WWW.NASAWATCH.COM SSP 54014 Revision A Increment Definition and Requirements Document for Increment 14
International Space Station Program
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April 2006
National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract Number: NNJ04AA02C SSP 54014 WWW.NASAWATCH.COM Revision A
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
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INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
APRIL 2006
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PREFACE
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
This document is the Increment Definition and Requirements Document for Increment 14. Official delivery of this document is under control of the Space Station Control Board (SSCB). Any changes or revisions will be jointly agreed to and signed by the National Aeronautics and Space Administration (NASA) and the affected International Partners (IPs).
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NASA/ROSCOSMOS
INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
APRIL 2006
Michael T. Suffredini Alexi Krasnov National Aeronautics and Space Roscosmos Administration Director, Manned Flight Program Manager, International Space Station Program
Date Date
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NASA/CSA
INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
APRIL 2006
Michael T. Suffredini Benoit Marcotte National Aeronautics and Space CSA Program Manager Administration Manager, International Space Station Program
Date Date
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NASA/ESA
INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
APRIL 2006
Michael T. Suffredini Alan Thirkettle National Aeronautics and Space ESA Program Manager Administration Manager, International Space Station Program
Date Date
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
CONCURRENCE
APRIL 2006
Concurred by: Valeri Ryumin RSC-E ISS PROGRAM DIRECTOR ORG
SIGNATURE DATE
Developer Concurrence: Nikolai Bryukhanov RSC-E DEPUTY ISS PROGRAM DIRECTOR ORG
SIGNATURE DATE
Developer Concurrence: Igor Khamits RSC-E RUSSIAN SEGMENT INTEGRATION ORG
SIGNATURE DATE
Developer Concurrence: Mikhail Shutikov RSC-E RUSSIAN MODULES MANAGER ORG
SIGNATURE DATE
Developer Concurrence: Marina Sycheva RSC-E PLANNING AND MANIFEST MANAGER ORG
SIGNATURE DATE
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
CONCURRENCE
APRIL 2006
Concurred by: Sergey Yaroshenko RSC-E VEHICLE INTEGRATED PERFORMANCE AND ORG RESOURCES REPRESENTATIVE
SIGNATURE DATE
Developer Concurrence: Galina Kaportseva RSC-E PROGRAM MANAGER ORG
SIGNATURE DATE
Developer Concurrence: Natalya Zabolotnaya RSC-E MANIFEST AND CREW PROVISIONING ORG REPRESENTATIVE
SIGNATURE DATE
Developer Concurrence: Ludmila Chaykina RSC-E FLIGHT MECHANICS REPRESENTATIVE ORG
SIGNATURE DATE
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
CONCURRENCE
APRIL 2006
Prepared by: Lynn Hadley OC BOOK MANAGER ORG
SIGNATURE DATE
Concurred by: Melissa C. Owens OC INCREMENT 14 MANAGER ORG
SIGNATURE DATE
Concurred by: Kathy Leary OC REQUIREMENTS AND INCREMENT INTEGRATION ORG MANAGER
SIGNATURE DATE
Concurred by: Kenneth O. Todd OC MISSION INTEGRATION AND OPERATIONS OFFICE ORG MANAGER
SIGNATURE DATE
MIC DQA: Delegated Representative OH DATA MANAGEMENT ORG
SIGNATURE DATE
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INTERNATIONAL SPACE STATION PROGRAM
INCREMENT DEFINITION AND REQUIREMENTS DOCUMENT FOR INCREMENT 14
LIST OF CHANGES
APRIL 2006
All changes to paragraphs, tables, and figures in this document are shown below:
SSCB Entry Date Change Paragraph(s)
June 2006 Baseline All June 2006 Revision A All
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TABLE OF CONTENTS
PARAGRAPH PAGE
1.0 INTRODUCTION ...... 1-1 1.1 PURPOSE ...... 1-1 1.2 SCOPE...... 1-1 1.3 PRECEDENCE...... 1-2 1.4 DELEGATION OF AUTHORITY ...... 1-2 1.5 DEVIATION...... 1-2 2.0 DOCUMENTS...... 2-1 2.1 APPLICABLE DOCUMENTS ...... 2-1 2.2 REFERENCE DOCUMENTS...... 2-3 3.0 INCREMENT DEFINITION...... 3-1 3.1 INCREMENT 14 OVERVIEW ...... 3-1 3.2 INCREMENT 14 FLIGHT SUMMARY ...... 3-3 3.3 INCREMENT SUMMARY AND OBJECTIVES...... 3-5 3.4 DEVIATIONS TO THE GENERIC GROUNDRULES, REQUIREMENTS, AND CONSTRAINTS DOCUMENT...... 3-8 4.0 ON-ORBIT RESOURCE ASSUMPTIONS AND ALLOCATIONS...... 4-1 4.1 POWER BALANCE AND ALLOCATIONS...... 4-1 4.2 CREW TIME ...... 4-6 4.3 ACCOMMODATIONS ...... 4-7 4.4 COMMUNICATIONS...... 4-9 4.5 ADDITIONAL RESOURCE REQUIREMENT...... 4-10 5.0 ASCENT/DESCENT CARGO ALLOCATIONS AND MANIFEST SUMMARY...... 5-1 6.0 REQUIREMENTS...... 6-1 6.1
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6.4.2 STAGE 13S TASKS (IN DESCENDING PRIORITIZED ORDER)...... 6-7 6.4.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS ...... 6-9 6.4.4 CONTINGENCY REQUIREMENTS ...... 6-10 6.4.5 JETTISON REQUIREMENTS...... 6-11 6.4.6 GROUND SYSTEMS REQUIREMENTS...... 6-12 6.5 FLIGHT 12A.1 REQUIREMENTS...... 6-13 6.5.1
APPENDIX
A ACRONYMS AND ABBREVIATIONS ...... A-1 B GLOSSARY OF TERMS ...... B-1 C OPEN WORK...... C-1
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D TOPOLOGIES ...... D-1 E INCREMENT CONFIGURATIONS...... E-1 F
TABLE
3.2-1 INCREMENT 14 FLIGHT SUMMARY ...... 3-4 3.3-1 INCREMENT 14 SUMMARY ...... 3-5 4.1-1 POWER BALANCE AND ALLOCATIONS...... 4-2 4.2-1 CREW TIME ALLOCATIONS
FIGURE
3.1-1 INCREMENT 14 OVERVIEW ...... 3-2 D.3-1 INCREMENT 14 NODE 1 TOPOLOGY...... D-3 D.4-1 INCREMENT 14 UNITED STATES LABORATORY TOPOLOGY ...... D-4 D.5-1 INCREMENT 14 JOINT AIRLOCK TOPOLOGY...... D-5
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1.0 INTRODUCTION
1.1 PURPOSE
This document provides the assignment of flight dates, resources and accommodations, as well as defines the requirements for Increment 14 in Planning Period 6. Requirements are provided for both joint International Space Station (ISS)/mated vehicle operations and ISS-only continuous operations stages of the increment.
