The file's text, extracted by GovTribe without its formatting.
ISS Configuration Document
International Space Station Program
Revision A
April 2015
National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract No.: NNJ12GA46C
SSP 50110 Draft
SSP 50949
Revision A viii 11-28-94 A-
REVISION AND HISTORY PAGE
| REV. |
| DESCRIPTION |
| PUB. DATE |
| - |
| Initial Release (Reference per SSCD 013357, EFF. 09-21-12) |
| 04-10-13 |
| A |
| Revision A (Reference per SSCD 13848, EFF. 02-05-16) |
SSP 50949
Revision A
PREFACE
ISS Configuration document The contents of this document are to be consistent with the tasks and products prepared by the International Space Station (ISS) Program participants as specified in SSP 50011-01, Concept of Operation and Utilization, Volume 1: Principles. Official deliveries of this document are under control of the Space Station Control Board (SSCB) and any changes or revisions will be jointly agreed to and signed by the SSCB.
v
INTERNATIONAL SPACE STATION PROGRAM
ISS Configuration document
CONCURRENCE
April 2015 concurrence
APRIL 2015
TABLE OF CONTENTS
| PARAGRAPH | PAGE | |
| 1.0 | INTRODUCTION | 1-1 |
| 1.1 | PURPOSE | 1-1 |
| 1.2 | SCOPE | 1-1 |
| 1.3 | PRECEDENCE | 1-1 |
| 1.4 | DELEGATION OF AUTHORITY | 1-1 |
| 1.5 | CHANGES | 1-1 |
| 2.0 | DOCUMENTS | 2-1 |
| 2.1 | applicable documents | 2-1 |
| 2.2 | reference documents | 2-1 |
| 3.0 | EXTERNAL CONFIGURATION and robotic task descriptions | 3-1 |
| 3.1 | CONFIGURATION | 3-1 |
| 3.1.1 | ISS element CONFIGURATION | 3-1 |
| 3.1.2 | ISS PORT connectivity | 3-3 |
| 3.1.3 | Truss Configuration | 3-5 |
| 3.1.4 | Express logistics carrier (ELc) on-orbit stowage | 3-8 |
| 3.1.5 | EXternal camera/video port Configuration PLAN | 3-13 |
| 3.1.6 | ISS Retro Reflector Configuration | 3-15 |
| 3.1.7 | columbus external payload facility (Epf) on-orbit configuration | 3-20 |
| 3.1.8 | Japanese Experiment Module Exposed Facility (JEM EF) on-orbit configuration | 3-20 |
| 3.2 | robotic task descriptions | 3-21 |
| 4.0 | ISS INTERNAL TOPOLOGY | 4-1 |
| 4.1 | interior volume CONFIGURATION Constraints | 4-1 |
| 4.2 | USOS Rack Position Allocations | 4-1 |
| 4.3 | USOS INterior Volume TopologY | 4-3 |
APPENDIX
| a | Acronyms and abbreviations | a-1 |
| b | glossary | b-1 |
| c | open work | c-1 |
| d | ISS Configuration Roadmap | d-1 |
TABLE
| 3.1.5-1 | EXTERNAL CAMERA/VIDEO PORT PLAN | 3-13 |
| 3.1.6-1 | ISS RETRO REFLECTOR DATA (2 pages) | 3-16 |
| C-1 | TO be determined items | c-1 |
| C-2 | TO BE RESOLVED ISSUES | c-1 |
| D-1 | ISS Configuration Roadmap (PAGE 1 OF 2) | d-1 |
FIGURE
| 3.1.1-1 | ISS CONFIGURATION | 3-2 |
| 3.1.2-1 | ISS PORT connectivity <TBR 3-1> | 3-4 |
| 3.1.3-1 | TRUSS ConfiguratioN | 3-5 |
| 3.1.3-2 | ESP-1 ON-ORBIT CONFIGURATION | 3-6 |
| 3.1.3-3 | ESP-2 ON-ORBIT CONFIGURATION | 3-7 |
| 3.1.3-4 | ESP-3 ON-ORBIT CONFIGURATION | 3-8 |
| 3.1.4-1 | ELC-1 ON-ORBIT CONFIGURATION | 3-9 |
| 3.1.4-2 | ELC-2 ON-ORBIT CONFIGURATION | 3-10 |
| 3.1.4-3 | ELC-3 ON-ORBIT CONFIGURATION | 3-11 |
| 3.1.4-4 | ELC-4 ON-ORBIT CONFIGURATION | 3-12 |
| 3.1.5-1 | External Camera/Video Ports | 3-14 |
| 3.1.6-1 | USOS RETRO REFLECTOR LABELS | 3-18 |
| 3.1.6-2 | ISS REFLECTOR COVERAGE MAP | 3-19 |
| 3.1.7-1 | Columbus-epf Site Labeling | 3-20 |
| 3.1.8-1 | JEM-EF Site labeling | 3-21 |
| 4.2-1 | USOS Rack Position Allocations | 4-2 |
| 4.3-1 | USOS internal topology – Increment 43 and increment 44 | 4-3 |
| 4.3-2 | USOS INternal Topology - Increment 45 through increment 64 | 4-4 |
1-1
INTRODUCTION
PURPOSE
The purpose of this document is to control the International Space Station (ISS) baseline module configuration, external platform configuration and internal volume rack and large equipment configuration. This document provides the mechanism for coordination across the ISS Program, including International Partners (IPs).
