File talk:Type II ACBM Assy.jpg

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Prior Publication: //www.ehdavis.engineering/Exegeses/common-berthing-mechanism-core-design-description/

Created in TurboCAD 10.2 and TurboCAD 2019 based on multiple sources of geometry and dimensions. No copyrighted graphics are incorporated. Critical geometric features and dimensions are taken from SSP 41004J “CBM to Pressurized Element ICD”, several NASA Execute Packages, technical papers found in the NTRS, and many on-orbit photographs stored in the National Archives. Ancillary features and details have been simplified or omitted for clarity. Drawing is not to a scale of uniform precision.

References used to develop the image:

  1. S683-229902B “Active Common Berthing Mechanism Prime Item Development Specification”, CAGE 3A768, October 1, 1998. Referred to in the notes as “the spec”.
  2. SSP-41004J “Common Berthing Mechanism to Pressurized Elements Interface Control Document Part 2”, National Aeronautics and Space Administration/Johnson Space Center, Houston, Texas (October 25, 2005). The ICD is authoritatively called by the spec as being applicable in its entirety. Referred to below as “the ICD”.
  3. T683-13850-3, “Common Berthing Mechanism Assembly Qualification Test Report”, Boeing Defense and Space Group, Missiles and Space Division, Huntsville, AL (October 8, 1998). Referred to here as “the AQT”.
  4. NSTS photographs of assembly and on-orbit operations in the National Archives (e.g., //catalog.archives.gov/search?q=common%20berthing%20mechanism&f.materialsType=photographsandgraphics). All NSTS photographs are now in the archives, including many previously published on neither the NASA website nor on the new Flikr feed. Where some specific photograph is referred to, a NASA photograph designator is used.
  5. ISS photographs of assembly and other on-orbit operations in the NASA collections (https://www.flickr.com/photos/nasa2explore/). Where some specific photograph is referred to, a NASA photograph designator is used. Few, if any, of the ISS Expedition photographs are yet available in the national archives. Only a small fraction appear to have been published as yet on the Flikr feed.
  6. The Kennedy Space Center media archives (//mediaarchive.ksc.nasa.gov/#/Home/), referred to below as “KSC”.
  7. JSC-48503, “International Space Station ISS/Shttle Joint Operations Book”, National Aeronautics and Space Administration/Johnson Space Center Mission Operations Directorate, Operations Division (28 JUN 05), referred to in the notes as “Joint Ops”. See //www.nasa.gov/centers/johnson/pdf/123838main_iss_shuttle_joint_ops_book.pdf.
  8. JSC-48502-5A “International Space Station Assembly Operations Book ISS-5A (Final)”, National Aeronautics and Space Administration/Johnson Space Center Mission Operations Directorate, Operations Division, August 16, 2000. Referred to as “5A Assy Ops” below. See //www.spaceref.com/iss/ops/5A.Assembly.Ops.Final.pdf.
  9. Sievers, Daniel E. and Harry K. Warden, “International Space Station Powered Bolt Nut Anomaly and Failure Analyusis Summary, 40th Aerospace Mechanisms Symposium (2010). See NTRS (//ntrs.nasa.gov/search.jsp) record 201000321933. Referred to in the notes as “Sievers and Warden”.
  10. McLaughlin, Richard J., and William H. Warr, “The Common Berthing Mechanism (CBM) for International Space Station”, SAE (2001). Referred to in the notes as “Honeywell”. This paper is already available on Wikipedia.
  11. Zipay, John J, Karen S. Bernstein, Erica E. Bruno, Phillipe Deloo, Raymond Patin, “Structural Verification of the First Orbital Wonder of the World – The Structural Testing and Analysis of the International Space Station (ISS)”, National Aeronautics and Space Administration, Johnson Space Center, Houston TX (2011). See NTRS, record #20110013394. Referred to in the notes as “Zipay”.
  12. Several NSTS Execution Packages, all of which are internet searchable by the filenames given below.
  13. JSC-48513-4A, “International Space Station Maintenance & Repair Group (MRG) In-Flight Maintenance Book ISS-4A” (2000), NASA Johnson Space Center, Mission Operations Directorate, Operations Division. See http://www.spaceref.com/iss/ops/4a.ifm.pdf. Referred to in the notes as “4A IFM”.