The schedule for products (i.e., documentation, reviews, etc.) that must be developed to support Increment 14 is found in the Common Schedule Database (CSD).
1.2 SCOPE
This document covers Increment 14, beginning with the launch of the ISS-14 Commander (CDR) and Flight Engineer (FE)-1 on Flight 13 Soyuz and ends with their departure on Flight 13 Soyuz. The ISS-14/15 FE-2 is launched on Flight 12A.1 and replaces the ISS-13/14 FE-2. Increment 14/15 FE-2 returns on Flight
This document is based on ISS Flight Program definition, as specified in SSP 54100, Increment Definition and Requirements Document Flight Program.
This document defines the capabilities and objectives of Increment 14. This document also controls the following: resource and accommodation allocations between assembly, system, and utilization; requirements and priorities for ISS execution planning; ISS manifest (SSP 540XX-XX, Increment Definition and Requirements Document for Increment X, Annex 1: Station Manifest (SSP 54013-12S, Increment Definition and Requirements Document for Increment 13, Annex 1: Station Manifest, Flight 12S (Soyuz 218); SSP 54013-22P, Increment Definition and Requirements Document for Increment 13, Annex 1: Station Manifest, Flight 22P (Progress 357)
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Increment 14, Annex 3: Imagery Requirements
1.3 PRECEDENCE
SSP 54014 will be developed in compliance with the specification documents. Deviations from the specifications are possible only as a result of specific scenarios analysis. If there are any discrepancies between this document and SSP 54100, SSP 54100 takes precedence. If there are any discrepancies between this document, SSP 50110, Multi-Increment Manifest Document, and the Consolidated Operations and Utilization Plan 2000-2004, this document shall take precedence.
The real-time time frame for a flight and its associated stage begins after the applicable Stage Operations Readiness Review (SORR) in accordance with the process in Station Program Implementation Plan (SPIP) Volume 2. The differences between the “as planned” requirements in the Increment Definition and Requirements Document (IDRD) and the “real-time” requirements will be documented in SSP 543XX, Post Increment Evaluation Report (PIER) for Increment 14
This document should be used in conjunction with SSP 50261-01, Generic Groundrules, Requirements, and Constraints Part 1: Strategic and Tactical Planning. Deviations to SSP 50261-01 for this increment are documented in Section 3.4.
1.4 DELEGATION OF AUTHORITY
The Space Station Control Board (SSCB) has formal control and approval of this document. All changes to this document will be processed in accordance with the procedures as specified in SSP 50123, Configuration Management Handbook.
1.5 DEVIATION
Any request for deviation from this document shall be made to the Space Station Program Control Board (SSPCB) in accordance with the procedures as specified in SSP 41170, Configuration Management Requirements. National Aeronautics and Space Administration (NASA) will maintain this document and process changes per these requirements. IPs should provide any recommended changes to the NASA Mission Integration and Operations Office for processing.
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2.0 DOCUMENTS
2.1 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.
DOCUMENT TITLE TYPE
SSP 50110 Multi-Increment Manifest Document Multilateral
SSP 50123 Configuration Management Handbook Multilateral
SSP 50200-02 Station Program Implementation Plan, Multilateral Volume 2: Program Planning and Manifesting
SSP 50255 Flight Mechanics - Trajectory Bilateral
SSP 50260 International Space Station Medical Operations Multilateral Requirements Document (ISS MORD)
SSP 50261-01 Generic Groundrules, Requirements, and Multilateral Constraints Part 1: Strategic and Tactical Planning
SSP 50448 Station Development Test Objective (SDTO) Multilateral Catalog
SSP 50562 ISS Program Off-Nominal Situation Plan Multilateral
SSP 54013 Increment Definition and Requirements Multilateral Document for Increment 13
SSP 54013-12S Increment Definition and Requirements Multilateral Document for Increment 13, Annex 1: Station Manifest, Flight 12S (Soyuz 218)
SSP 54013-22P Increment Definition and Requirements Multilateral
SSP 54014-13S Increment Definition and Requirements Multilateral
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SSP 54014-12A.1 Increment Definition and Requirements Multilateral
SSP 54014-23P Increment Definition and Requirements Multilateral
SSP 54014-13A Increment Definition and Requirements Multilateral
SSP 54014-24P Increment Definition and Requirements Multilateral
SSP 54014-25P Increment Definition and Requirements Multilateral
SSP 54014-ANX 2 Increment Definition and Requirements Multilateral Document for Increment 14, Annex 2: On-Orbit Maintenance Plan
SSP 54014-ANX 3 Increment Definition and Requirements Multilateral
SSP 54014-ANX 4 Increment Definition and Requirements Multilateral Document for Increment 14, Annex 4: Medical Operations and Environmental Monitoring
SSP 54014-ANX 5 Increment Definition and Requirements Multilateral
SSP 540XX Increment Definition and Requirements Multilateral
SSP 54100 Increment Definition and Requirements Multilateral Document Flight Program
SSP 543XX Post Increment Evaluation Report Increment 14 Multilateral
NSTS 21504 International Space Station-12A.1 Mission NASA Internal Integration Plan
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NSTS 21509 International Space Station-13A Mission NASA Internal Integration Plan
NAS15-10110 Contract NAS15-10110 between the National Bilateral Aeronautics and Space Administration of the United States of America and the Russian Space Agency of the Russian Federation for Supplies and Services Relating to MIR-1 and the International Space Station: Phase One and Selected Phase Two Activities
No Number Consolidated Operations and Utilization Plan Multilateral 2000-2004
2.2 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.
DOCUMENT TITLE TYPE
SSP 41000 System Specification for the International Space NASA Internal Station
SSP 41162 Segment Specification for the United States NASA Internal On-Orbit
SSP 41163 Russian Segment Specification Bilateral
SSP 41170 Configuration Management Requirements NASA Internal
SSP 50094 NASA/RSA Joint Specifications Standards Bilateral Document for the ISS Russian Segment
SSP 50478 Payload Data Library Requirements Document NASA Internal
SSP 50699-03 USOS Certification Baseline Volume III; Flight Multilateral Attitudes
SSP 543XX Post Increment Evaluation Report for Multilateral
NSTS 12820 Joint Shuttle/ISS Flight Rules Volume C Joint NASA Internal Operations
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3.0 INCREMENT DEFINITION
This section defines the Increment 14 objectives. The inclusion of objectives in this document provides ISS Program Office control of major events and emphasis during this time frame.
3.1 INCREMENT 14 OVERVIEW
Figure 3.1-1, Increment 14 Overview, provides a high level graphical overview of the increment. It contains the increment’s duration, when and where vehicles are docked to the ISS, planned crew rotations, the number of ISS crew on ISS, and the number of Shuttle and Soyuz (S) visiting crews.
