May 2013 

NASA/TM2013-217996 

NESC-RP-12-00867 

 

Structural Analysis Peer Review for the Static 

Display of the Orbiter Atlantis at the Kennedy 

Space Center Visitors Center 

Stephen J. Minute/NESC 

Langley Research Center, Hampton, Virginia 
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May 2013 

NASA/TM2013-217996 

NESC-RP-12-00867 

 

Structural Analysis Peer Review for the Static 

Display of the Orbiter Atlantis at the Kennedy 

Space Center Visitors Center 

Stephen J. Minute/NESC 

Langley Research Center, Hampton, Virginia 
Available from: 

NASA Center for AeroSpace Information 

7115 Standard Drive 

Hanover, MD 21076-1320

443-757-5802 

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NASA Engineering and Safety Center 

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Kennedy Space Center Visitors Center Orbiter Atlantis Static 

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Structural Analysis Peer Review 

of the 

Kennedy Space Center Visitors Center Orbiter 

Atlantis Static Display 

March 14, 2013 
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Report Approval and Revision History 

NOTE: This document was approved at the March 14, 2013, NRB. This document was 

submitted to the NESC Director on March 22, 2013, for configuration control. 

Approved: Original Signature on File 3/25/13

NESC Director Date

Version Description of Revision Office of Primary 

Responsibility Effective Date

1.0 Initial Release Mr. Stephen Minute, 

NESC Chief Engineer, 

KSC

3/14/13
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Table of Contents 

Technical Assessment Report 

1.0 Notification and Authorization ........................................................................................ 4

2.0 Signature Page ................................................................................................................... 5

3.0 Team List ........................................................................................................................... 6

4.0 Executive Summary .......................................................................................................... 7

5.0 Assessment Plan ................................................................................................................ 9

6.0 Problem Description, Scope, Proposed Activities .......................................................... 9

7.0 Data Analysis ................................................................................................................... 10

7.1 Compliance of Attach Points for Thermal Expansion ................................................ 10

7.2 Sufficient Control of the Load While On the Lifting Jacks ........................................ 12

7.3 Payload Bay Door Support Beam Support Structure Strength ................................... 18

7.4 Payload Bay Door Opening Operations ...................................................................... 18

7.5 Miscellaneous ............................................................................................................. 18

8.0 Findings and NESC Recommendations ........................................................................ 18

9.0 Alternate Viewpoint ........................................................................................................ 19

10.0 Acronyms List ................................................................................................................. 19

11.0 References ........................................................................................................................ 19

12.0 Appendices ....................................................................................................................... 20

List of Figures 

Figure 7.1-1. Orbiter Attach Point Compliance (Weight and Reaction Loads) ......................... 12

Figure 7.2-1. Free Body Diagram of Loads to the Support Structure ........................................ 13

Figure 7.2-2. Free Body Diagram of Loads to the Jacks ............................................................ 13

Figure 7.2-3. BRPH Drawing of Orbiter in Final Rotated Position with Loads Applied 

to Jacks .................................................................................................................. 14

Figure 7.2-4. Pathfinder Demonstration – Initial Lift................................................................. 15

Figure 7.2-5. Pathfinder Demonstration – Rotation (aft view) ................................................... 16

Figure 7.2-6. Pathfinder Demonstration – Rotation (side view) ................................................ 17
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Technical Assessment Report 

1.0 Notification and Authorization 

Mr. Christopher Miller with the NASA Safety & Mission Assurance (S&MA) at the Kennedy 

Space Center (KSC), in conjunction with the KSC Education and External Relations Directorate, 

requested an independent peer review of the Orbiter Atlantis static display structural analysis for 

display at the KSC Visitors Center. The principal focus of the assessment was to review the 

engineering firm’s structural analysis for lifting and aligning the orbiter and its static display 

configuration. 

A NASA Engineering and Safety Center (NESC) initial evaluation was approved to proceed by 

the NESC Review Board (NRB) on March 22, 2012. Mr. Steve Minute, NESC Chief Engineer 

at KSC, was assigned to lead this assessment. A preliminary stakeholder summary was approved 

by the NRB on September 27, 2012.

The key stakeholders for this assessment are the KSC S&MA, KSC Education and External 

Relations Directorate, Shuttle Transition and Retirement (T&R) Project, and the NESC. 
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2.0 Signature Page 

Submitted by: 

Team Signature Page on File – 4-15-13 

Mr. Stephen A. Minute Date 

Significant Contributors: 

Dr. Ivatury S. Raju Date Mr. Kevin Roscoe Date 

Dr. Curtis E. Larsen Date Mr. David A. Hamilton Date 

Dr. Kenny B. Elliott Date 

Signatories declare the findings, observations, and NESC recommendations compiled in the 

report are factually based from data extracted from program/project documents, contractor 

reports, and open literature, and/or generated from independently conducted tests, analyses, and 

inspections. 
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3.0 Team List 

Name Discipline Organization

Core Team

Steve Minute NESC Lead KSC

Kenny Elliott

NASA Deputy Discipline Expert for 

Structures LaRC

Curt Larsen

NASA Technical Fellow for Loads & 

Dynamics JSC

Patricia Pahlavani MTSO Program Analyst LaRC

Ivatury Raju NASA Technical Fellow for Structures LaRC

Kevin Roscoe Structures Discipline Expert LaRC

Mark Terrone NESC Systems Engineer KSC

Consultant

Dave Hamilton Structures Discipline Expert Consultant

Administrative Support

Erin Moran Technical Writer LaRC/AMA
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4.0 Executive Summary 

Mr. Christopher Miller with the Kennedy Space Center (KSC) NASA Safety & Mission 

Assurance (S&MA) office requested the NASA Engineering and Safety Center’s (NESC) 

technical support on March 15, 2012, to review and make recommendations on the structural 

analysis being performed for the Orbiter Atlantis static display at the KSC Visitor Center. The 

S&MA office requested the NESC to consider three parts to this review: 

1. Final static display – minimal dynamic loads (i.e., indoors, no internal access).

2. Lifting and handling to get orbiter onto final stands – potential dynamic loads on orbiter 

and support stands. 

3. Payload bay door support – Atlantis will be displayed with doors open. 

The primary interfaces for NESC team during this review were with the KSC S&MA office and 

with the KSC Shuttle Transition & Retirement (T&R) Program via their KSC Engineering 

Project engineering representative. However, there were numerous telecons and meetings 

convened with participation from NESC, KSC S&MA, KSC Shuttle T&R, KSC Engineering, 

Delaware North Companies (DNC), BRPH Engineering, and United Space Alliance (USA). 

Numerous drawings, analysis, design, and data packages were provided to the NESC team. 

Because this was a peer review of the engineering analysis, a formal independent NESC 

assessment was not performed due to time constraints. The NESC team reviewed the existing 

work with technical experts asking questions about methodology and assumptions, and 

performing hand and finite element calculations as deemed appropriate. The NESC questions 

and comments were exchanged directly with the cognizant engineers in a real-time and effective 

technical interchange. 

