the abstract is to be limited. If blank, the abstract Is assumed to

be unlimited.

Standard Form 298 Back (Rev. 2-89

53-56 FORMS (June30,1989)NFSD89-0

PREPARATION OF THE REPORT DOCUMENTATION PAGF

The last page of a report facing the th rd cover is the Report Documentation Page, RDP. Information presented on thispage is used in announcing and cataloging reports as well as preparing the cover and title page. Thus, it is importantthat the information be correct. Instructions for filing in each block of the form are as follows:

Block 1. Re0od NO, NASA report series number, if

preassigned.

Block2. Government Accession No. Leave blank.

Block 3. Recipient's Catalog NO,. Reserved for use by each

report recipient.

Block 4. Title and Subtitle. Typed in caps and lower case with

dash or period separating subtiSe from title.

Block 5. Report Date. Approximate month and year the report

will be published.

Block 6. Performing OrganizaUon Code Leave blank.

Block 7. _ Provide full names exactly as they are to

appear on the title page. If applicable, the word editor should

follow a name.

Block 8. Performing Organization RePort NO, NASA installation

report control number and, if desired, the non-NASA performing

organization report control number.

Block 9. Performing Organization Name and Address. Provide

affiliation (NASA program office, NASA installation, or contractor

name) of authors.

Block 10. Work Unit No. Provide Research and Technology

Objectives and Plants (RTOP) number.

Block 11. Contract or Grant No. Provide when applicable.

Block 12. Sponsoring Agency_ Name and Address, National

Aeronautics and Space Administration, Washington, D.C. 20546-

0001. If contractor report, add NASA installation or HQ programoffice.

Block 13. Tyoe of Report and Period Covered. NASA formal

report series; for Contractor Report also list type (interim, final)

and pedod covered when applicable.

Block 14. Sponsoring Agency_ Code. Leave blank.

Block 15. Supplementary. Notes. Information not included

elsewhere: affiliation of authors if additional space is required

for Block 9, nofice of work sponsored by another agency, monitor

of contract, information about supplements (file, data tapes, etc.)

meeting site and date for presented papers, journal to which an

article has been submitted, note of a report made from a thesis,

appendix by author other than shown in Block 7.

Block 16. &b._,&t.r.6£LThe abstract should be informative rather

than descriptive and should state the objectives of the

investigation, the methods employed (e.g., simulation,

experiment, or remote sensing), the results obtained, and the

conclusions reached.

Block 17. Key Words, IdentJfying words or phrases to be used

in cataloging the report.

Block 18. Distribution Statement, Indicate whether report is

available to public or not. If not to be controlled, use

"Unclassified-Unlimited." If controlled availability is required,

list the category approved on the Document Availability

Authorization Form (see NHB 2200.2, Form FF427). Also

specify subject category (see "Table of Contents" in a current

issue of __T2_]) in which report is to be distributed.

Block 19. Secufify Classification (of the reoor(), Self-

explanatory.

Block 20. Securi.ty Classification (of this page), Self-

explanatory.

Block 21. No. of Pages. Count front matter pages beginning with

iii, text pages including Internal blank pages, and the RDP, but

not the title page or the back of the title page.

Block 22. Price Code. If Block 18 shows "Unclassified-

Unlimited," provide the NTIS price code (see "NTIS Price

Schedules" in a current issue of STAR) and at the bottom of the

form add either "For sale by the National Technical Information

Service, Springfield, VA 22161-2171" or "For sale by the

Supedntendant of Documents, U.S. Government Printing Office,

Washington, D.C. 20402-0001 ," whichever is appropriate.

18-53.303-1626 CFR TITLE 48 CHAPTER 18

REPORT DOCUMENTATION PAGE Form ApprovedOMB No. 0704-0188

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering

and maintaining the data needed, and completing and reviewing the collection ot information Send comments regarding this burden estimate or any other aspect of this collection of

information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite

1204, Arlington, VA 22202-4302, and to the Office of Mana_ement and BudCiet, Paperwork Reduction Project 10704-01881, Washington, DC 20503.

1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVEREDFebruary 1996 Contractor Report

4. TITLE AND SUBTITLE 5. FUNDING NUMBERS

METSAT Advanced Microwave Sounding Unit-A2 (AMSU-A2),

Stress Analysis Report, A I Module

6. AUTHOR(S)

PI: W. Ely

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

Aerojet

1100 W. Hollyvale

Azusa, CA 91702

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)

NASA Aeronautics and Space Administration

Washington, D.C. 20546-(X)01

Code 48 I

Contract: NAS5-32314

8. PERFORMING ORGANIZATIONREPORT NUMBER

CDRL 113-A

10381, Addendum I

February 1996

10. SPONSORING/MONITORINGAGENCY REPORT NUMBER

CR-203675

11. SUPPLEMENTARY NOTES

Technical Monitor: S. Krimchansky, Code 481

12a. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified-Unlimited

Subject Category: 6 I

Report available from the NASA Center for AeroSpace Information,

800 Elkridge Landing Road, Linthicum Heights, MD 21090; (301)621-0390.

13. ABSTRACT (Maximum 200 words)

12b. DISTRIBUTION CODE

This addendum supplements Report 1038 I, dated June 1995, to include a new and more refined finite element model.

14. SUBJECT TERMS

EOS, Microwave System, AMSU-A

17. SECURITY CLASSIFICATIONOF REPORT

Unclassified

NSN 7540-01-280-5500

18.SECURITY CLASSIRCATIONOF THIS PAGE

Unclassified

19. SECURITY CLASSIRCATIONOF ABSTRACT

Unclassified

15. NUMBER OF PAGES

325

16. PRICE CODE

20. LIMITATION OF ABSTRACT

Unlimited

Standard Form 298 (Rev. 2-89)Prescribed bv ANSI Std. 239-18. 298-102

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