Notes

  1. Typing (“Type II ACBM”) is defined in Section 3.1 of the spec.
    1. The Type II definition specifically includes M/D protection for Resource Node Radial Ports. It is used for ports that are exposed to the space environment for long periods of time or in relatively aggressive flight orientations.
    2. The spec makes no mention of the bumpers, observed on radial ports only. It is unclear whether they’re considered part of the Type II, or merely a different design that happens to be unique to those locations. They’re shown in the subject image only (not in the Type I image).
  2. The AQT identifies the spec as the source of requirements for which compliance is being verified, establishing the report’s relevance. It identifies many major components by nomenclature in Figure 2-1. That nomenclature was used to correlate with the qualification part numbers listed in Appendix B (“CBM ALQT Test Article Summary”) of the test report. The designs might (or might not) have been revised since qualification, so part numbers might have changed since that time (1998). No attempt has been made to reconcile current part numbers with those that were originally qualified.
  3. Critical dimensions of the ACBM structural ring are documented in several figures of the ICD.
    1. The height of the ring is found in Figure 3.1.4.1-4.
    2. Planform dimensions of the lower (“inboard”) flange of the ring are in Figures 3.3.2.1-2 and -3. The thickness of the inboard flange is from Figure 3.1.4.1-10.
    3. Thickness of the outboard flange was estimated from flight photographs (e.g., STS092-354-019 at //catalog.archives.gov/id/23171334) as being the same as that of the PCBM ring. It was further observed from flight photographs (see sts092-354-013 in the National Archives) and from the AQT that the two sides mount the same part number of Alignment Guide, identically installed (the part markings are legible in the reference photograph). The thickness of the PCBM flange itself is found in Figure 3.3.10-10 of the ICD. The outboard flange diameter is found in Figure 3.3.7-1. The outboard flange’s inner diameter and powered bolt locations are given in Figure 3.1.4.1-8.
    4. Similarly, the gussets of the two rings (ACBM and PCBM) appear on flight photographs to be aligned. The PCBM gusset locations were taken from Figure 3.3.10-9 of the ICD. Their thickness is dimensioned in Figure 3.3.10-12. Both dimensions were applied to the ACBM ring.
    5. Thickness of the vestibule wall on the ACBM ring is not clearly documented in the available material. It was assumed as equal to that of the PCBM ring, which is explicitly shown in Figure 3.3.10-10 of the ICD.
  4. Clearance dimensions for the Alignment Guides are found in Figure 3.1.4.1-14 and -15. They do not appear to be uniformly consistent with scaling from multiple flight photographs. “Artistic” license has been taken in the image to be more consistent with the photographs. License includes, but is not limited to, the apparent difference in material (or finish) between two sections of each guide. The sections appear to be riveted together. See, for example, sts097-330-011 (//catalog.archives.gov/id/23215626) and several photographs taken in profile during STS-124 EVA preparation of the Kibo ACBM.
  5. The ICD also located and provided the envelope for the Capture Latch. On-orbit photographs such as the afore-mentioned sts097-330-011 and S124E006465 (//catalog.archives.gov/id/23466528) and the figures on Pages 142 and 143 of the 5A Assy Ops were used to estimate the geometry and size of the individual latch linkages, as well as the size and mounting method for the actuator. Only the visible elements of the latch were modeled for this image.
  6. ICD Figures 3.1.4.1-11, -12, and -13 locate and provide enveloping geometry for the Ready-to-Latch indicator. There appear to be discrepancies between the height of the envelope in the ICD and on-orbit photographs (e.g., S124E006465 mentioned above). The height was estimated from flight photographs based on its apparent relationship to the face of the outboard flange (the CBM/CBM interface plane).
  7. Envelopes for the Alignment Pin are defined in ICD Figure 3.3.10-5. Upper-bound values for the details were scaled on the basis of the mating feature on the PCBM, as shown in Figure 2 of the Joint Ops. The photograph is nearly a planform (orthogonal) view, and the width of the outboard flange is reasonably discernable as a basis for estimation. The results were compared to (and adjusted from) photographs of the pre-berthed ACBM interface taken during EVA on STS-124 on which the pins can be plainly observed.