The number of planned United States On-orbit Segment (USOS) and Russian Segment (RS) Extravehicular Activities (EVAs) are also shown in this figure. The two contingency EVAs specified in SSP 50261-01, Section 4.3.2.10, are not shown in this figure.
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Aug 06 Sep 06 Oct 06 Nov 06 Dec 06 Jan 07 Feb 07 Mar 07 Apr 07 May 07
Shows Crew Inc 14 CDR Inc 15 CDR, FE -1 Handover Period Inc 14 FE -1 RS Elements
EVAs RS
Visiting 12A.1
Visiting Crew Shuttle 6 6
Soyuz 1
Legend: - Assembly EVA performed by the Shuttle crew - Assembly EVA performed by the ISS crew while Shuttle docked - Assembly EVA performed by the ISS crew after Shuttle undock - Projected maintenance EVA performed by the Shuttle crew - Projected maintenance EVA performed by the ISS crew while Shuttle docked - Maintenance EVA performed by the ISS crew after Shuttle undock - Science EVAs by the Shuttle Crew - Science EVAs by the ISS crew while Shuttle docked - Science EVAs by the ISS crew after Shuttle undock - Shuttle objective EVA performed by the Shuttle Crew - Contains science EVA activities *# - Contains Shuttle objective EVA activities
FIGURE 3.1-1 INCREMENT 14 OVERVIEW
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3.2 INCREMENT 14 FLIGHT SUMMARY
Table 3.2-1, Increment Flight Summary, identifies planning data for all flights scheduled to visit the ISS or undock from the ISS during this increment.
The mission duration column lists the planned mission duration of each flight. For Shuttle flights in this column, two numbers are listed: 1. The nominal mission duration. 2. Additional contingency days available to accomplish ISS mission objectives (to cover docking problems, mated operations delays, (EVA), etc.). The docked duration column lists the planned docked duration for each flight. Duration calculations are based on the calendar day difference between events.
All planning docking altitudes presented in this document represent average altitudes unless stated otherwise. Altitudes are defined in accordance with SSP 50255, Flight Mechanics - Trajectory.
For those Shuttle missions identified to be performance critical, the docking altitudes are to be maximum apogee altitude limits. ISS Flight Mechanics will coordinate with Shuttle Flight Design at the start of each increment design cycle to identify performance-critical missions. Modifications to the altitude strategy will be made in the final increment product cycle.
All launch dates in Table 3.2-1 are shown in the time standard selected by the launch vehicle organization. Space Shuttle Program dates correspond to the Kennedy Space Center (KSC) time zone. Russian dates correspond to the Decreed Moscow Time (DMT) zone. Automated Transfer Vehicle (ATV) dates correspond to the Kourou time zone.
Soyuz ascent crew size is denoted in the “Launch Vehicle Crew Size” column in Table 3.2-1, using the following convention: x+y, where x=number of Expedition crew members and y=number of Soyuz crew members. Soyuz descent crew size will be identified with a table note when it differs from ascent crew size.
Shuttle ascent crew size is denoted in the “Launch Vehicle Crew Size” column in Table 3.2-1, using the following convention: w+z, where w=number of Shuttle Transportation System (STS) crew members and z=number of Expedition crew members. Shuttle descent crew size will be identified with a table note when it differs from ascent crew size.
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TABLE 3.2-1 INCREMENT 14 FLIGHT SUMMARY
ISS Launch Launch Planned Mission Shuttle Planned Docked Planned Flight Vehicle Flight Vehicle Crew Duration Docking Duration Undock Date Launch Docking Name Name Size (days) Altitude (days) Date Date (km/nmi) 12S Soyuz-TMA 2+1 [1] 178 - [1] 176 24 Sept 06
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3.3 INCREMENT SUMMARY AND OBJECTIVES
The increment definitions and primary objectives for assembly, system, and utilization operations are provided in Table 3.3-1, Increment 14 Summary. The Multilateral Crew Operations Panel (MCOP) defines crew assignments and respective agencies.
TABLE 3.3-1 INCREMENT 14 SUMMARY (PAGE 1 OF 3)
Increment Start Flight 13S (CDR/FE-1) Launch (14 Sept 06)
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TABLE 3.3-1 INCREMENT 14 SUMMARY (PAGE 2 OF 3)
Flight 12A.1 Assembly/System • Rotate departing Inc 13/14 FE-2 with arriving Inc 14/15 ISS FE-2 Objectives • Install ITS P5 on ITS P4 • Perform ISS power reconfiguration • Retract P6 (Channel 4B) Port Solar Array • R&R ETVCG at CP3 S1 Lower/Outboard • Transfer SMDP to PMA-3 Flight 12A.1 Utilization NASA: Objectives Perform Operations to support the following SDBIs and Sorties:
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TABLE 3.3-1 INCREMENT 14 SUMMARY (PAGE 3 OF 3)
Flight 13A Utilization Objectives NASA: Perform Operations to support the following SDBIs and Sorties:
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3.4 DEVIATIONS TO THE GENERIC GROUNDRULES, REQUIREMENTS, AND CONSTRAINTS DOCUMENT
No deviations to SSP 50261-01 have been identified for Increment 14.
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4.0 ON-ORBIT RESOURCE ASSUMPTIONS AND ALLOCATIONS
This section defines the allocation of the on-orbit ISS capabilities. Allocations are limited to power, crew time, on-orbit accommodations, communications coverage and datalink rates between system and utilization across the Increment. Any non-standard requirements of resources are also provided in Section 4.5. The allocation guidelines are baselined in SSP 50261-01. All data contained in this section represent operational requirements.
4.1 POWER BALANCE AND ALLOCATIONS
Table 4.1-1, Power Balance and Allocations, summarizes ISS power capability and allocations for each flight/stage in the increment. Allocations are representative, and are based on assumed operational mode and the Flight Attitude Plan included in this table. The Flight Attitude Plan was chosen from the attitude envelopes defined in SSP 50699-03, USOS Certification Baseline Volume III; Flight Attitudes, and is the operational plan to meet the energy balance requirement and optimize power availability for Utilization. This plan does not contain attitudes used for waste-water dumps, proximity operations, stage EVAs, etc. Deviations from planned attitudes and power transfers will be reviewed by the ISS Program, the Operations community, and all affected parties, and will be documented in their respective increment Flight Rules. All calculations in this table represent power availability while the station is in eclipse.
The solar beta angle ranges and attitude symbols also correspond to those defined in SSP 50699-03.
Table 4.1-1 also shows power transfer in kilowatts (kW) between the RS, Functional Cargo Block (FGB), and USOS for the Flight Attitude Plan specified. All values are from the input side of the American-to-Russian Converter Units (ARCUs) at their saturation point. Power transfer allocation values are based on Russian core systems power deficit. However, due to power architecture design constraints in the RS, numbers are shown in ARCU incremental values. USOS may consider cycling the ARCUs to recover power transfer above allocation if needed, and the RS will be notified in advance when cycling will be executed. Power transfers will be updated to meet minimum system power requirements as needed. A negative transfer power number represents a transfer in the opposite direction. For analysis purposes, the FGB is considered to be separate from the RS.