SCOPE
The ISS Configuration Document (ISSCD) defines major ISS configurations and port connectivity. In addition, the document also illustrates ISS external configuration data and increment-by-increment internal volume configurations.
PRECEDENCE
Information contained in this document will be consistent with other ISS Program documentation. The configuration data depicted in this document takes precedence over any other documentation with the exception of the SSP 54100, Multi-Increment Planning Document, and the Increment-specific Increment Definition and Requirements Document (IDRD).
DELEGATION OF AUTHORITY
The ISSCD is prepared by the Vehicle Enhancement Team, for approval by the Space Station Control Board (SSCB). The SSCB delegates technical management of the ISSCD to the ISS Systems Engineering & Integration Office/OM; however, the SSCB retains the control of changes or revisions to the document.
CHANGES
The ISSCD will be updated, as required, to reflect major changes. Other requests for revisions should be made to the controlling authority in accordance with the procedures defined in SSP 41170, Configuration Management Requirements.
DOCUMENTS
applicable documents The following documents include specifications, models, standards, guidelines, handbooks, and other special publications. The documents listed in this paragraph are applicable to the extent specified herein. Inclusion of applicable documents herein does not in any way supersede the order of precedence identified in Paragraph 1.3 of this document.
| SSP 41170 |
| Configuration Management Requirements |
| SSP 50011-01 |
| Concept of Operation and Utilization, |
Volume 1: Principles
| SSP 50261-01 |
| Generic Groundrules, Requirements, and Constraints, |
Part 1: Strategic and Tactical Planning
| SSP 54100 |
| Multi-Increment Planning Document |
reference documents The following documents contain supplemental information to guide the user in the application of this document. These reference documents may or may not be specifically cited within the text of this document.
| No Number |
| IP Memoranda of Understanding |
| SSP 41000 |
| System Specification for the International Space Station |
| SSP 50200-01 |
| Station Program Implementation Plan, |
Volume 1: Station Program Management Plan
| SSP 50450 |
| Multi-Increment Payload Resupply and Outfitting Model (MiPROM) |
| SSP 54004 |
| Increment Definition and Requirements Document for Increment X Annex 5: Payload Tactical Plan |
2-1
EXTERNAL CONFIGURATION and robotic task descriptions
CONFIGURATION
This section documents the ISS configuration baseline after each change. It serves as the official baseline regarding modules, trusses, external carrier placement, external payload and Orbital Replacement Unit (ORU) stowage locations and external camera/video port utilization with associated constraints.
Russian concurrence is required only for Paragraphs 3.1.1 and 3.1.2 since the remaining information applies to the United States On-orbit Segment (USOS) only.
ISS element CONFIGURATION The ISS element configuration of the ISS is controlled by the SSCB in accordance with SSP 41170 and is reflected in Figure 3.1.1-1, ISS Configuration.
International Docking Adapter (IDA)-1 will be installed to Pressurized Mating Adapter (PMA)-2 to enable the docking of the future USOS crew vehicles. PMA-3 will be moved to Node 2 Zenith where the International Docking Adapter (IDA)-2 will be installed to enable the docking of the future USOS crew vehicles. The Permanent Multipurpose Module (PMM) will also be moved to Node 3 Forward. These moves and other hardware moves are depicted in Figure 3.1.1-1.
3-4
Figure 3.1.1-1 ISS CONFIGURATION ISS PORT connectivity Figure 3.1.2-1, ISS Port Connectivity <TBR 3-1>, shows the ISS ports, port mechanisms, and open ports on the ISS. Visiting Vehicle (VV), element locations and attach methods are also identified. The port connectivity figure is not intended to show vehicle traffic.
A legend is provided to describe the colors, shading, and acronyms. Green highlights indicate open ISS ports for visiting vehicle/element dockings. The cross-hatching on the Node 3 Zenith port indicates that the port has been disabled and has been identified as a Special Purpose Dexterous Manipulator (SPDM) parking spot.
The berthing/docking mechanism at each port is accompanied by an “(A)” which indicates an active mechanism whereas the “(P)” indicates a passive mechanism. All vehicle traffic constraints are captured in SSP 50261-01, Generic Groundrules, Requirements, and Constraints Part 1: Strategic and Tactical Planning.
