File talk:Type I ACBM.jpg

From Wikimedia Commons, the free media repository
Jump to navigation Jump to search

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

References:

  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 in the notes 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. 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 I ACBM”) is defined in Section 3.1 of the spec. The Type I definition specifically excludes M/D protection for Resource Node Radial Ports. It is used for ports that are exposed to the space environment for short periods of time or in relatively benign flight orientations.
  2. The AQT identifies the spec as the source of requirements for which compliance is being verified, establishing its 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 numerous 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 were taken from 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 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. Figure 1 of Sievers and Warden shows a cross-section of the Powered Bolt. Details of the housing were simplified into flanged right circular cylinders, very little of which can be seen in the subject image.
    1. Of the bolt assembly’s internal parts, only the tip of the shaft was modeled. The shaft diameter was back-calculated as 0.625 inch from the equation in the abscissa label of Figure 5-7 of the AQT, given the values documented in section 5.2.2 thereof.
    2. The aspect ratio of the outboard flange does not compare well to cross-sections in the ICD: it appears to be longer in the radial direction than other cross-sections show. A good view of the bolt housing without an actuator mounted is available in KSC photo 2010-3453 (//mediaarchive.ksc.nasa.gov/#/Detail/47029). Noting that Figure 1 of Sievers and Warden appears to show that it is radial, it seems safe to assume that the cross-section of that figure is, in fact, non-radial. The apparent aspect ratio of that figure was, therefore, disregarded here. The longitudinal proportions were accepted.
      1. The description of the referenced KSC photo identifies the CBM as “...a test fixture that simulates the joining of of the International Space Station with a pressurized element”. This appears to be incorrect, since many features described in the spec and ICD are missing from the article. The subject of the photo appears to be a piece of Test Support Equipment that emulates a subset of CBM features.
  10. The gross envelope dimensions for Powered Bolt Actuator are available in Figures 3.1.4.1-9 and -10 of the ICD. Noting that the ICD figures are merely envelopes, additional geometric features and proportions can be estimated from Figures 6 and 7 of Honeywell, from the figures on pages 130 and 131 of 5A Assy Ops and from numerous flight photographs of the mated vestibule (e.g., STS106-372-019 and STS101-387-016).
  11. 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.
  12. 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).
    3. The AQT describes them as part of the test fixture rather than as part of the test article.
  13. Routing of actuator and sensor harnessing from the CPA’s is evident on several photographs already mentioned, and in figures on pages 129, 130, 131, and 142 of 5A Assy Ops. The routing appears to utilize specific features of the (not modeled) berthing plate. Therefore, no attempt was made to accurately route harnessing in the subject image.
  14. The available sources were silent on the issue of whether power and data harnessing to the CPA’s was in-scope to the CBM design per se. They were omitted for this figure.
  15. Flight photographs show a large assortment of grounding straps, brackets, and fasteners. None are germane to understanding the overall arrangement of the design. None were modeled.
  16. 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) 22:17, 29 February 2020 (UTC)[reply]

Retrieved from "https://commons.wikimedia.org/w/index.php?title=File_talk:Type_I_ACBM.jpg&oldid=401012040"