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TABLE 4.1-1 POWER BALANCE AND ALLOCATIONS (PAGE 1 OF 3)
Flight/Stage Power Availability Power Consumption Flight Attitude Power Transfer Power Margin (kW) (kW) Plan (kW) (kW) Total Capability Allocation to Allocation to Allocation to [1] Systems Systems Utilization [2] [2] [3] Increment 14
USOS L M H L M H L M H L M H L M H [4] [4] [4]
R Sz 13S 20.0 22.0 22.0 12.4 13.6 13.6 V Y Y 7.2 5.4 5.4 0.4 3.0 3.0 S 13S [5] 20.0 22.0 22.0 12.4 13.6 13.6 V Y Y 5.4 3.6 3.6 2.2 4.8 4.8 S 13S [6] 20.0 22.0 22.0 12.4 13.6 13.6 V Y Y 5.4 3.6 3.6 2.2 4.8 4.8 F 12A.1 21.0 21.0 N/A 14.6 13.8 N/A V V N/A 5.4 3.6 N/A 1.0 3.6 N/A [6] [8] [14] [7] [7] [7] [7] [7] F 12A.1 post 30.9 31.5 N/A 20.8 20.0 N/A V V N/A 5.4 3.6 N/A 4.7 7.9 N/A [6] [9] [14] [7] [7] [7] [7] [7] F 12A.1 21.0 21.0 N/A 14.6 13.8 N/A V V N/A 5.4 3.6 N/A 1.0 3.6 N/A [5] [8] [14] [7] [7] [7] [7] [7] F 12A.1 post 30.9 31.5 N/A 20.8 20.0 N/A V V N/A 5.4 3.6 N/A 4.7 7.9 N/A [5] [9] [14] [7] [7] [7] [7] [7] S 12A.1 30.9 29.0 31.8 18.9 19.6 18.7 V V V 5.4 5.4 8.7 6.6 4.0 4.4 [6] [11] [14] S 12A.1 30.9 29.0 31.8 16.6 17.3 16.4 V V V 5.4 5.4 8.7 8.9 6.3 6.7 [6] [12] [14] S 12A.1 30.9 29.0 24.0 14.3 15.0 14.1 V V V 5.4 5.4 8.7 11.2 8.6 1.2 [6] [13] [14] S 12A.1 30.9 29.0 31.8 18.9 19.6 18.7 V V V 5.4 5.4 8.7 6.6 4.0 4.4 [5] [11] [14] S 12A.1 30.9 29.0 31.8 16.6 17.3 16.4 V V V 5.4 5.4 8.7 8.9 6.3 6.7 [5] [12] [14] S 12A.1 30.9 29.0 24.0 14.3 15.0 14.1 V V V 5.4 5.4 8.7 11.2 8.6 1.2 [5] [13] [14] F 13A 30.7 31.5 N/A 17.7 17.7 N/A V V N/A 5.4 5.4 N/A 7.6 8.4 N/A [6] [15] [7] [7] [7] [7] [7] F 13A 41.7 42.0 N/A 18.2 18.2 N/A V V N/A 5.4 5.4 N/A 18.1 18.4 N/A [6] [16] [7] [7] [7] [7] [7] S 13A 40.9 42.0 42.0 15.5 15.6 15.6 V V V 7.1 7.1 8.9 18.3 19.3 17.5 [6] S 13A 40.9 42.0 42.0 15.5 15.6 15.6 V V V 7.1 7.1 8.9 18.3 19.3 17.5 [5] R Sz 14S 40.9 42.0 42.0 15.5 15.6 15.6 V V V 8.9 8.9 8.9 16.5 17.5 17.5
FGB L M H L M H L M H L M H L M H [4] [4] [4]
R Sz 13S 1.7 3.3 3.0 1.5 1.5 1.5 V Y Y 0.0 0.0 0.0 0.2 1.8 1.5 S 13S 1.7 3.3 3.0 1.5 1.5 1.5 V Y Y 0.0 0.0 0.0 0.2 1.8 1.5 [5]
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TABLE 4.1-1 POWER BALANCE AND ALLOCATIONS (PAGE 2 OF 3)
Flight/Stage Power Availability Power Consumption Flight Attitude Power Transfer Power Margin (kW) (kW) Plan (kW) (kW) Total Capability Allocation to Allocation to Allocation to [1] Systems Systems Utilization [2] [2] [3] Increment 14
FGB L M H L M H L M H L M H L M H [4] [4] [4]
S 13S 1.7 3.3 3.0 1.5 1.5 1.5 V Y Y 0.0 0.0 0.0 0.2 1.8 1.5 [6] F 12A.1 1.7 1.7 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.2 N/A [6] [8] [7] [7] [7] [7] [7] F 12A.1 post 1.7 1.7 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.2 N/A [6] [9] [7] [7] [7] [7] [7] F 12A.1 1.7 1.7 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.2 N/A [5] [8] [7] [7] [7] [7] [7] F 12A.1 post 1.7 1.7 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.2 N/A [5] [9] [7] [7] [7] [7] [7] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [6] [11] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [6] [12] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [6] [13] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [5] [11] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [5] [12] S 12A.1 1.7 1.5 0.9 1.5 1.5 1.5 V V V 0.0 0.0 -1.5 0.2 0.0 0.7 [5] [13] F 13A 1.7 1.5 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.0 N/A [6] [15] [7] [7] [7] [7] [7] F 13A 1.7 1.5 N/A 1.5 1.5 N/A V V N/A 0.0 0.0 N/A 0.2 0.0 N/A [6] [16] [7] [7] [7] [7] [7] S 13A 0.0 0.0 0.0 1.4 1.4 1.4 V V V -1.7 -1.7 -1.7 0.0 0.0 0.0 [6] S 13A 0.0 0.0 0.0 1.4 1.4 1.4 V V V -1.7 -1.7 -1.7 0.0 0.0 0.0 [5] R Sz 14S 0.0 0.0 0.0 1.4 1.4 1.4 V V V -1.7 -1.7 -1.7 0.0 0.0 0.0
RS [10] L M H L M H L M H L M H L M H [4] [4] [4]
R Sz 13S 6.4 6.4 6.4 V -7.2 -5.4 -5.4 1.4 0.7 1.2 [18] 1.8 2.6 3.1 Y Y S 13S 5.1 5.1 5.1 V -5.4 -3.6 -3.6 1.2 0.5 1.0 [5] [18] 1.8 2.6 3.1 Y Y
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TABLE 4.1-1 POWER BALANCE AND ALLOCATIONS (PAGE 3 OF 3)
Flight/Stage Power Availability Power Consumption Flight Attitude Power Transfer Power Margin (kW) (kW) Plan (kW) (kW) Total Capability Allocation to Allocation to Allocation to [1] Systems Systems Utilization [2] [2] [3] Increment 14
RS [10] L M H L M H L M H L M H L M H [4] [4] [4]