Figure 3.1.2-1 ISS PORT connectivity <TBR 3-1> Truss Configuration Figure 3.1.3-1, Truss Configuration, represents the truss configuration at the start of Increment 36 in May 2013, permanent relocations of ExPRESS Logistics Carrier (ELC)1, ELC2, ELC3, ELC4, Alpha Magnetic Spectrometer (AMS), and External Stowage Platform (ESP) 3 are not currently planned and will remain in the configuration outlined below.
P3 ELC3 on P3 Upper ELC1 on P3 Lower S3 ELC2 on S3 Upper Outboard AMS on S3 Upper Inboard ESP-3 on S3 Lower Outboard ELC4 on S3 Lower Inboard
Figure 3.1.3-1 TRUSS ConfiguratioN Planned use of stowage locations on ESP-1, ESP-2, and ESP-3 are shown graphically in Figure 3.1.3-2, ESP-1 On-Orbit Configuration, through Figure 3.1.3-4, ESP-3 OnOrbit Configuration. Changes in ESP configurations may occur in response to onorbit events such as an ORU failure requiring a Remove and Replace (R&R) operation. In each carrier description, failed ORUs will be represented by stating “Failed” next to the respective ORU. ORU moves are also tracked in the Incrementspecific IDRD, On-Orbit Configuration Plan, and External Configuration Analysis Tracking Tool “ExCATT.” Further detail on all of these products are included in the configuration roadmap included in Appendix D of this document.
ESP-1 is attached to the Laboratory (Lab) and has two square grid interface attach sites. The ORUs shown in Figure 3.1.3-2 are listed below with the appropriate site numbering.
Site 1: Direct Current Switching Unit (DCSU) Site 2: Pump/Flow Control Subassembly (PFCS)
Figure 3.1.3-2 ESP-1 ON-ORBIT CONFIGURATION ESP-2 is attached to the airlock and has eight Flight Releasable Attachment Mechanism (FRAM) attach sites. The ORUs shown in Figure 3.1.3-3, ESP-2 OnOrbit Configuration, are listed below with the appropriate site numbering.
Zenith Site 1: Pump Module (PM) Site 2: DCSU Site 3: Cargo Transport Container (CTC-3) Site 4: Main Bus Switching Unit (MBSU) Nadir Site 5: Yaw Joint Site 6: MBSU Site 7: Flex Hose Rotary Coupler (FHRC) with Adjustable Grapple Bar (AGB) Site 8: Utility Transfer Assembly (UTA)
Figure 3.1.3-3 ESP-2 ON-ORBIT CONFIGURATION ESP-3 is attached to S3 Lower Outboard with six attach sites and one direct mount attach site. The ORUs shown in Figure 3.1.3-4 are listed below with the appropriate site numbering.
Inboard Site 5: Space to Ground Antenna (SGANT) Site 6: Battery Charge Discharge Unit (BCDU) Direct Mount (DM): Ammonia Tank Assembly (ATA) Flight Support Equipment (FSE) potential to be converted to two ORU compatible sites in 2017 Outboard Site 1: Pitch/Roll (P/R) Joint Site 2: FHRC Site 3: Empty (Previous Pump Module Location) Site 4: Linear Drive Unit (LDU)
Figure 3.1.3-4 ESP-3 ON-ORBIT CONFIGURATION Express logistics carrier (ELc) on-orbit stowage The ELC On-Orbit stowage plan is graphically shown in Figures 3.1.4-1, ELC-1 OnOrbit Configuration, through 3.1.4-4, ELC4 On-Orbit Configuration. In the graphics, ELC locations reserved for utilization payloads are shown “as payload sites.”
Changes in ELC configurations may occur as launch dates approach or in response to on-orbit events, such as an ORU failure requiring an R&R operation, or the arrival of replacement utilization. In each carrier description, failed ORUs will be represented by stating “Failed” next to the respective ORU. ORU moves are also tracked in the Increment-specific IDRD, On-Orbit Configuration Plan, and ExCATT. Payload traffic is tracked in the Increment-specific IDRD, Annex 5 which captures the external topologies and sub-rack topologies. The MiPROM captures the external strategic payload topologies.
Further detail on all of these products are included in the configuration roadmap included in Appendix D of this document.
ELC1, shown in Figure 3.1.4-1, is attached to P3 lower and has nine stowage sites. Two sites are dedicated to utilization, one direct mount for an ATA, with the remaining sites for FRAM ORUs.
Outboard Side Site 1: Latching End Effector (LEE) Site 2: Plasma Contactor Unit (PCU) Site 3: Payload Site Site 4: BCDU Site 5: Control Moment Gyro (CMG) Inboard Side Site 6: Nitrogen Tank Assembly (NTA) Site 7: PM Site 8: Payload Site
DM: ATA
Figure 3.1.4-1 ELC-1 ON-ORBIT CONFIGURATION ELC2, shown in Figure 3.1.4-2, ELC-2 On-Orbit Configuration, is attached to S3 Upper Outboard and has nine stowage sites. Two sites are dedicated to utilization, one direct mount High Pressure Gas Tank (HPGT) site, with the remaining sites for FRAM ORUs.