Throughout the review there were comments and concerns that centered around four specific 

areas of the proposed design and process. 

1. Compliance of attach points primarily for thermal expansion. 

2. Sufficient control of the load while on the lifting jacks. 

3. Payload bay door support beam support structure strength. 

4. Payload bay door opening operations. 

DNC, BRPH Engineering, and USA were responsive to the NESC team inquiries and took action 

to improve their analysis and design, where appropriate. Details of these technical exchanges are 

discussed in this report. Based on the data and information provided, the NESC team found the 

DNC, BRPH Engineering, and USA designs and analysis to be appropriate and acceptable. 

One observation was noted during the review. In general, there was a lack of “procedures” that

NASA engineers are accustomed to seeing, such as detailed documentation on how a structure 
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goes from one position to another, and how the load is transitioned from one support system to 

another. The contractor captured the general processes in the drawing system and drawing notes 

to convey the activities. To assess the activities involving structures and the orbiter without 

procedures, assumptions were made on the NESC team’s part that the vendor would safely 

execute the activity as discussed. 

However since the conclusion of the NESC peer review activities, the contractors demonstrated 

the lifting and rotation processes using an orbiter mass simulator. The NESC team contacted 

KSC S&MA office to confirm that no issues were encountered during the tests. 
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5.0 Assessment Plan 

Since this was a peer review, the assessment plan was waived. 

6.0 Problem Description, Scope, Proposed Activities 

Mr. Christopher Miller with the KSC S&MA office requested NESC technical support on March 

15, 2012, to review and make recommendations on the structural analysis being performed for 

the Orbiter Atlantis static display at the KSC Visitor Center. In particular, Mr. Miller requested 

the NESC to consider three parts to the scope of this review and comment effort: 

1. Orbiter final static display design and engineering analysis with the assumption that there 

would be minimal dynamic loads after the orbiter was in place (i.e., indoors – no wind 

loading, no internal access).

2. Lifting and handling processes to move the orbiter onto the final stands – potential 

dynamic loads on orbiter and support stands.

3. Process to open the payload bay doors and provide static support of the doors in the open 

position.1

The primary interfaces for the NESC team during this review were with the KSC S&MA office 

and with the KSC Shuttle T&R Program via their KSC Engineering Project engineering 

representative. 

This peer review was an iterative process. Numerous drawings, analysis, design, and data 

packages were provided to the NESC team in different drops (See Reference Documents 1-10). 

The NESC held internal telecons to assess the engineering analysis and formulate questions and 

comments. In most instances, the NESC questions and comments were transmitted to Mr. John 

Dillon with the KSC S&MA office, who forwarded the questions to the appropriate responsible 

contractor personnel. Some of the responses were handled via e-mail but, in some cases, it was 

more appropriate to have telecons with cognizant Atlantis Display project personnel. The 

primary organizations included, as appropriate, the NESC, KSC S&MA, KSC Shuttle T&R, 

KSC Engineering, DNC, BRPH Engineering, and USA.

Because this was a peer review of the engineering analysis, the NESC team did not perform a 

formal independent modeling and analyses due to time constraints. The NESC reviewed the 

existing work with technical experts asking questions about methodology and assumptions, and 

performing hand and finite element calculations as deemed appropriate. 

A stakeholder outbrief of the NESC team’s activities was approved at the NESC Review Board 

on September 27, 2012 (Appendix A). It was subsequently shared with KSC S&MA, KSC 

 

1

 Activity not performed. See Section 7.4. 
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T&R, and KSC Education & External Relations organizations in preparation for their readiness 

reviews. 

7.0 Data Analysis 

The review focused around several general areas of the proposed design and analysis process 

with comments and concerns on the first four areas.

1. Compliance of attach points for thermal expansion and dynamic loading (i.e., rotation). 

2. Sufficient control of the load while on the lifting jacks. 

3. Payload bay door support beam factors of safety (FoS). 

4. Payload bay door opening operations. 

5. Reaction loads for static display. 

6. FoS. 

DNC, BRPH Engineering, and USA were responsive to the NESC team inquiries and took 

appropriate action to modify and improve their analysis and design, where appropriate. Details 

of these items are discussed in more detail in the following sub-sections. 

7.1 Compliance of Attach Points for Thermal Expansion 

BRPH assessments (References 8 and 9) were provided to NASA as part of an ongoing process 

to show that the orbiter final display configuration was safe to construction personnel and the 

public, and would not damage the Orbiter Atlantis. A review of Reference (8) showed that the 

attachment points on the orbiter and the attachment hardware to be sufficient for the 43 degrees, 

port wing down roll display configuration. This sufficiency is contingent on the support 

structure/attachment hardware providing the adequate compliance, especially for thermal 

expansion. (See Figure 7.1-1 for the aircraft/orbiter (AO)-2 attach point.) The fore/aft direction 

should be compliant at the AO-1 forward support point, and the lateral direction should be 

compliant at the AO-2 aft port support point. Without these compliances, there is a risk to 

exceed the design loads in ICD-2-17001 Table 3.2.3-1.2 of Reference (1). A summary of the 

telecom to discuss this concern is included in Appendix B, Appendix H, items 1 and 2, and 

Appendix I, item 1. Comments, concerns, and questions are provided in Appendix C with 

subsequent responses from BRPH Engineering in Appendix D. 

NESC Concern (Roscoe, August 17): The orbiter installation was to be performed in November 

and without environmental control (i.e., without the building’s roof installed). Given a change in 

temperature event during installation or while on display, differential thermal expansion between 

the orbiter and the support structure drove the need for compliance between the two articles. The 

DNC calculations (Appendix E) predicted forces at the AO joints with perfectly compliant 

(i.e., zero stiffness) support structure. The DNC used Fluorogold®

bearing elements to add 
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compliance. However, these bearings were not “perfectly” compliant. The non-zero compliant 

bearings would result in additional shear forces at the AO joints during thermal events. Also, the 

thermal events would have a zero relative velocity starting point at the Fluorogold® interface. 

The joint would tend to stick until sufficient shear force would overcome static friction. 