S 13S 1.8 2.6 3.1 5.4 5.4 5.4 V -5.4 -3.6 -3.6 0.9 0.2 0.7 [6] [18] Y Y F 12A.1 1.8 2.6 N/A 5.4 5.4 N/A V V N/A -5.4 -3.6 N/A 0.9 0.2 N/A [6] [8] [17] [7] [7] [7] [7] [7] F 12A.1 post 1.8 2.6 N/A 5.4 5.4 N/A V V N/A -5.4 -3.6 N/A 0.9 0.2 N/A [6] [9] [17] [7] [7] [7] [7] [7] F 12A.1 1.8 2.6 N/A 5.1 5.1 N/A V V N/A -5.4 -3.6 N/A 1.2 0.5 N/A [5] [8] [17] [7] [7] [7] [7] [7] F 12A.1 post 1.8 2.6 N/A 5.1 5.1 N/A V V N/A -5.4 -3.6 N/A 1.2 0.5 N/A [5] [9] [17] [7] [7] [7] [7] [7] S 12A.1 1.8 1.3 0.4 5.4 5.4 5.4 V V V -5.4 -5.4 -7.2 0.9 0.4 1.0 [6] [11] [19] S 12A.1 1.8 1.3 0.4 5.4 5.4 5.4 V V V -5.4 -5.4 -7.2 0.9 0.4 1.0 [6] [12] [19] S 12A.1 1.8 1.3 0.4 5.4 5.4 5.4 V V V -5.4 -5.4 -7.2 0.9 0.4 1.0 [6] [13] [19] S 12A.1 1.8 1.3 0.4 5.1 5.1 5.1 V V V -5.4 -5.4 -7.2 1.2 0.7 1.3 [5] [11] [19] S 12A.1 1.8 1.3 0.4 5.1 5.1 5.1 V V V -5.4 -5.4 -7.2 1.2 0.7 1.3 [5] [12] [19] S 12A.1 1.8 1.3 0.4 5.1 5.1 5.1 V V V -5.4 -5.4 -7.2 1.2 0.7 1.3 [5] [13] [19] F 13A 1.8 1.3 N/A 5.4 5.4 N/A V V N/A -5.4 -5.4 N/A 0.9 0.4 N/A [6] [15] [19] [7] [7] [7] [7] [7] F 13A 1.8 1.3 N/A 5.4 5.4 N/A V V N/A -5.4 -5.4 N/A 0.9 0.4 N/A [6] [16] [19] [7] [7] [7] [7] [7] S 13A 1.8 1.3 0.4 5.4 5.4 5.4 V V V -5.4 -5.4 -7.2 0.9 0.4 1.0 [6] [19] S 13A 1.8 1.3 0.4 5.1 5.1 5.1 V V V -5.4 -5.4 -7.2 1.2 0.7 1.3 [5] [19] R Sz 14S 1.8 1.3 0.4 6.4 6.4 6.4 V V V -7.2 -7.2 -7.2 1.4 0.9 0.0 [19] NOTES: [1] Power Availability limited by rules governing BCDU power output. This limits each channel to 11 kW available before 12A.1, and 10.5 kW following F 12A.1. [2] Includes power required for assembly and system tasks. [3] Utilization Allocations to each IP based on NASA: 100 percent of USOS power, Rosaviakosmos: 100 percent of RS power. [4] Low Beta is defined as ≤ 37 degrees, Mid Beta is defined between 37 and 52 degrees, High Beta is defined as >52 degrees. [5] 1 Progress attached to RSOS. [6] 2 Progress attached to RSOS.
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[7] Shuttle mated flight ops are constrained to solar beta angles of less than 60 degrees. [8] Pre MBSU Reconfig. [9] Post MBSU Reconfig. [10] RS Loads and Power Generation values provided by S. Yaroshenko. [11] 12A.1 Stage pre heat exchanger reconfiguration. [12] 12A.1 Stage with 1 heat exchanger reconfiguration. [13] 12A.1 Stage with 2 heat exchanger reconfiguration. [14] Power availability and Power Consumption numbers are from WPRR 204 time phased analysis. [15] Pre S4 deployment. [16] Post 2B retraction (S4 arrays 1A and 3A deployed). [17] XVV Z Nadir with 40 degree roll provided by S. Yaroshenko. [18] XVV Z Nadir with (0,0,0) data provided by S. Yaroshenko. [19] SM arrays are parked in the vertical position; data provided by S. Yaroshenko.
Legend L Low beta angle range LTA Launch To Activation R Sz Soyuz rotation
M Mid beta angle range F Flight V XVV flight attitude
H High beta angle range S Stage P XPOP flight attitude
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4.2 CREW TIME
Table 4.2-1, Crew Time Allocations
TABLE 4.2-1 CREW TIME ALLOCATIONS
Crew Time (hours) ISS 14 NASA Roscosmos Total Total Capability [1] 1953 Systems Requirements [2] [3] 862 977 1839 Amount Subscribed 897 1029 1926 [4] [5]
Total Allocation to Utilization [6] [7] 76 76 152 [8] [8] [8]
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4.3 ACCOMMODATIONS
Table 4.3-1, On-Orbit Accommodation Allocations (Pressurized), shows the pressurized on-orbit accommodation allocations for the Increment and when the on-orbit internal configuration changes. The unit of measure is Rack Volume Equivalents (RVEs). Russian accommodations are not shown since they are not allocated to the other Partners.
TABLE 4.3-1 ON-ORBIT ACCOMMODATION ALLOCATIONS (PRESSURIZED) (PAGE 1 OF 2)
Rack Volume Equivalents [1] ISS 14 13S-12A.1 12A.1-13A 13A-14S Total Capability (RVE) 43.7 43.7 43.7 Node 1 4 4 4 US Lab 24 24 24 Airlock 4 4 4 FGB 11.7 11.7 11.7 NASA Allocation to System Node 1 4 4 4 US Lab [2] 12 12 12 Airlock 4 4 4 FGB 10.9 10.9 10.9 NASA Allocation to Utilization Node 1 0 0 0 US Lab [3] 12 12 12 Airlock 0 0 0 FGB 0 0 0 Total Amount subscribed [3] 9+1.5 9+1.5 9+1.5 Remaining available 1.5 [5] 1.5 [5] 1.5 [5]
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TABLE 4.3-1 ON-ORBIT ACCOMMODATION ALLOCATIONS (PRESSURIZED) (PAGE 2 OF 2)
Rack Volume Equivalents [1] ISS 14 13S-12A.1 12A.1-13A 13A-14S Roscosmos Allocation 0 0 0 Node 1 0 0 0 US Lab 0 0 0 Airlock 0 0 0 FGB [4] 0.8 0.8 0.8 NOTES: [1] RVEs can be equated to rack locations in Node 1, US Lab, and Airlock. The FGB has 11.7 m3 of stowage volume before installation of new stowage enclosures, which is approximately equal to 11.7 RVEs. [2] During Increment 14, System will use one of the rack locations in the US Lab allocated to Utilization for pre-positioning of assembly and maintenance hardware. Thirteen rack locations in the US Lab will be allocated to utilization at AC. [3] Utilization items belonging to the Utilization passive stowage RVE allocation might not be physically stowed in the US Lab. [4] Includes 0.8 m3 for stowage provided by FGB enclosures per January 2003 protocol (Ref. OC-03-003). [5] One unsubscribed RVE is positioned in front of Lab window.