Outboard Side Site 5: NTA Site 6: PM (failed) Site 7: Payload Site Site 8: Trailing Umbilical System - Reel Assembly (TUS-RA) Inboard Side Site 1: MBSU Site 2: DCSU Site 3: Payload Site Site 4: CMG DM: High Pressure Gas Tank (HPGT) FSE
Figure 3.1.4-2 ELC-2 ON-ORBIT CONFIGURATION ELC3, shown in Figure 3.1.4-3, ELC-3 On-Orbit Configuration, is attached to P3 Upper and has eight stowage sites. Two sites are dedicated for utilization, one direct mount site for the SPDM Arm stowage, one direct mount site dedicated to HPGT stowage, and one direct mount site dedicated to ATA stowage. The remaining sites are for FRAM ORUs.
Outboard Side Site 4: S-Band Antenna Sub-Assembly (SASA)
DM: HPGT (O2)
Site 5: Payload Site
DM: ATA
Inboard Side DM: SPDM Arm Site 1: CTC-5 Site 2: SASA Site 3: Payload Site
Figure 3.1.4-3 ELC-3 ON-ORBIT CONFIGURATION
ELC4, shown in Figure 3.1.4-4, is attached to S3 Lower Inboard and has five stowage sites, two of which are dedicated for utilization and one direct mount site dedicated to Heat Rejection Subsystem (HRS) Radiator stowage. The remaining sites are dedicated to FRAM ORUs.
Outboard Side DM: HRS Radiator Inboard Side Site 1: CTC-2 Site 2: Payload Site Site 3: Payload Site Site 4: UTA Site 5: FHRC
Figure 3.1.4-4 ELC-4 ON-ORBIT CONFIGURATION EXternal camera/video port Configuration PLAN Table 3.1.5-1, External Camera/Video Port Plan, identifies the usage of each of the fourteen camera ports on ISS. The table identifies existing hardware at each location and, if required, reflects changes as they occur.
The table shows the ISS timeline along the far left column and the Camera Port (CP) number in the top row. The location of each camera port is shown below the camera port number designation and is marked with an asterisk (*) at the locations that can be utilized by wireless video transceivers. The hardware located at each camera port includes the Wireless Video System External Transceiver Assembly (WETA), the External Television Camera Group (ETVCG), the Floating Potential Measurement Unit (FPMU), and the Orbiter Boom Sensor System (OBSS) Keep Alive Umbilical (KAU). Figure 3.1.5-1, External Camera/Video Ports depicts the location of each camera/video port and identifies what hardware is attached at each location.
TABLE 3.1.5-1 EXTERNAL CAMERA/VIDEO PORT PLAN
ISS Camera Ports
| CP1 |
| CP2 |
| CP3 |
| CP4 |
| CP5 |
| CP6 |
| CP7 |
| CP8 |
| CP9 |
| CP10 |
| CP11 |
| CP12 |
| CP13 |
| CP14 |
| MBS |
| Flight |
| S3 * |
| S1 Outboard Upper * |
(4)(5) S1 Outboard Lower * (5)(12) S1 Inboard Upper (2) S1 Inboard Lower * (3) P1 Inboard Upper (2) P1 Inboard Lower * (19)
| P1 Outboard Upper * |
| P1 Outboard Lower * |
(13)
(10)
FPMU
Mast Camera
WETA
FPMU
Mast Camera
WETA
FPMU
Mast Camera
WETA
FPMU
Mast Camera
WETA
FPMU
Mast Camera
FPMU
Mast Camera
Notes:
* - Wireless video transceivers can be used on these ports.
(2) The use of the S1 Inboard Upper (CP4) and P1 Inboard Upper (CP6) camera ports should be minimized due to potential camera damage from S-band antenna radiation.
(3) The S1 Inboard Lower (CP5) camera port is unavailable when ESP-2 is attached to the Airlock forward trunnion due to physical clearances.
(4) S1 Outboard Upper (CP2) camera port is unavailable when AMS (ULF6) is attached to S3 Upper Inboard PAS due to magnetic field interference issues with ETVCG and WETA.
(5) ELC cargo layout has been optimized to maximize clearance between the camera, including sweep envelope, and the ELC cargo.
(10) CP14 stanchion mount is available for structural attachment, but clearance issues with ESP1 exist. The port is not functional due to lack of wiring on Node 3.
(12) Installation of wedge at CP3 mounting location on ULF5 to angle the ETVCG away from the S3 PAS site, but still retain HTV Crew Monitoring capability.