BRPH Response (Paquette, August 20): “We have been looking at the concerns about 

differential thermal expansion between the Orbiter and the Orbiter Support frame and had the 

following response. 

a. According to the slide bearing manufacturers, the static coefficient of friction to 

break away is anywhere from nearly the same as the dynamic friction (0.07) to a 

maximum of 0.1. So at AO2 the maximum breaking frictional resistance 

Yo = 93.1(0.1) = 9.31 kips which we used in our calculations. To assure the 

0.07 coefficient of friction in the short term, lubricants are used according to the 

bearing manufacturers, we are specifying them for the jacking and rotation. The 

coefficient of friction is also improved with bearing pressures above a minimum of 

75 psi according to the slide bearing manufacturers - so for the slide bearings under 

the spacers, the bottom plate bearing surface was reduced where required to assure 

that the bearing pressures are above 75 psi for applicable Orbiter orientations. (The 

Orbiter when level was a controlling factor at the aft slide bearings.) 

b. We have also added high capacity slide bearings at the edges of the shear lugs at the 

spacers to reduce friction at AO3 and AO1 in the Xo direction from the Yo loads 

and at AO2 in the Zo direction and we have considered the breakaway friction at 

the edge slide bearings in our calculations as well. 

c. After rotation, the support frame between the Aft and Forward AO supports is 

intended to be removed, so differential thermal expansion of the Orbiter versus the 

horizontal support frame between the forward and aft Orbiter supports will not be 

applicable. The forward support frame is capable of deflecting because it is not 

braced in the Xo direction. 

d. We identified as much as 10.2 kips of uplift at AO3, which isn’t very much for all 

8 bolts (1.5 inch diameter A325) in the spacer to resist. We have removed the 

torque requirements after jacking and rotation from the contact documents. 

e. We have analyzed and provided a table considering the Orbiter loads combined with 

friction developed on the slide bearings prior to movement and differential thermal 

expansion for cases that include in the level or rotated condition during jacking and 

rotation.”

Static Display Compliance Summary: 

The NESC team assessed this item has been satisfactorily addressed, assuming compatibility of 

the lubricant and Fluorogold®, and believing 0.10 is the maximum coefficient of friction per the 

manufacturer. Both assumptions would rate as a low risk. The contractor team has sufficiently 

engineered the joint (e.g., contacted the manufacturer to estimate break-away friction, reduced 
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bearing area to increase pressure load to the minimum recommended, added slide bearings to the 

shear lugs, removed post-installation bolt torque, and calculated predicted max break-away shear 

loads due to thermal expansion). The contractor team could have (or may have) tried to 

determine the structural compliance between AO-2 and AO-3 for the small thermal expansion 

difference. However, the 16,300-lb limit may have been too low for the Support Frame. Either 

way the bearing solution works. Once a slide bearing was introduced under AO-1, the contractor 

team solved the biggest threat to the thermal expansion issue. Refer to in-depth question and 

response discussion in Appendix F. 

Figure 7.1-1. Orbiter Attach Point Compliance (Weight and Reaction Loads) 

7.2 Sufficient Control of the Load While On the Lifting Jacks 

The NESC team had an initial concern that the jacks will experience a moment as the orbiter is 

being rotated to final position i.e., 43 degrees, port wing down) (See Figures 7.2-1, 7.2-2, and 

7.2-3, and Appendix G and Appendix H, items 3 and 4). 
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Figure 7.2-1. Free Body Diagram of Loads to the Support Structure 

Figure 7.2-2. Free Body Diagram of Loads to the Jacks 
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Figure 7.2-3. BRPH Drawing of Orbiter in Final Rotated Position with Loads Applied to Jacks 

The following response was provided to the initial NESC team’s comments and concerns via an 

email from Mr. Ken Paquette, BRPH to Mr. John Dillon, KSC-Safety & Mission Assurance 

Support Services (SMASS), dated July 10, 2012: 

Response to Atlantis-Pivot.xlsx Load Diagrams in Appendix G 

“Beyel Brothers has the bottom of the jacks stabilized by (propel) hydraulic cylinders 

that are attached to the jack alignment runway tracks. (See attachments – Propel Jack 

Cylinder.pdf and Lift Systems Jack Runway.pdf; Appendix J) The hydraulic cylinder allows 

controlled horizontal movement. Leveling systems are being used to keep the jack straight. The 

top of the jacks are attached to a hinged connection on the orbiter support beam. There are 

diagonal braces that extend from the aft jack locations on the orbiter support beam to spreader 

beams between the aft and forward supports for the orbiter. The rotation procedure will be 

performed slowly to allow for adjustment to keep the jacks vertical.” 

BRPH Engineering and DNC provided jack stability analysis (Reference 10). However, during 

the telecon on July 27, 2012, the NESC team and DNC agreed that there was insufficient jack 

data to perform a thorough analysis. DNC agreed to develop a test fixture with an orbiter mass 
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simulator to demonstrate capability and provide a pathfinder test for future processes. DNC 

modified their design to include load cells at the top of the jack. With the load cells, DNC were 

able to monitor jack side loads and improve the load control (Appendix I, item 2). 

Subsequent to the peer review and stakeholder outbrief, DNC performed a pathfinder 

demonstration with an orbiter mass simulator. (Figures 7.2-4, 7.2-5, and 7.2-6) No issues were 

identified as a result of the test. The pathfinder test satisfied the concerns raised in this section. 

BRPH Engineering incorporated bracing, sliding tracks for jacks, dunnage, and moved in 2-inch 

increments to control the load. (Figures 7.2-4, 7.2-5, and 7.2-6) 

Figure 7.2-4. Pathfinder Demonstration – Initial Lift 
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Figure 7.2-5. Pathfinder Demonstration – Rotation (aft view) 
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Figure 7.2-6. Pathfinder Demonstration – Rotation (side view) 

Beyel Brothers completed the lift and rotation demonstration test at their Rigging and Heavy 

Equipment Yard on October 11, 2012. The test used a mass simulator and equivalent support 

structure to demonstrate the planned process for lifting and rotating the orbiter at the KSC 

Visitor Center display site. The contractor demonstrated a well-choreographed process using a 

combination of lifting jacks and support cribbing/dunnage to lift and rotate the orbiter to its final 

display configuration (i.e., 43 degrees, port wing down). 

Dunnage was used to support the port side jacks, the frame at the 43-degree position, and the 

load in the event of a jack casualty (loss of hydraulics). The dunnage load capacity was based on 

an aligned stacking configuration (concentric pipes axis) per page 92 of Volume I, Reference 7. 

The aft port location had staggered dunnage where the pipes were not aligned and a load capacity 

rating was not defined. The NESC team performed an assessment of dunnage for this 

configuration (Appendix K) and found it to be sufficient for this application. No issues were 

identified from the NESC team.
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7.3 Payload Bay Door Support Beam Support Structure Strength 

The DNC/USA bolt calculation showed a FoS of 3 on yield and 5 on ultimate (see Appendices L, 

M, and N). However, the DNC/USA calculations were in error because they did not account for 

the prying/lever action of the two-piece support arm on the bolt. It was assumed all the cable 

load would go directly to the bolt. The NESC bolt force load estimation, assuming only one bolt 

was active out of the six, was 1,591 lbs, versus the DNC/USA value of 679 lbs (1,357/2) (see 

Appendices O, P, and Q). DNC/USA subsequently revised their analysis and agreed to improve 

the design by increasing the bolt strength to achieve a FoS of 5 (MP-35N 240KSI tensile strength 

versus 90-100 KSI for the original bolt).

No further concerns were generated from the NESC team.