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4.4 COMMUNICATIONS
Table 4.4-1, On-Orbit Communications Coverage and Datalink Rates, shows communication coverage and datalink rates allocations among communications systems for each flight/stage in the Increment. USOS times represent the average time that the communication link is not blocked when the Tracking and Data Relay Satellite (TDRS) is above the horizon. RS times represent the time that the communication link is not blocked when the satellite is above the horizon when working with the Lira system, and the average time when there is an uninterrupted link within the visibility zone of the ground antennas. Communication from the RS can occur via the satellite or via direct to the ground. RS-to-ground communication may be conducted via satellite (provided a relay satellite is available). Coverage via direct communication to the ground is expected for up to nine passes every day. The coverage duration for each pass depends on the number of ground antenna within the line of sight of the ISS (approximately 10 minutes per ground antenna). Access for United States (U.S.) communications through Russian link is confined to payload commands, system telemetry, system commands, and audio. The same capability is also available for the RS through the U.S. link. This capability is to be used in a backup situation only.
TABLE 4.4-1 ON-ORBIT COMMUNICATIONS COVERAGE AND DATALINK RATES
Segment USOS RS System Ku-Band Downlink S-Band Uplink Russian Downlink Stage/Flight Communications Allocations (Mbps) Communications Allocations (Mbps) Configuration Coverage Capability/Systems/ Coverage Percent Capability/Systems/ Percent Utilization (Low/Medium/High) Utilization (Low/Medium/High) Increment 14 Flight 13S
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4.5 ADDITIONAL RESOURCE REQUIREMENT
Table 4.5-1, Additional Resource Requirement, provides the tactical agreements on using non-standard requirements of on-orbit resources (i.e. consumables: water, Oxygen (O2), Nitrogen (N2), propellant, etc.) that is not specified in Sections 4.1 - 4.4.
Table 4.5-1 provides the total amount of a resource needed for a specific increment or stage. When the resource is used on-orbit, the resource may be recovered back into resource or emitted in the ISS environment. If the requirement has a closed-loop system, then, the percentage recovered and emitted is not applicable.
TABLE 4.5-1 ADDITIONAL RESOURCE REQUIREMENT
Total Amount Resource of Usage Increment 14 Russian None Defined None Defined U.S. S 13S Water 2400 ml S 12A.1 Water 4800 ml S 13A Water 4800 ml
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5.0 ASCENT/DESCENT CARGO ALLOCATIONS AND MANIFEST SUMMARY
Table 5.0-1, Ascent/Descent Allocations and Manifest Summary, contains the cargo delivery and return allocations, and the manifest summary for each flight in the Increment. The table includes major cargo to the rack or Orbital Replacement Unit (ORU) level. This table controls program-level allocations. Detailed ISS manifest items are documented in the appropriate SSP 54014-XX. The cargo allocations are for the Partner that provides the transportation vehicle unless stated otherwise.
The allocations are based on the Consolidated Operations and Utilization Plan 2000-2004, and then refined based on current capability and ISS requirements. Volume data shown is for pressurized stowage areas only and is listed as rack locations for full racks in the Multi-Purpose Logistics Module (MPLM), Middeck Locker Equivalents (MLEs) for stowage on the middeck, and Cargo Transfer Bag Equivalents (CTBEs) for passive stowage in the MPLM and SpaceHab, and RVEs for ATV. The maintenance allocation includes pre-positioned spares and planned maintenance equipment. It does not include items that are considered urgent need spares. Water transfer listed under allocations represents the transfer target for Shuttle water generated on-orbit that is transferred to the ISS. Water transfer listed under Progress vehicles is water transported up in a Progress.
All allocations need to include packing factor and trash. Each owner is responsible for including packing factor and trash.
Soyuz Transport Modified Anthropometric (TMA) vehicles provide transportation for the Soyuz crew, Expedition crew rotation and will provide the capability for ISS crew rescue return (up to three). The Soyuz TMA has minimal capability to deliver cargo.
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TABLE 5.0-1 ASCENT/DESCENT ALLOCATIONS AND MANIFEST SUMMARY (PAGE 1 OF 4)
Flight Manifest Item Category Mass (kg/lb) Volume 12 Soyuz DESCENT
STS O2 for EVA prebreathe 8/16
O2 transfer to ISS Airlock HPGTs 0/0
N2 transfer to ISS Airlock HPGTs 25/55
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TABLE 5.0-1 ASCENT/DESCENT ALLOCATIONS AND MANIFEST SUMMARY (PAGE 2 OF 4)
Flight Manifest Item Category Mass (kg/lb) Volume 12A.1 (cont.) DESCENT Manifest Summary SPACEHAB Single Cargo Module ICC: STP-H2 Middeck ISS content Shuttle Integration H/W Allocations Russian
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TABLE 5.0-1 ASCENT/DESCENT ALLOCATIONS AND MANIFEST SUMMARY (PAGE 3 OF 4)
Flight Manifest Item Category Mass (kg/lb) Volume 13A ASCENT
STS O2 for EVA prebreathe 8/17.6
O2 transfer to ISS Airlock HPGTs 34.1/75
N2 transfer to ISS Airlock HPGTs 0.0/0.0 Water Transfer to ISS
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TABLE 5.0-1 ASCENT/DESCENT ALLOCATIONS AND MANIFEST SUMMARY (PAGE 4 OF 4)
Flight Manifest Item Category Mass (kg/lb) Volume 24P DESCENT
Table 5.0-1A, Ascent/On-Orbit/Descent Power Allocation for Utilization (Watts), contains power availability for each flight in the increment.