(13) Close clearances exist to the installed 5th Airlock tank if R&R is required
(19) Alternate mounting method must be used due to close proximity between CP7 and PMM when PMM is moved to Node 3 Forward, however EVA access to the connector panel remains
| Legend: |
| CP is not available for use |
| CP is available and not being utilized |
| CP is occupied |
Figure 3.1.5-1 External Camera/Video Ports
3-10
ISS Retro Reflector Configuration Laser retro reflectors for visiting vehicle use are strategically placed on ISS at various locations. These retro reflectors are used in conjunction with laser range-finding equipment on the visiting vehicles to provide range, range rate, and relative attitude information during vehicle approach and departure from the ISS. The locations of the various USOS and Russian Segment (RS) retro reflectors are shown in Figure 3.1.6-1, USOS Retro Reflector Labels, with coordinate locations shown in Table 3.1.6-1, ISS Retro Reflector Data. Figure 3.1.6-2, ISS Reflector Coverage Map, shows the reflector coverage.
TABLE 3.1.6-1 ISS RETRO REFLECTOR DATA (2 pages)
Inches (mm) Y coordinate Inches (mm) Z coordinate Inches (mm) Pointing Inches X Pointing Inches Y Pointing Inches Z Covered?
| PMA2 N2 Hemi |
| 533.22 |
| 0.31 |
| 240.56 |
| -0.0015 |
| -0.0044 |
| 1 |
| Yes (f) |
| PMA2 Planar |
| 607.25 |
| -11.51 |
| 183.79 |
| 1 |
| -0.0053 |
| -0.0061 |
| Yes (d) |
| JEM LRR Hemi A |
| 428.27 |
| -214.47 |
| 276.43 |
| 0.0035 |
| -0.0066 |
| 0.9999 |
| No |
| JEM LRR Hemi B |
| 428.2 |
| -239.85 |
| 276.27 |
| -0.0019 |
| -0.0049 |
| 0.9999 |
| No |
| FWD PMM Planer |
| 162.07 |
| -254.95 |
| 184.52 |
| 0.9999 |
| 0.0029 |
| 0.0014 |
| No |
| PMA3 Planar |
| 423.05 |
| -11.34 |
| 18.45 |
| 0 |
| 0.0015 |
| -1 |
| Yes (e) |
| PMA3 Hemi |
| 479.71 |
| 0.6 |
| 92.68 |
| 0.9999 |
| -0.0006 |
| -0.0018 |
| Yes |
| IDA 1 Hemi A (a) |
| 621.61 |
| 3.35 |
| 174.61 |
| 0.7075 |
| 0 |
| -0.7067 |
| No |
| IDA 1 Planar (a) |
| 621.65 |
| 44.25 |
| 214.02 |
| 1 |
| 0 |
| 0 |
| No |
| IDA 1 Hemi B (a) |
| 621.61 |
| 35.08 |
| 245.63 |
| 0.7067 |
| 0 |
| 0.7075 |
| No |
| IDA 2 Hemi A (b) |
| 414.69 |
| 3.7 |
| 4.49 |
| -0.7068 |
| 0 |
| -0.7074 |
| No |
| IDA 2 Planar (b) |
| 454.09 |
| 44.65 |
| 4.57 |
| 0 |
| 0 |
| -1 |
| No |
| IDA 2 Hemi B (b) |
| 485.71 |
| 35.43 |
| 4.57 |
| 0.7074 |
| 0 |
| -0.7068 |
| No |
| C2V2 S3 Forward Antenna Boom Hemi (c) |
| 60 |
| 901.06 |
| -55.79 |
| 0.9336 |
| 0 |
| 0.3584 |
| No |
| C2V2 P3 Zenith Antenna Boom Hemi (c) |
| -96.34 |
| -901.06 |
| -40.91 |
| -0.3091 |
| 0 |
| -0.951 |
| No |
| C2V2 P3 Nadir Antenna Boom Hemi (c) |
| -103.19 |
| -901.06 |
| -38.5 |
| -0.3007 |
| 0 |
| 0.9537 |
| No |
| FGB Forward |
| -401.47 |
| -30.71 |
| 142.01 |
| 0.9983 |
| 0.0538 |
| 0.0217 |
| No |
| FGB Aft |
| -837.73 |
| -11.3 |
| 91.58 |
| -0.9999 |
| -0.0007 |
| 0.0003 |
| No |
| SM MRR A No 1 (g,i) |
| -1401.413637 |
| -17.11125271 |
| 188.2815524 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM MRR A No 2 (g,i) |
| -1401.454051 |
| 24.08399823 |
| 179.6378646 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM MRR A No 3 (g,i) |
| -1404.221193 |
| 13.9923106 |
| 233.2659619 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM LRR PA V1 (i) |
| -1403.074896 |
| 6.903323744 |
| 200.2237114 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM LRR PA V2 (i) |
| -1403.077321 |
| 11.57310708 |
| 203.2534997 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM LRR PA V3 (i) |
| -1403.073657 |
| 8.543320482 |
| 207.9232833 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM LRR PA V4 (i) |
| -1403.071232 |
| 3.873537142 |
| 204.893495 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
| SM LRR PA V5 (i) |
| -1406.42 |
| 7.72 |
| 204.07 |
| -1 |
| 0 |
| 0 |
| (h) Partial obscuration |
Notes:
All locations and directions in SSACS. Unless otherwise noted herein, all primary dimensions are in the English system of units (inch, pound, second) followed by the equivalent International System (metric) value shown in parenthesis. Conversion will be in accordance with ASTM E380, Standard Practice for use of the International System of Units (SI) (The Modernized Metric System).