  8. The enveloping dimensions of the Strike Plate are shown on Figure 3.3.10-6 of the ICD. The geometry was adjusted on the basis of flight photographs from (primarily) STS-124.
  9. Envelopes and locations for the Controller Panel Assembly (CPA) are shown in Figures 3.3.4.3-1 and -2. Geometric features of the CPA are observable in figure 4 of Honeywell, and in several on-orbit photographs (e.g., STS102-328-033, STS106-304-024, SS003-E-5134), from which proportions were estimated.
  10. The berthing plate and hatch were not modeled for this image for three reasons:
    1. The spec did not regard them as part of the CBM.
    2. The ICD describes the plate (in effect) as the thing an ACBM mounts to, and the hatch as plugging the hole in the plate. That is consistent with Zipay (see, in particular, Figures 2 and 3 of Zipay).
    3. The AQT describes them as part of the test fixture rather than as part of the test article.
  11. Flight photographs show a large assortment of grounding straps, brackets, and fasteners. None are germane to understanding the general arrangement of the design. Only a few of those one the M/D center section were modeled, exclusively for artistic purposes (the large, empty expanse looked bare). No specific version of the cover is intended in this respect.
  12. The “stay-out” profile for the CPA and M/D cover center section is defined in ICD Figures 3.1.4.1-20 and -21. Noting, from flight photographs, that the center section envelopes the CPA’s in that direction, it was taken as applicable to the center section in its entirety.
    1. STS092-335-009 shows the installed center section in near profile. The height is readily compared to that of the structural ring, alignment guides, extended capture latch, CPA, and bumpers.
    2. ) ISS047e028518 shows the center section under handling by IVA crew. Pulleys (including the installation stud), standoffs, straps, turnbuckles and seams are easily recognizable.
    3. Retention provisions for the hatch window cover are identified as “velcro” on page 24 (“Page 2 of 2, 16-0056A (MSG-032A)”) in Flight Day 04 Execute Package for STS-120/10A (194491main_fd04exec.pdf).
    4. Many features of the center section are shown and labeled in figures on pages 34 – 40 (pdf pages 37 through 43) of Flight Day 13 Execute Package for STS-126/ULF2 (293870main_FD13EP.pdf), which also describes many aspects of IVA installation operations. The relationship between the center section and the clevises is plainly shown in this material.
  13. Unfortunately, envelopes for the deployable “petals” (outboard sections) of the M/D cover are incorporated into the ICD by reference to a CATIA model in Section 3.1.4.4. Dimensions are, therefore, not directly available.
    1. ICD Figures 3.1.4-7.1, -7.2, and -7.3 provide static and dynamic envelopes for the petals in their deployed configuration, but few actual dimensions.
    2. A good qualitative impression of the fit between the deployed petals and a berthed element can be obtained from sts098-705-011. This photograph also illustrates details on the underside of the petal that are not readily apparent in other flight photographs.
  14. Bracket locations for M/D shields (co-located with radial port petals) are shown for Node 2 in ICD Figure 3.3.12-1. The “goose-neck” of the bracket is plainly visible in several preflight processing photographs from KSC (e.g, in two locations near the upper corners of 04pd0633). Although the goose-neck bracket itself was not modeled, these figures were used to locate and roughly size the petal deployment mechanism bracket.
    1. The “split” design of the petal mechanism bracket attached to the outside of the ACBM ring is also clear from the KSC preflight processing photographs referenced in other notes herein. The petals and clevises themselves are not yet installed in those photographs.
    2. Several of the subject preflight processing photographs also show the brackets for the center section’s standoffs on either side of the CPA’s. In some of the photographs, the brackets are present but not yet fully installed into the “hatch beam”. These, and other nearby parts, are explicitly labeled on “page 22” (pdf page 25) of Flight Day 03 Execute Package for STS-122 (211206main_fd03_exec_pkg.pdf).