TABLE 5.0-1A ASCENT/ON-ORBIT/DESCENT POWER ALLOCATION FOR UTILIZATION (WATTS)
Flight Ascent On-Orbit Descent 13S 0 0 0 12A.1
Table 5.0-2, Ascent/Descent Utilization Manifest Summary
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TABLE 5.0-2 ASCENT/DESCENT UTILIZATION MANIFEST SUMMARY
Flight Manifest Item Category Mass (kg/lb) Volume 13S ASCENT
Middeck (Items not requiring a locker) Spacehab Payload Bay
Candidates N/A Total (Mass and volume numbers include a calculated packing factor that may not reflect actual packing efficiencies.) DESCENT Middeck N/A Middeck (Items not requiring a locker location) Spacehab (SHLR) Cargo Bay Candidates N/A Total (Mass and volume numbers include a calculated packing factor that may not reflect actual packing efficiencies.) 23P ASCENT
Total Total with candidates
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TABLE 5.0-2 ASCENT/DESCENT UTILIZATION MANIFEST SUMMARY
Flight Manifest Item Category Mass (kg/lb) Volume 13A ASCENT
Middeck (Items not requiring a locker) Candidates N/A Total (Mass and volume numbers include a calculated packing factor that may not reflect actual packing efficiencies.) DESCENT Middeck N/A Middeck (Items not requiring a locker) Candidates N/A Total (Mass and volume numbers include a calculated packing factor that may not reflect actual packing efficiencies.) 24P ASCENT
Total Total with candidates 25P ASCENT
Total Total with candidates
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6.0 REQUIREMENTS
This section defines all of the unique Programmatic requirements for the increment’s flights and stage intervals necessary to ensure successful completion of planned assembly, maintenance, operations, and utilization of the ISS during increment. Generic requirements and constraints are documented in SSP 50261-01.
6.1
6.2 INCREMENT 14 SPECIFIC REQUIREMENTS
This section identifies requirements applicable during Increment 14. Detailed requirements and agreements between ISS Program and the Payload Developers (PDs) for payloads identified in Table 5.0-2 are specified in SSP 54014-ANX 5.
6.2.1 RUSSIAN UTILIZATION EXPERIMENTS
Russian science experiments to be conducted during Increment 14 shall consist of the following:
EXPERIMENT CODE EXPERIMENT NAME KHT-1 GTS KHT-20 GCF-JAXA KHT-29 ROKVISS ___-32 JAXA 3DPC ___-7 SVS (___) ___-9 Kristallizator (Crystallizer) ___-1 Relaksatsiya ___-8 Uragan ___-16 Vsplesk (Burst) ___-5 Kardio-ODNT ___-8 Profilaktika ___-9 Pulse ___-15 Pilot ___-2 Biorisk ___-4 Aquarium ___-5 Rasteniya-2 ___-10 Mezhkletochnoe vzaimodeistvie (Intercellular interaction) ___-11 Statoconia
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___-12 Regeneratciya (Regeneration) ___-1 Prognoz ___-3 Matryeshka-R ___-2 Diatomea ___-11 Volny (Waves) ___-1 Glikoproteid ___-2 Mimetik-K ___-3 KAF ___-4 Vaktsina-K (Vaccine) ___-8 Biotrek ___-20 Interleukin-K ___-10 Kon’yugatsiya (Conjugation) ___-11 Biodegradatsiya ___-12 Bioekologiya (Bioecology) ___-31 Antigen ___-5 (SDTO 16002-R) Meteoroid ___-14 (SDTO 12002-R) Vektor-T ___-15 (SDTO 13002-R) Izgib ___-20 Plazmennyi Kristall (Plasma Crystal) ___-22 (SDTO 13001-R) Identifikatsiya ___-25 Scorpion ___-44 Sreda (Environment) ___-45 Infotekh ___-3 Econ ___-6 Plazma-MKS (Plasma-ISS) ___-2_ BTN-Neutron
6.2.2 VISITING CREW UTILIZATION
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6.3 FLIGHT 13S REQUIREMENTS This section identifies ISS requirements during Flight 13S. 6.3.1
6.3.2 FLIGHT 13S TASKS (IN DESCENDING PRIORITIZED ORDER)
These tasks, listed in order of ISS Program priority, are to be executed during this flight. The order of execution for these tasks in the nominal plan may vary, depending on timeline efficiencies. The Flight 13S Off-Nominal Situation (ONS) Plan (in Appendix J
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D. Conduct transfer activities. 1) Soyuz Unloading. 2) Equipment return. E. Conduct Communications. 1) Russian Mission Control Center (Soyuz and ISS). 2) Sessions using the Sputnik-Service Module (SM) ham radio. F. Conduct Soyuz systems maintenance. G. Conduct Soyuz handover. H. Conduct RS crew life support activities onboard the ISS. I. Conduct emergency evacuation walkthrough. 9. Perform USOS/Russian payload research operations tasks. [IVA] A. Mandatory daily maintenance for powered payloads. B. Daily scheduled payload operations and data capture. 10. Perform additional 4 hours per rotating crewmember of ISS crew handover (16 hours per crewmember total). [IVA] 11. Transfer remaining items from 13S TMA to ISS. [IVA] 12. Complete 12A cleanup/unpack of U.S. Items. [IVA] 13. Perform SDTO 13004-U, Russian Vehicle Docking/Undocking Loads on ISS, for 12S undocking from FGB nadir port (ISS Wireless Instrumentation System (IWIS) required). [IVA] [Ground] 14. Perform SDTO 14001-U,Solar Array Shunt Test (if not performed in previous stage).
6.3.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS
6.3.3.1 Flight 13 Soyuz TMA shall dock to the SM Aft port. [ATT]
6.3.3.2 Flight 12 Soyuz TMA shall undock from FGB Nadir port. [ATT]
6.3.3.3 The ISS shall be in Control Moment Gyroscope (CMG) control with all thrusters inhibited for the following activities:
None identified.
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6.3.3.4 The ISS shall be in a free drift configuration with the CMGs not controlling and with all thrusters inhibited for the following activities:
None identified.
6.3.4 CONTINGENCY REQUIREMENTS
6.3.4.1 Mission Control Center - Houston (MCC-H) and Mission Control Center - Moscow (MCC-M) shall build procedures, contingency timelines, and conduct training for the following non-EVA tasks (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning until the contingency is invoked.): A. USOS and/or RS critical maintenance tasks as follows:
None Identified.
6.3.4.2 MCC-H and MCC-M shall build procedures, contingency timelines, and provide pre-flight training for the EVA tasks to sufficient maturity to provide for the EVA response times designated. A. Class 1: All procedures, timelines and training are developed and certified to support an EVA response within 24 hours. None Identified. B. Class 2: For contingencies occurring during the docked timeframe an EVA response is available on a subsequent EVA based on re-prioritization of the mission tasks. Published procedures and timelines are developed, but may require real time updates to match the flight specific failure. None identified. C. Class 3: For contingencies related to first flights hardware that are not time critical, skeleton EVA procedures will be developed preflight to support a Class 3 EVA. The EVA response time can be greater than two weeks and can be deferred to the stage or next available mission. The ISS Program has determined that additional resources will not be applied to further refine the training and integrated planning until the failure occurs. Subsequent flight listings for these hardware items will be contained in the Generic Groundrules, Requirements, and Constraints (GGR&C). None Identified.
6.3.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of
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6.3.5.1 Planned Jettison
The following items are planned for jettison during EVA in this flight/stage: A. U.S.:
None Identified. B. Russian:
None Identified.
6.3.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew. A. U.S.:
None Identified. B. Russian:
None Identified.