7.4 Payload Bay Door Opening Operations 

Initially, a review of the payload bay door opening operations was included in the initial NESC 

request. The engineering and operational expertise associated with payload bay door operations 

for the Space Shuttle Program resides with KSC Engineering, USA, KSC S&MA, and the 

Shuttle T&R personnel at KSC. It was agreed with all parties, including KSC Education and 

External Relations Directorate, that the NESC was not the appropriate organization to peer 

review those operations. 

7.5 Miscellaneous 

There were other items the NESC team reviewed. They were not significant items, but are 

included in this section for completeness. The NESC considers these items accepted and closed. 

1. The DNC orbiter support frame with respect to the orbiter and the test fixture, including 

center of gravity measurements and checks of critical dimensions of the orbiter-to-shuttle 

carrier aircraft interfaces as found in the interface control document (ICD). 

2. The shuttle documentation for the external tank (ET)-to-orbiter limit loads allowed 

during ascent flight. Those allowable loads were more severe than the ferry flight ICD 

limits used in designing the DNC static display structure. The demonstrated ascent loads 

reflect the true orbiter interface load capability and give additional comfort in accepting 

the loads to be imposed by the static display structure (Appendix R). 

8.0 Findings and NESC Recommendations 

Because of the iterative nature of this peer review there were no formal findings or NESC 

recommendations. All comments and concerns were addressed in real-time discussions and 

e-mail and captured as best as practical in this report. Based on the data and information 

provided, the NESC finds the DNC, BRPH Engineering, and USA design and analysis results to 

be appropriate and acceptable. 
NASA Engineering and Safety Center 

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One observation was noted during this review and documented in the stakeholder outbrief 

(Appendix A). In general, there was a lack of “operational procedures” that NASA as an Agency 

are accustomed to, such as detailed documentation on how a structure goes from one position to 

another, and how the load is transitioned from one support system to another. The contractor 

captured the general processes in the drawing system and drawing notes to convey the 

activities. To assess the activities involving structures and the orbiter without procedures, 

assumptions were made on the NESC team’s part that the vendor would safely execute the 

activity as discussed. Subsequent to the peer review and stakeholder outbrief, DNC performed a 

pathfinder demonstration with an orbiter mass simulator (Figures 7.2-4, 7.2-5, and 7.2-6). No 

issues were identified to the NESC as a result of the test. The pathfinder satisfies the concerns 

raised in this observation.

9.0 Alternate Viewpoint 

There were no alternate viewpoints identified during the course of this assessment by the NESC 

team or the NESC Review Board quorum. 

10.0 Acronyms List 

AO Aircraft/Orbiter 

DNC Delaware North Companies 

ET External Tank 

FoS Factor of Safety 

ICD interface control document 

KSC Kennedy Space Center 

MTSO Management Technical Support Office 

NASA National Aeronautics and Space Administration 

NESC NASA Engineering and Safety Center 

S&MA Safety & Mission Assurance 

SMASS Safety & Mission Assurance Support Services 

T&R Transition & Retirement 

USA United Space Alliance 

11.0 References 

1. Atlantis Loads Assessment, KSC Visitor Complex Analysis Report, Final Submittal, BRPH 

No. 5636.45, dated July 5, 2012 (pdf) 

2. KSC Visitor Complex Atlantis Support Dwg., 60% Submittal, BRPH No. 5636.44, dated 

June 18. 2012 (pdf) 

3. KSC Visitor Complex Atlantis Support Dwg., 90% Submittal, BRPH No. 79K39277, dated 

August 22, 2012 (pdf) 
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4. Atlantis Support Orbiter Opening Doors, Pre-100% Submittal, BRPH 79K39277, dated 

September 12, 2012 (pdf) 

5. KSC Visitor Complex Atlantis Support Dwg., 100% Submittal, BRPH No. 79K39277, dated 

September 19, 2012 (pdf) 

6. Test Fixture Design, 100% Submittal, BRPH Drawing 6701.01, dated August 9, 2012 (pdf) 

7. 100% Structural Calculations Volumes I & II, BRPH No. 5636.44, dated January 19, 2012 

(pdf) 

8. Atlantis Loads Assessment, KSC Visitor Complex Analysis Report, 90% Submittal, BRPH 

No. 5636.45, dated May 3, 2012 (pdf) 

9. Atlantis Support Concept, KSC Visitor Complex, 100% Submittal, BRPH No. 5636.44, 

dated February 17, 2012 (pdf) 

10. Orbiter Rotation Frame 7-9-2012.pdf (STAAD Analysis FilePropel Jack Cylinder.pdf 

(Jacks to be used for lift and Orbiter Rotation Frame 7-9-2012.pdf (STAAD Analysis File) 

12.0 Appendices 

A. NESC Stakeholder Outbrief 

B. Atlantis_Review-Executive_Summary-060112[1].docx (Notes from Telecon held 6/1/2012) 

C. AtlantisLoadsAssess_Comments.xlsx (K. Roscoe Comments from NESC Review of 

Reference Documents: Attachments D of Ref. 1, Ref. 8, and Ref. 9) 

D. AtlantisLoadsAssess_Comments RBPH Response.pdf (Response to NESC comments in 

Appendix C - AtlantisLoadsAssess_Comments.xlsx) 

E. Orbiter Loads 155K Xo = 159 On SCA Connections.pdf 

F. Email from K. Roscoe to S. Minute on 9/3/2012: 5636.44 RE: Atlantis Support Structure - 

Additional Design Calculations 

G. Atlantis-Pivot.xlsx (K. Roscoe’s Free Body Diagrams)

H. AtlantisItemsFor072712meeting.docx (Discussion items for telecon held 7/27/2012) 

I. AtlantisReview072712-Summary.docx (Summary of telecon on 7/27/2012) 

J. Propel Jack Cylinder.pdf (jacks to be used for lift and rotation) 

K. Atlantis DunnageRevA.pptx (Assessment of dunnage to be used in lift and rotation 

procedure) 

L. PLBD Support-C.pdf 

M. G-Ops Support.pdf 

N. Mathcad - OV-104_Door_Support_Analysis_3.pdf 

O. PLBD Comments.pptx (K. Roscoe’s assessment of PLBD analysis)

P. PLBD Attach Beam calcs.xlsx (K. Roscoe’s analysis)

Q. AttachBeamBolts.xlsx (K. Roscoe’s analysis)

R. Email from C. Larsen to Minute, et. al. on September 5, 2012: Re: Atlantis Support Structure 

– Orbiter allowable loads. 
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Appendix A. NESC Stakeholder Outbrief
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Appendix B. Atlantis_Review-Executive_Summary-060112[1].docx (Notes 

from Telecon held 6/1/2012) 

Subject: Display of Atlantis in the KSC Visitor Complex 

References (1) and (2) were provided to NASA as part of an ongoing process to show that all 

procedural steps from transporting the orbiter to the final display configuration are safe and will 

not damage the Orbiter Atlantis. A review of Reference (1) shows that the attachment points on 

the orbiter and the attachment hardware to be sufficient for the 43° roll display configuration. 