(a) IDA 1 reflector installation scheduled for second quarter 2015
(b) IDA 2 reflector installation scheduled for fourth quarter 2015
(c) C2V2 reflector installation scheduled for first quarter 2015
(d) PMA2 Planar reflector cover installation scheduled for second quarter 2015
(e) PMA3 Planar reflector cover installation scheduled for fourth quarter 2015
(f) PMA2 Hemi Retro-reflectors will be removed/covered second quarter 2015
(g) Each SM MRR is comprised of 7 planar retros. Individual RR locations are shown in In (mm) from the center MRR location as defined in the table above and have the same vector. The mm values are provided by RSC-E as design information.
(6.35)
(25.3) 0.57
(14.6)
(h) Vehicle at SM aft port presents partial obscuration.
(i) Vector data is as-designed for these targets.
Values for C2V2, IDA1, IDA2, PMM and PMA3 are based on design data and may change as source documentation becomes available. For the MRR LRRs in the table above under note (g), all primary dimensions are in the English system of units (inch, pound, second), followed by the equivalent in the International System of Units (SI) (The Modernized Metric System) value shown in parenthesis. Conversion will be in accordance with ASTM E380, Standard Practice.
Figure 3.1.6-1 USOS RETRO REFLECTOR LABELS
Figure 3.1.6-2 ISS REFLECTOR COVERAGE MAP columbus external payload facility (Epf) on-orbit configuration The payload stowage locations and the nomenclature for the site naming on the Columbus-EPF are shown in Figure 3.1.7-1, Columbus-EPF Site Labeling. The ColumbusEPF consists of four sites that are Columbus External Payload Adapter (CEPA) compatible. All four Columbus-EPF sites are dedicated to utilization. Payload traffic is tracked in the Increment-specific IDRD, Annex 5 which captures the external topologies and sub-rack topologies. The MiPROM captures the external strategic payload topologies. Further detail on these products are included in the configuration roadmap included in Appendix D of this document.
Figure 3.1.7-1 Columbus-epf Site Labeling Starboard Overhead Zenith (SOZ) Starboard Overhead X-Direction (SOX) Starboard Deck X - Direction (SDX) Starboard Deck Nadir (SDN) Japanese Experiment Module Exposed Facility (JEM EF) on-orbit configuration The graphical representation of the Japanese Experiment Module (JEM) accommodations on JEM-EF is shown in Figure 3.1.8-1, JEM-EF Site Labeling.
The JEM-EF has 12 Exposed Facility Units (EFUs), of which one is for the Inter-orbit Communications System (ICS) exposed unit located at site 7, one is for the H-II Transfer Vehicle (HTV) Exposed Pallet (EP) located at site 10, and the remaining 10 are designated for payloads and temporary locations for payload exchange.
Payload traffic is tracked in the Increment-specific IDRD, Annex 5 which captures the external topologies and sub-rack topologies. The MiPROM captures the external strategic payload topologies. Further detail on all of these products are included in the configuration roadmap included in Appendix D of this document.
figure 3.1.8-1 JEM-EF Site labeling robotic task descriptions All free flyer capture vehicles (HTV, SpaceX, and Orbital vehicles) require the use of the Space Station Remote Manipulator System (SSRMS) for berthing. Both the HTV and SpaceX vehicles have the capability to deliver unpressurized cargo which will require robotic extraction of the cargo from the vehicle. Robotic requirements for Orbital include the berthing/unberthing of the vehicle only.
The HTV-EP, with unpressurized cargo integrated to the deck, is extracted from the Unpressurized Logistics Carrier (ULC) by the SSRMS and either berthed directly to the Payload On-Orbit Accommodation (POA) or handed off to the JEM Remote Manipulator System (RMS) for berthing to the JEM-EF. The EP berthing location is dependent on the type of cargo manifested on the EP. The SSRMS/SPDM will transfer the FRAM interface cargo from the EP and the JEM RMS will be used for moving the JEM-EF payload on HTV-EP. When at least one Exposed Facility (EF) payload is manifest on the EP, the EP will berth to the JEM-EF.