    3. 98pc1125 (KSC) shows the standoff brackets fully installed. The location and planform of the center section’s clevises is clearly shown on the left, just below the horizontal centerline of the photo.
  15. 255-STS-STS088-353-016, ISS022E065750 and ISS022E065751 clearly show how the “plate” is fastened to the petal and into a pair of clevises (referred to here as “plate clevises”) atop the “split” installation bracket.
    1. They also show a second link between a clevis on the back of the plate and another clevis, which is itself partially buried into the valley around the outside of the ring. ISS022E065750 and 255-STS-STS-088-352-12 and 255-STS-STS-101-374-14 hint at the shape of the second link, but leaves much to the interpretation. The best side view of this link is found on STS088-310-033, but the geometric information is still insufficient to enable detailed modeling of that link, so it was omitted from the subject figure. The perspective of the subject figure was purposely selected to mitigate the omission of these features.
    2. ISS022E065758 shows the plate clevises in profile. It also clearly profiles the fitting used to actuate closure of the petal by the capture latch. By virtue of high resolution, low distortion, and evident steady hand while snapping the shutter, the original jpeg photo is amenable to significant enhancement and enlargement, making it easier to distinguish the subject features.
  16. 255-STS-STS088-353-016 is a nearly-orthogonal image of the petal’s planform, showing how the bottom plate sits on the ACBM strike plates. See also ISS022E065751.
    1. It also illustrates that there are two distinct petals (“left hand” and “right hand”), and that the two ends of each petal are distinct. See also STS088-347-033.
      1. STS092-335-009, however, shows that the two distinct petal designs are not fully symmetric: the secondary feature mounted to the underside is “to clockwise” on both designs.
      2. The integrated CAD developed for the subject image strongly suggests that the (non-symmetrically installed) underside feature is very close to alignment with the RTL. The proportions suggest that it would depress the RTL during closure of the petal. Confirmation of the actuating stroke (depth of plunge) for the RTL is not available at this time. The feature was, however, modeled on the centerline of the RTL.
    2. The geometric relationship between petals and alignment pins is plainly evident.
  17. The underside of the petal is well displayed from two perspectives in S133E007596.
    1. The underside of the deployed petal is clearly seen in STS098-705-011 showing how the ends are connected to (and support) the central plate.
    2. The petal underside is also well displayed in STS092-335-009.
  18. ISS022E065751 shows the three different surfaces that are presented on the outer (CBM axial) face of the petal, the CBM-radial outboard surface, and the profile of the guide “pocket” that accommodates the alignment guides underneath.
  19. ISS022E065758 provides a nearly square profile of the “trigger” and the deployment clevises. The trigger is shown well enough to plausibly conclude it must extend, since it clearly cannot otherwise span far enough across the ring’s outboard flange to permit closure of the capture latch during petal retraction. Being irrelevant to the subject picture, the extension was not modeled. The photograph also shows the clearance behind the deployed cover.
  20. Little information about the deployment mechanism’s actuation was found. A qualitative assessment of the petal deployment dynamics from on-orbit video shows it continuing to move after release of the capture latch during deployment, suggesting that the deployment mechanism incorporates some sort of (probably spring-loaded) actuator, but that conclusion is little better than mere speculation. No associated feature was modeled for the subject image.
  21. The IVA seals, not shown, are delivered to orbit in kit form. The kits include parts for the CBM/PE and CBM/CBM joints, spline locks and “butter dish” covers for the powered bolts, and ancillary pieces. See the 4A IFM, pages 98-128. The IVA seal land covers, also not shown, are delivered in place. See the 4A IFM, page 122, and numerous flight photographs.

Not fred999 (talk) 22:27, 29 February 2020 (UTC)[reply]

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