This sufficiency is contingent on the support structure / attachment hardware providing the 

proper compliance. At the forward support point, AO-1 the fore/aft direction should be 

compliant. At the aft port support point, AO-2 the lateral direction should be compliant. 

Without these compliances it could be relatively easy to exceed the design loads in Table 3.2.3-

1.2 of Reference (3). 

To complete the review and assessment of the process, the following documents are needed: 

1. The structural steel support frame (display structure) assessment, including the 

appropriate support structure / attachment hardware compliances. 

2. Payload Bay Door procedure and hardware assessment (crane operations 

(opening), and supporting) 

3. Orbiter lifting / jacking procedure onto the display structure and hardware 

assessment

4. Orbiter rotation procedure and hardware assessment 

Confirmation should be provided stating that all hardware and procedures used for handling the 

orbiter are the same as those used for the flight articles. If not, an assessment of the variances 

should be provided for review. 

Note: Reference (2) contains operations that conflict with those in Reference (1). These conflicts 

need to be addressed and resolved. 

References: 

1. Atlantis Loads Assessment, KSC Visitor Complex Analysis Report, 90% Submittal, 

BRPH No. 5636.45, dated May 3, 2012 

2. Atlantis Support Concept, KSC Visitor Complex, 100% Submittal, BRPH No. 5636.44, 

dated February 17, 2012 

3. ICD-2-17001, rev G-1, Orbiter Vehicle / Carrier Aircraft, Dated March 5, 2007 
NASA Engineering and Safety Center 

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Appendix C. AtlantisLoadsAssess_Comments.xlsx (K. Roscoe Comments 

from NESC Review of Reference Documents: Attachments D of Ref. 1, Ref. 8, 

and Ref. 9): 

Atlantis Review

brph Atlantis Loads Assessment 

Section Paragraph Comments or Notes

1 2 Do not need to make an exception. Comparison to the worst case

tensile condition is not applicable. See ICD-2-17001, Section 3.2.3

1.2 2 Bullet 6: Cannot have a rigid support frame. All loading in contingent on

AO-2 not transmitting lateral loads. 

1.3 4 Support frame analysis is TBD

2.2 Figure Sideslip Maneuver Forces: shows vertical tensile force of 128 kips. This

case was used to size the bolt preload. See ICD-2-17001, Section 3.2.3

2.4 Last Statement that they will design the support stand with AO-2 lateral compliance.

3 1 Don't need exception

3 3 Disagree with their Z load at AO-3. See Figure in 2.1 and "Loads" sheet 

4.1 Orbiter support structure:

AO-1 should be compliant in fore/aft direction

A0-2 should be compliant in lateral direction

4.2 all Don't need FEA when all the dofs are released.

4.3 all Don't need FEA when all the dofs are released.

4.4 ICD-2-17001 rev G-1

Figure 1.2-1.1 has the attachment coordinates

3.2.3 Shows sideslip maneuver only used to derive preload

Table 3.2.3-1.2 shows worst case loads on attachment hardware

Table 3.2.3-1.3 shows sideslip maneuver loads

4.5 Figure 1 Figure is different from brph Atlantis Support Concept 2/17/12 

Step 2 Does not describe how they are going to install Atlantis on support frame

Step 3 Does not describe how they are going to rotate frame

Assumptions Bullet 3: Only applies to attach points (not doors) and needs to have a FS

Bullet 6: Frame must be appropriately compliant, not "rigid"

Limitations Assumption that there will be no differences between normal lifting and 

handling of the Orbiter and landing the Orbiter on the support stand.

4.6 email Analysis weight appears to be conservative. 

End
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Appendix D. AtlantisLoadsAssess_Comments RBPH Response.pdf (Response 

to NESC comments in Appendix C - AtlantisLoadsAssess_Comments.xlsx)
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Appendix E. Orbiter Loads 155K Xo = 159 On SCA Connections.pdf
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Appendix F. Email from K. Roscoe to S. Minute on 9/3/2012: 5636.44 RE: 

Atlantis Support Structure - Additional Design Calculations 

From: ROSCOE, KEVIN (LARC-D206) 

Sent: Monday, September 03, 2012 4:19 PM 

To: Minute, Stephen A. (KSC-C105) 

Cc: Raju, Ivatury S. (LARC-C104); Elliott, Kenny B. (LARC-D210); Larsen, Curtis E. (JSC-C104); 'David 

Hamilton' (dave@lifethoughts.com) 

Subject: RE: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Importance: High 

Steve, 

I think they closed this item, assuming compatibility of the lubricant and Flourogold, and 

believing 0.10 is the maximum coefficient of friction per the manufacture (we have margin 

if it is slightly higher). Both assumptions I would rate as a low risk. 

Prior to this response they assumed it would work and didn’t think about it (my 

opinion). Now they have engineered the joint (reduced bearing area to increase pressure 

load to the minimum recommended, removed post-installation bolt torque, added slide 

bearings to the shear lugs, contacted the manufacturer to estimate break-away friction, and 

calculated predicted max break-away shear loads due to thermal expansion). 

They could have (or may have) tried to determine the structural compliance between AO-2 

and -3 for the small thermal expansion difference. However, the 16,300 lb limit may have 

been too low for the massive Support Frame. Either way the bearing solution works.

Once they put a slide bearing under AO-1, they solved the biggest threat to the thermal 

expansion issue. The rest of this work is more or less good engineering (details). 

Disclaimer: I haven’t looked at the details in the analysis or the drawings, but BRPH gave 

the right response. I plan on looking at the details after I go thru the hot items in my 

inbox. 

Sincerely, 

Kevin Roscoe 

Structural & Thermal Systems Branch 

Engineering Directorate 

NASA Langley Research Center, MS 431 

1 N. Dryden Street / Hampton, VA 23681 

Bldg. 1209, Rm. 150B, Off: 757-864-4173 

From: Minute, Stephen A. (KSC-C105) 

Sent: Wednesday, August 29, 2012 12:45 PM 

To: Raju, Ivatury S. (LARC-C104); ROSCOE, KEVIN (LARC-D206); Elliott, Kenny B. (LARC-D210); Larsen, 

Curtis E. (JSC-C104); 'David Hamilton' (dave@lifethoughts.com) 
NASA Engineering and Safety Center 

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Subject: FW: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Importance: High 

I haven’t read any of this yet – wanted to get it directly into your hands. 

From: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration 

Company] 

Sent: Wednesday, August 29, 2012 12:24 PM 

To: Minute, Stephen A. (KSC-C105) 

Cc: Braden, Barry M. (KSC-SA000) 

Subject: FW: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Importance: High 

Steve, 

Here is the response from BRPH. 