The SSRMS/SPDM will be used for the extraction of cargo from the SpaceX Dragon trunk. For cargo installed to the ELC, the Enhanced ORU Temporary Platform (EOTP) can be used to assist in the robotic operations. For payload installation to the Columbus-EPF, the use of only SSRMS/SPDM is required.
ISS INTERNAL TOPOLOGY
The identified ISS internal volume constraints are applicable to all ISS interior integration processes to ensure that planned ISS interior configurations create an environment conducive to crew safety and mission productivity.
interior volume CONFIGURATION Constraints Constraints applicable to the integration of the ISS interior environment are documented in SSP 50261-01, Generic Groundrules, Requirements, and Constraints, Part 1: Strategic and Tactical Planning, Paragraph 3.12, Interior Volume Configuration. The constraints address free volume (unencumbered volume for crew physical and/or visual access to their environment) and hard protrusions (locations and volumes committed to the presence and/or operation of a particular piece of equipment).
Compliance with Program constraints for each internal ISS Increment configuration are verified in Increment Configuration Analysis. A separate Increment Analysis is completed for each Increment and supplied to the ISS community for review.
USOS Rack Position Allocations The interior volume USOS Rack Position Allocations, Figure 4.2-1, USOS Rack Position Allocations, displays the planned USOS ownership of the individual rack locations and notes the subgroup for which the rack belongs (i.e., utilization [payloads], system, or stowage). This chart will not change unless an agreement is made between Canadian Space Agency (CSA), European Space Agency (ESA), and/or Japan Aerospace Exploration Agency (JAXA) and National Aeronautics and Space Administration (NASA).
Figure 4.2-1 USOS Rack Position Allocations USOS INterior Volume TopologY The interior volume topologies are depicted in Figures 4.3-1, USOS Internal Topology – Increment 43 and Increment 44 and Figure 4.3-2, USOS Internal Topology - Increment 45 through Increment 64. For individual rack transfers during a particular Increment, refer to the “Configuration Changes” box included with the Increment topologies for rack relocations.
Topologies for the tactical timeframe are also captured in the Increment-specific IDRD at the rack level. Increment-specific IDRD, Annex 5 captures the external topologies and sub-rack topologies. The MiPROM captures the external strategic payload topologies.
Figure 4.3-1 USOS internal topology – Increment 43 and increment 44
Figure 4.3-2 USOS Internal Topology - Increment 45 through increment 64
Appendix a - Acronyms and abbreviations
| AGB |
| Adjustable Grapple Bar |
| AMS |
| Alpha Magnetic Spectrometer |
| ATA |
| Ammonia Tank Assembly |
| BCDU |
| Battery Charge Discharge Unit |
| CEPA |
| Columbus External Payload Adapter |
| CSA |
| Canadian Space Agency |
| CTC |
| Cargo Transport Container |
| DCSU |
| Direct Current Switching Unit |
| EFU |
| Exposed Facility Unit |
| ELC |
| ExPRESS Logistics Carrier |
| EOTP |
| Enhanced ORU Temporary Platform |
| EPF |
| External Payload Facility |
| ESA |
| European Space Agency |
| ESP |
| External Stowage Platform |
| ETVCG |
| External Television Camera Group |
| ExCATT |
| External Configuration Analysis Tracking Tool |
| ExPRESS |
| Expedite the Processing of Experiments to the Space Station |
| FHRC |
| Flex Hose Rotary Coupler |
| FPMU |
| Floating Potential Measurement Unit |
| FRAM |
| Flight Releasable Attachment Mechanism |
| FSE |
| Flight Support Equipment |
| HPGT |
| High Pressure Gas Tank |
| HRS |
| Heat Rejection Subsystem |
| HTV |
| H-II Transfer Vehicle |
| ICS |
| Inter-orbit Communications System |
| IDA |
| International Docking Adapter |
| IDRD |
| Increment Definition and Requirements Document |
| ISS |
| International Space Station |
| ISSCD |
| ISS Configuration Document |
| JAXA |
| Japan Aerospace Exploration Agency |
| JEM |
| Japanese Experiment Module |
| JEM-EF |
| Japanese Experiment Module-Exposed Facility |
| LEE |
| Latching End Effector |
| MBSU |
| Main Bus Switching Unit |
| MiPROM |
| Multi-increment Payload Resupply and Outfitting Model |
| NASA |
| National Aeronautics and Space Administration |
| NTA |
| Nitrogen Tank Assembly |
| OBSS |
| Orbiter Boom Sensor System |
| ORU |
| Orbital Replacement Unit |
| PCU |
| Plasma Contactor Unit |
| PFCS |
| Pump/Flow Control Subassembly |
| PMA |
| Pressurized Mating Adapter |
| PMM |
| Permanent Multipurpose Module |
| POA |
| Payload On-orbit Accommodation |
| RMS |
| Remote Manipulator System |
| SASA |
| S-Band Antenna Sub-Assembly |
| SDX |
| Starboard Deck X - Direction |
| SOX |
| Starboard Overhead X-Direction |
| SGANT |
| Space to Ground Antenna |
| SOZ |
| Starboard Overhead Zenith |
| SPDM |
| Special Purpose Dexterous Manipulator |
| SSCB |
| Space Station Control Board |
| SSRMS |
| Space Station Remote Manipulator System |
| TUS-RA |
| Trailing Umbilical System - Reel Assembly |
| ULC |
| Unpressurized Logistics Carrier |
| USOS |
| United States On-orbit Segment |
| UTA |
| Utility Transfer Assembly |
| WETA |
| Wireless Video System External Transceiver Assembly |
A-2
Appendix b - glossary
INCREMENT
This is a specific time period which combines different operations such as assembly, scientific research, test, logistics, maintenance, and other ISS systems and utilization operations. During the assembly phase, an increment is defined as a period supporting crew rotation. The duration of an increment is the time period starting immediately after the undocking of a Soyuz to, and including, the undocking of the next Soyuz. Postassembly complete increment boundaries are defined in the tactical planning process.