John 

From: Ken E. Paquette [mailto:kpaquette@brph.com] 

Sent: Wednesday, August 29, 2012 12:01 PM 

To: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration Company] 

Cc: Wohlert, William D. (KSC)[DELAWARE NORTH COMPANIES PARKS & RES]; Andrew H. Miller 

Subject: RE: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

John 

See my responses in Red below and forward with my attachments to Mr. Roscoe. 

Thanks Ken 

KEN E. PAQUETTE | Senior Structural Engineer

BRPH | 5700 North Harbor City Boulevard, Suite 400 | Melbourne, Florida 32940 

O: 321-751-3035 | F: 321-259-4703

KEP@brph.com | www.brph.com

ARCHITECTS | ENGINEERS | CONSTRUCTORS

From: ROSCOE, KEVIN (LARC-D206) 

Sent: Monday, August 20, 2012 1:00 PM 

To: Minute, Stephen A. (KSC-C105); Raju, Ivatury S. (LARC-C104); Elliott, Kenny B. (LARC-D210); 'David 

Hamilton' (dave@lifethoughts.com); Larsen, Curtis E. (JSC-C104) 

Cc: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration Company] 

Subject: RE: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Steve, 
NASA Engineering and Safety Center 

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Great. Based on my understanding that takes care of the connection from AO-1 to AO-2 

(and AO-3) in the X direction for the post installation condition. An estimate of shear force 

given the assumptions and calculations can be added to the predicted load summary for the 

AO joints, provided this is the worst case. 

Is the connection situation identical for the AO-2 to AO-3 in the lateral direction? 

There isn’t a separate frame in between AO-2 and AO-3 so we considered the full breaking 

friction force in the Yo directions at the slide bearing at AO-2 for thermal stresses. 

The Change in length of the Orbiter from AO2 to A03 due to a 30 degree temperature 

swing is approximately: 

13x10^-6 (30 degrees)(96.25+96.25) = 0.075 inches 

The change in length of the steel Orbiter support beam for the same length is: 

6x10^-6(30)(96.25+96.25) = 0.03465 inches 

The change in length difference is 0.0404 inches – a little more than 1/32 of an inch. 

According to the slide bearing manufacturers, the static coefficient of friction to break 

away is anywhere from nearly the same as the dynamic friction (0.07) to a maximum of 

0.1. So at AO2 the maximum breaking frictional resistance Yo = 93.1(0.1) = 9.31 kips 

which we used in our calculations. To assure the 0.07 coefficient of friction in the short 

term, lubricants are used according to the bearing manufacturers, we are specifying them 

for the jacking and rotation. The coefficient of friction is also improved with bearing 

pressures above a minimum of 75 psi according to the slide bearing manufacturers - so 

for the slide bearings under the spacers, the bottom plate bearing surface was reduced 

where required to assure that the bearing pressures are above 75 psi for applicable 

Orbiter orientations. ( The Orbiter when level was a controlling factor at the aft slide 

bearings.) 

We have also added high capacity slide bearings at the edges of the shear lugs at the 

spacers to reduce friction at AO3 and AO1 in the Xo direction from the Yo loads and at 

AO2 in the Zo direction, and we have considered the breakaway friction at the edge slide 

bearings in our calculations as well. 

Also, does environmental control from the time the orbiter is secured to the support frame 

till the final display configuration exist? 

Environmental control is not expected, however this procedure is intended to be done in 

November, when milder temperatures occur. 

After the building is in use and conditioned, emergency systems to keep the artifacts at a 

constant temperature are part of the facility design. 

If not, then there is a risk during this time (jacking and rotation) of an environmental load 

condition. The event could occur in the level or rotated condition. 

We have analyzed and provided a table considering the Orbiter loads combined with 

friction developed on the slide bearings prior to movement and differential thermal 

expansion for cases that include in the level or rotated condition during jacking and 

rotation. 
NASA Engineering and Safety Center 

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Preload: 

We haven’t had a lot of discussion concerning bolt torque after installation at the AO 

joints. The Fluorogold® slide bearings provide compliance once they start sliding. Until 

then, the bearings provide a rigid structural connection. The bearing’s compliance begins 

once the static friction times the normal force acting on the bearing is exceeded. Bolt 

preload increases the normal load, thus reduces the compliance (higher break-away 

force). 

The structural compliance as described in the email below should cover the reduction in 

bearing compliance due bolt preloading at the AO-1 joint. I don’t think that is the case at 

the AO-2 and AO-3 joints. Is there a need to torque the bolts at both AO-2 and AO-3 

joints? 

We identified as much as 10.2 kips of uplift at AO3, which isn’t very much for all 8 bolts ( 

1.5 inch diameter A325) in the spacer to resist. We have removed the torque requirements 

after jacking and rotation from the contact documents. 

Note: A rigid bearing joint would not meet the contingency per “Atlantis Review 6-1-12 - 

Summary.docx” (excerpt):

“A review of Reference (1) shows the attachment points on the Orbiter and the attachment 

hardware to be sufficient for the 43° roll display configuration. This sufficiency is 

contingent on the support structure / attachment hardware providing the proper 

compliance.”

It should be demostrated (calculated) that proper compliance exists. 

We have included additional tabulated comparisons with the Interface loads from ICD-2-

17001. 

Sincerely, 

Kevin Roscoe 

Structural & Thermal Systems Branch 

Engineering Directorate 

NASA Langley Research Center, MS 431 

1 N. Dryden Street / Hampton, VA 23681 

Bldg. 1209, Rm. 150B, Off: 757-864-4173 

From: Minute, Stephen A. (KSC-C105) 

Sent: Monday, August 20, 2012 11:51 AM 

To: Raju, Ivatury S. (LARC-C104); ROSCOE, KEVIN (LARC-D206); Elliott, Kenny B. (LARC-D210); 'David 

Hamilton' (dave@lifethoughts.com); Larsen, Curtis E. (JSC-C104) 

Cc: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration Company] 

Subject: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Importance: High 
NASA Engineering and Safety Center 

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Folks, 

Please see included email and attachment. 

Thanks John. 

SM

From: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration Company] 

Sent: Monday, August 20, 2012 11:02 AM 

To: Minute, Stephen A. (KSC-C105) 

Subject: FW: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

Importance: High 

Please forward. 

Thanks! 

John 

From: Ken E. Paquette [mailto:kpaquette@brph.com] 

Sent: Monday, August 20, 2012 10:51 AM 

To: Dillon III, John Thurman Rascoe (KSC-SMASS-E)[Millennium Engineering and Integration Company] 

Cc: Wohlert, William D. (KSC)[DELAWARE NORTH COMPANIES PARKS & RES]; Andrew H. Miller 

Subject: RE: 5636.44 RE: Atlantis Support Structure - Additional Design Calculations 

John – Please Forward to Mr. Roscoe

1. We have been looking at the concerns about differential thermal expansion 

between the Orbiter and the Orbiter Support frame and have the following 

response. 

a. After rotation, the support frame between the Aft and Forward AO 

supports is intended to be removed, so differential thermal expansion of 

the Orbiter versus the horizontal support frame between the forward 

and aft Orbiter supports will not be applicable. The forward support 

frame is capable of deflecting because it is not braced in the Xo direction. 

b. We reviewed the lateral stiffness of the Orbiter forward support 

frame on its own, and determined that it would deflect about 1 inch 

for a 1000 lb force conservatively applied at the column below the 

Teepee support stand. We also determined that the change of length of 

the Orbiter due to a temperature change from 100 degrees to 70 

degrees would be about 0.36 inches based on the coefficient of thermal 

expansion for Aluminum. 