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT
The IDRD is a Program and tactical level requirements document that provides the assignment of resources, accommodations, and the requirements for flights and increment(s).
USOS
Refers to the on-orbit elements of NASA, JAXA, ESA, and CSA. The term USOS crew applies to the roles and responsibilities of astronauts representing NASA, JAXA, ESA, and CSA.
Utilization Consists of science hardware and/or activities that focus on research of astronauts health, technology development, and validation of operational practices for longduration space missions.
B-1
Appendix c - open work Table C-1 lists the specific To Be Determined (TBD) items in the document that are not yet known. The TBD is inserted as a placeholder wherever the required data is needed and is formatted in bold type within brackets. The TBD item is numbered based on the section where the first occurrence of the item is located as the first digit and a consecutive number as the second digit (i.e., <TBD 4-1> is the first undetermined item assigned in Section 4 of the document). As each TBD is solved, the updated text is inserted in each place that the TBD appears in the document and the item is removed from this table. As new TBD items are assigned, they will be added to this list in accordance with the above described numbering scheme. Original TBDs will not be renumbered.
Table C-1 TO be determined items
| TBD |
| Paragraph / Section |
| Description |
Table C-2 lists the specific To Be Resolved (TBR) issues in the document that are not yet known. The TBR is inserted as a placeholder wherever the required data is needed and is formatted in bold type within brackets. The TBR issue is numbered based on the section where the first occurrence of the issue is located as the first digit and a consecutive number as the second digit (i.e., <TBR 4-1> is the first unresolved issue assigned in Section 4 of the document). As each TBR is resolved, the updated text is inserted in each place that the TBR appears in the document and the issue is removed from this table. As new TBR issues are assigned, they will be added to this list in accordance with the above described numbering scheme. Original TBRs will not be renumbered.
table C-2 TO BE RESOLVED ISSUES
| TBR |
| Paragraph / Section |
| Description |
| 3-1 |
| Figure 3.1.2-1 |
| This TBR will be removed from the document when all work associated with SSCN 13565 “PMM Relocation and Second Docking Port at Node 1 Nadir,” is resolved. |
The forward work entails; plume impingement analysis (plume impingement VV at N1Nadir with HTV capture/departure including abort/CAM case, HTV at N2Nadir with docking vehicle capture/departure including abort/CAM case, MRM1 Soyuz departure while HTV is on N1Nadir, etc.). Clearance analysis (MRM1 Soyuz departure while HTV at N1nadir). GPS antenna blockage, multi-pass analysis (depends on the docked vehicle design). Power quality analysis for HTV at N1nadir. Establish HTV installation and EP ops timeline. Verify any ISS attitude changes will be captured in HTV spec. SRP for HTV release at N1nadir while another vehicle is at Node2nadir.
D-2
Appendix d - ISS Configuration Roadmap Table D-1 is the ISS Configuration Roadmap which is a tool to help the user identify the appropriate product/website for understanding different aspects of the ISS configuration. This table identifies common items that the ISS community regularly needs to understand/utilize as well as the products and/or websites which house the specific configuration data.
Table D-1 ISS Configuration Roadmap (PAGE 1 OF 2)
Table D-1 ISS Configuration Roadmap (PAGE 2 OF 2) image3.png image4.png image5.wmf oleObject1.bin image6.wmf image7.emf image8.emf image9.emf image10.emf image11.emf image12.emf image13.emf image14.emf image15.emf image16.emf image17.emf image18.emf image19.png image20.png image21.png image22.png image23.png image24.png image25.jpeg image26.png image27.png image28.jpeg image29.jpeg image30.png image31.png image32.png image33.png image34.emf image35.emf image36.png image37.png image38.png image39.emf image40.emf image1.png image2.png