 13.0 x 10^-6 (100-70)(1317-388.045) = 0.36 inches 
NASA Engineering and Safety Center 

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Title:

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So if the slide bearing is not effective for thermal movement, the 

forward Orbiter support frame will deflect in the Xo direction 

significantly under low lateral forces.

Thanks Ken 

KEN E. PAQUETTE | Senior Structural Engineer

BRPH | 5700 North Harbor City Boulevard, Suite 400 | Melbourne, Florida 32940 

O: 321-751-3035 | F: 321-259-4703 

| www.brph.com
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Appendix G. Atlantis-Pivot.xlsx (K. Roscoe’s Free Body Diagrams)
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Title:

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Title:

Structural Analysis Peer Review for the Static Display of the 

Orbiter Atlantis at the Kennedy Space Center Visitors Center

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Orbiter Atlantis at the Kennedy Space Center Visitors Center

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Title:

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Appendix H. AtlantisItemsFor072712meeting.docx (Discussion items for 

telecon held 7/27/2012) 

Discussion Items for Atlantis Display Meeting on July 27, 2012 

1. Did not find calculations showing the design (including Flourogold) limits the loads at 

the AO-1 and AO-2 location to the allowable values. 

a. Found Flourogold coefficient of friction data in vendor brochure. Could not find 

data for zero velocity (stick/slip). 

b. Found Flourogold recommended pressure data, but no calculations showing it was 

not exceeded when torque is applied to bolts the 8 11⁄2-inch bolts. Did not find the 

torque call-out. 

2. Found space between Aft Support Spacer and Shear Lugs. Did not find shims to close 

the gap (sheet 18 in Atlantis Support.pdf). 

3. Orbiter Rotation Frame Analysis: 

a. Sliding jack has 4 wheels contacting the XZ plane. The wheels will react 

translation loads in the Y direction (vertical) and moments about the X and Z 

axes. The Analysis released the moments at this joint, thus could not assess 

bending in the jack (line 91 of STAAD input deck and joint 3510 output on page 

9 of analysis package. Could not find another method where the moments were 

assessed. 

b. Could not find documentation for jack vertical stiffness 

c. Could not find documentation for Propel cylinder stiffness. 

i. Propel cylinder line of action is in the YZ plane at a shallow horizontal 

angle. Could not find where the analysis accounted for this vector. 

d. Did not find lateral load strength or limitation for gantry system, nor lateral 

stiffness 

e. Beam model joins member of different size. Without joint releases, the joint is 

rigid where all degrees of freedom are transmitted. Did not find in Atlantis 

Support.pdf joint details that were consistent with the analysis method. 

i. For example, the long Fore/aft beams (X direction) were connected 

together in the Z direction with smaller beams. Could not find the joint 

detail. 

4. Could not find the “Rigging plans from the Contractor will provide a detailed full 

procedure and equipment used” document.

a. Cannot interpret the lifting note 1 on page 7 of Atlantis Support.pdf, zone F7 

without “Rigging Plan”. Alternate the lift fore/aft or port/starboard? 
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b. Could not find a plan to control the load 

i. Could not find position sensors or load indicators 

c. Could not find lateral load limits for the gantry system 

d. Cannot fully assess rotation operations without more detail 
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Appendix I. AtlantisReview072712-Summary.docx (Summary of telecon on 

7/27/2012) 

Subject: Display of Atlantis in the KSC Visitor Complex 

Subject: 7/27/2012 Meeting minutes 

Doug Wohlert opened the meeting by describing three tasks that DNC is performing: 

1) Atlantis load assessment – 90% design review package released in May and transmitted 

to NASA on July 12. 

2) Transportation of Orbiter Planning – the 90% transportation plan is released and they 

plan to move the orbiter in November. 

3) Atlantis Structural Support – the concept was released on Feb 17, 30% design package 

was released in May, 60% released on June 21. They plan to release the 90% package 

on August 22 and hold a 2-week review period. The final package is planned to be 

released on Sept. 19. 

This was followed by a review of the attachment to Reference (1) with the bulk of the 

conversation closing out the drawing comments. A portion of the content of the Reference (1) 

material was deferred and addressed in the discussion based on the comment in the attachment to 

Reference (2). The conversation about Reference (2) resulted in the following action items for 

DNC: 

1) Redesign AO-1 joint to allow for axial displacement. Although the fitting to the orbiter 

allows rotation, it transmits forces. Thermal expansion could overload the joint with the 

current design. 

1. A calculation package showing the predicted loads at the orbiter supports (AO-1, 

AO-2 and AO-3) was requested. Although the design has elements to reduce the 

joint shear loads, the predicted values were not presented. The predicted loads 

would be compared to the orbiter limits to show margin in the design during 

operations. 

2) Develop a test fixture, test plan, conduct qualification tests to demonstrate control of 

the load and provide the obiter operation plan. The test fixture would simulate the 

orbiter weight and center of gravity. The test plan would envelop the orbiter plan 

operation environment. The jacks would also be operated asynchronously to 

demonstrate control of the load. 

1. Due to lack of technical data such as jack lateral stiffness, DNC is not able to 

analytically show the design is sufficient. 
NASA Engineering and Safety Center 

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The beam finite element model presented was too simplistic when it came to joint details and 

jack simulation. DNC stated they had separate detail analysis results for some critical joints and 

that they could provide a package for review. 

References: 

4. Email from Doug Wohlert [DWohlert@dncinc.com] on Mon 7/23/2012 at 11:09 AM 

with attachment “(2012-07-20) 60% Review Comments and Support 

Documentation.pdf”.

5. Email from Raju, Ivatury S. (LARC-C104) on Fri 7/27/2012 with attachment 

“AtlantisItemsFor072712meeting.docx”
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Appendix J. Propel Jack Cylinder.pdf (Jacks to be used for lift and rotation)

Propel Jack Cylinder.pdf is available at:

 http://lift-systems.com/
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Appendix K. Atlantis DunnageRevA.pptx (Assessment of dunnage to be used 

in lift and rotation procedure) 
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Appendix L. PLBD Support-C.pdf 
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Appendix M. G-Ops Support.pdf 
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Appendix N. Mathcad - OV-104_Door_Support_Analysis_3.pdf 
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Appendix O. PLBD Comments.pptx (K. Roscoe’s assessment of PLBD 

analysis) 
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Appendix P. PLBD Attach Beam calcs.xlsx (K. Roscoe’s analysis)

PLBD Calcs

Load per side w/ 

GSE 3,600

GSE 2 Tube Wt 1,400

Total Door Wt at cable 2,200

Ratio 1 to 2 Tube 

GSE 33.3%

GSE 1 Tube Wt 467

Wt on Cable 2,667

Num of Support Cables 4

Wt per support 

cable 667

Distribution factor 1.00

Wt per Attach Beam 667

Overall length 8

pivot end 0.58

pin end 0.5

Cable lever arm 6.92 = 8 - 0.58 - 0.5

number of spacings 5

spacing 0.57

Bolt lever arm 2.9

= 5 * 

0.57

Force ratio 2.39

Bolt force 1,591

1/4" 3/8"

Bolt tensile area 0.0364 0.0775

Bolt tensile stress 43,735 20,529

Bolt ultimate stress 100,000 100,000

Bolt FS, ult 2.29 4.87

Attach Beam 

Bending

Thru Bolt 1/4" 3/8"
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Height 1.5 1.5

Width 1 1

Hole thru 0.257 0.382

Net width 0.743 0.618

Section modulus 0.279 0.232 = bh2/6

Lever 4.02 4.02 = 6.92 - 2.9

Moment 2,680 2,680

Bending stress 9,619 11,564

AB ultimate stress 108,000 108,001

AB FS, ult 11.23 9.34

Lots of bending capacity, not a lot of bolt capacity:

Consider using larger bolt

Shear Tube to shear tube distance

Radius at bottom of hole 161.69

Shear tube radius 0.81

Radius at shear tube ctr 162.5

Arc length to Block edge 22.89

Distance to block edge 22.87

Block edge to tube 

ctr 1.875

Tube to tube 

distance 24.75

Edge to SB edge 10.36

Approx Tubt to SB edge 12.235

Tube to 1/4" bolt 11.665

Tube to cable 15.69

Cable to 1st 3/8" 

bolt 15.00

At: 

3/8" 

hole Shear Tube 

Approx Depth 2.144 1.572 Scaled

Width 1 1

Hole thru 0.386 0

Net width 0.614 1

Section modulus 0.470 0.412 = bh2/6
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Moment approx 9,997 10,457

Bending stress 21,258 25,388

AB Yield stress 60,000 60,000

AB FS, Yld 2.82 2.36 Ultimate??

Reaction Loads

Cable lever arm 40.43

Shear Tube lever 

arm 24.75

Force ratio 1.63

ST force middle 1,089

ST force end 423

3/8" bolt Force 545 ~ 1/2 ST force middle

Bolt tensile area 0.0775

Bolt tensile stress 14,056

Bolt ultimate stress 100,000

Bolt FS, ult 7.11 > 5
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Appendix Q. AttachBeamBolts.xlsx (K. Roscoe’s analysis)

bolt load Strength area factor

1 -810 180,000 0.0364 n/a

2 -440 180,000 0.0364 n/a

3 -70 180,000 0.0364 n/a

4 290 180,000 0.0364 22.5931

5 660 180,000 0.0364 9.927273

6 1020 180,000 0.0364 6.423529

Load lb 667 FEA

Load Arm in 6.92

Bolt 

force 1,003

Stress 27,555

Current 

Bolts Strength 180,000

At in2 0.0364 FS 6.5

Ftu psi 100,000

Fty psi 60,000

Bolt 1 2 3

Strength psi 100,000 60,000 60,000

Capacity lbs 3640 2184 2184

L in 2.9 2.33 1.76

Moment in-lb 10,556 5,089 3,844

Total 

moment in-lb 19,489

Applied 

mom in-lb 4,616

FS - 4.2

High Strength Bolts

At in2 0.0364

Ftu psi 180,000

Fty psi 120,000

Bolt 1 2 3

Strength psi 180,000 120,000 120,000

Capacity lbs 6552 4368 4368

L in 2.9 2.33 1.76

Moment in-lb 19,001 10,177 7,688

Total 

moment in-lb 36,866

Applied 

mom in-lb 4,616

FS - 8.0
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Appendix R. Email from C. Larsen to Minute, et. al. on September 5, 2012: 

Re: Atlantis Support Structure – Orbiter allowable loads 

From: Larsen, Curtis E. (JSC-C104) 

Sent: Wednesday, September 05, 2012 12:43 PM 

To: Minute, Stephen A. (KSC-C105); Raju, Ivatury S. (LARC-C104); ROSCOE, KEVIN (LARC-D206); Elliott, 

Kenny B. (LARC-D210); 'David Hamilton' (dave@lifethoughts.com) 

Subject: RE: Atlantis Support Structure - Orbiter allowable loads 

Importance: High 

Folks – 

I have gone back to Shuttle documentation and tabulated below the ET to Orbiter limit loads allowed 

during ascent flight. These allowable loads are higher than those in the ferry flight ICD for the obvious 

reason of the more severe flight environment. Thus they reflect the true Orbiter interface load 

capability and should give us additional comfort in accepting the loads to be imposed by the static 

display support structure. My reference for these loads is: Lockheed Martin report no. 826-2470, Jan. 

2001, “SLWT Structural Load Indicators and Capabilities”.

All loads are in kips (1000 lbs), in Orbiter coordinate system. 

Interface AO-1: Fx = 10.8/-8.5 Fy = 64.5/-70.9 Fz = 96.4/-127.8 

Interface AO-2: Fx = 154.3/-705.3 Fy = 82.0/-107.8 Fz = 247.8/-326.0 

Interface AO-3: Fx = 152.9/-699.8 Fy = 103.7/-70.7 Fz =243.1/-395.7 

I hope this helps in our discussions. 

Thanks, 

Curt 

Curtis E. Larsen, Ph.D., P.E. 

NASA Technical Fellow for Loads & Dynamics

NASA Engineering and Safety Center (NESC) 

281-483-8401 phone 

713-392-4923 cell 

http://nesc.nasa.gov/

NASA (internal only) Loads and Dynamics Community of Practice: 

https://nen.nasa.gov/web/lnd
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Structural Analysis Peer Review for the Static Display of the Orbiter 

Atlantis at the Kennedy Space Center Visitors Center

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Minute, Stephen A.

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NASA Langley Research Center

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Mr. Christopher Miller with the Kennedy Space Center (KSC) NASA Safety & Mission Assurance (S&MA) office requested 

the NASA Engineering and Safety Center's (NESC) technical support on March 15, 2012, to review and make 

recommendations on the structural analysis being performed for the Orbiter Atlantis static display at the KSC Visitor Center. 

The principal focus of the assessment was to review the engineering firm's structural analysis for lifting and aligning the 

orbiter and its static display configuration. 

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NASA Engineering and Safety Center; Orbiter Atlantis; Retirement; Safety and Mission Assurance; Static Display; Transition

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