6.3.6 GROUND SYSTEMS REQUIREMENTS
A. Ground support is required to operate Space Acceleration Measurement System (SAMS)-II, Structural Dynamic Measurement System (SDMS), and Microgravity Acceleration Measurement System (MAMS) sensors for SDTO 13004-U. (SAMS and MAMS availability will be assessed real time.) B. Ground support is desired to operate Russian ALO for SDTO during the 12S undock for SDTO 13004-U.
6.3.7 ISS REQUIREMENTS ON SHUTTLE DURING NONDOCKED TIME FRAME Not applicable.
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6.4 FLIGHT 12S UNDOCK TO FLIGHT 12A.1 DOCK REQUIREMENTS (STAGE 13S)
This section identifies ISS requirements applicable from Flight 12 Soyuz undock to Flight 12A.1 dock, including requirements associated with 23 Progress-M dock, 22 Progress-M undock, 24 Progress-M dock and Flight 13 Soyuz TMA relocation.
6.4.1
6.4.2 STAGE 13S TASKS (IN DESCENDING PRIORITIZED ORDER)
These tasks, listed in order of ISS Program priority, are to be executed during this stage. The order of execution for these tasks in the nominal plan may vary depending on timeline efficiencies. An ONS plan (see Appendix J
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10. Perform checkout and preparation tasks for Flight 12A.1. [IVA] A. Position Mobile Transporter (MT) at workstation (WS) #8. B. Perform Mobile Servicing System (MSS) pre-launch checkout for Flight 12A.1. [Robotics] [Ground] C. P5 Install Dry-Run using Space Station Remote Manipulator System (SSRMS) or Robotic On-Board Trainer (ROBoT). [Robotics] D. Unstow and configure Joint Airlock. E. Configure and checkout Extravehicular Mobility Unit (EMU) and EVA equipment. F. Perform pre-pack for 12A.1 return items and tool preparation. G. Flight plan and EVA timeline reviews. H. Retrieve Y-jumper from Z1 dome. I. Additional Robotics Refresher (included in OBT) using SSRMS or ROBoT. [Robotics] J. Perform the second survey and verify the status of the P6 4B Solar Array Wing (SAW) using SSRMS (first survey performed during Stage 12A). [Robotics] [Imagery] K. Reconfigure Station Support Computer (SSC) File server power source in preparation for 12A.1.
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15. Perform Orlan-based EVA#17. [EVA] [Imagery] [ATT] A. Install Splash experiment Hardware.
6.4.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS
6.4.3.1 The ISS shall be in CMG control without ISS thrusters firing for the following activities:
None identified.
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6.4.3.2 The ISS shall be in free drift configuration with the CMGs not controlling and without ISS thrusters firing for the following activities:
None identified.
6.4.3.3 The 23 Progress-M shall dock to the SM aft port.
6.4.3.4 The 22 Progress-M shall undock from the DC 1 Nadir port.
6.4.3.5 The 24 Progress-M shall dock to the DC 1 Nadir port.
6.4.4 CONTINGENCY REQUIREMENTS
6.4.4.1 MCC-H and MCC-M shall build procedures, contingency timelines, and conduct training to allow the crew to perform the following non-EVA tasks (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning until the contingency is invoked.): A. USOS and/or RS critical maintenance tasks as follows:
None identified. B. Complete critical unfinished Flight 13 Soyuz assembly tasks as follows:
None identified. C. Remove/replace critical spares as follows:
None identified.
6.4.4.2 MCC-H and MCC-M shall build task specific procedures, contingency timelines, and conduct training to a high level sufficient to meet the following objectives:
• Identify task specific technical and safety issues.
• Identify on-board equipment required to perform the task.
• Determine the scope of effort required to prepare for the specific configurations, locations, and environmental conditions for the EVA.
• Provide the crew with the proper skill set required to perform the tasks given the on-board proficiency training assets available.
The readiness of these tasks will be based upon the generic development of the task procedures and timelines to a level that can be validated against a set of criteria. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to
6-10 SSP 54014 WWW.NASAWATCH.COM Revision A Stage 13S develop products/planning and the feasibility to perform those tasks on this flight/increment will be undetermined until the contingency is invoked. A. USOS and/or RS critical maintenance tasks as follows:
8. Fluid Line Anchor Patch (FLAP) installation (subset of Ammonia (NH3) Leak Detection/Isolation Requirement documented in SSP 50261-01 update and 11A Flight Rules)
None identified.
6.4.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of recontact with ISS and of damage or injury following re-entry, procedures and training for the crew including worksite identification and desired jettison direction and velocity, and related hazard assessments.
6.4.5.1 Planned Jettison
The following items are planned for jettison during EVA in this flight/stage: A. U.S.: None Identified.
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B. Russian: None Identified.
6.4.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew. A. U.S.:
None Identified. B. Russian:
None Identified.
6.4.6 GROUND SYSTEMS REQUIREMENTS
A. Ground Support is required to operate SDMS, IWIS and External Wireless Instrumentation System (EWIS) for SDTOs 13004-U and 13005-U. B. Ground support is highly desired to operate SAMS-II, MAMS and Russian ALO sensors for SDTOs 13004-U and 13005-U. (SAMS and MAMS availability will be assessed real time.) C. Ground support is required to perform SSRMS/MBS prelaunch checkout.
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6.5 FLIGHT 12A.1 REQUIREMENTS
This section identifies ISS requirements during Flight 12A.1. Detailed requirements and agreements between the ISS Program and the Space Shuttle Program are specified in NSTS 21504, International Space Station-12A.1 Mission Integration Plan.
6.5.1
6.5.2 FLIGHT 12A.1 TASKS (IN DESCENDING PRIORITIZED ORDER) These tasks, listed in order of ISS Program priority, are to be executed during this flight. The order of execution for these tasks in the nominal plan may vary, depending on timeline efficiencies. The Flight 12A.1 ONS Plan (in Appendix J
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10. Perform EVA tasks to remove items from the Integrated Cargo Carrier (ICC) and install on the ISS, and return cargo from the ISS to the ICC, per Flight 12A.1 TPL in Appendix I
19. Transfer required N2 from the Orbiter to the ISS Airlock High Pressure Gas Tanks (HPGTs).
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23. Perform an additional 4 hours per rotating crewmember of ISS crew handover (16 hours per crewmember total). [IVA] 24. Perform imagery survey of the ISS exterior during Orbiter flyaround after undock. [IVA] [Imagery]
25. Transfer required O2 from the Orbiter to the ISS Airlock (A/L) HPGTs
6.5.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS 6.5.3.1 The maximum rendezvous altitude for Flight 12A.1 shall be 343 km (185 nmi).
6.5.3.2 The Orbiter shall dock at PMA-2.
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6.5.3.3 The ISS with Shuttle docked shall be in CMG control without ISS thrusters firing as well as the Shuttle Reaction Control System (RCS) inhibited for the following activities: A. Solar array and radiator extension (15 minutes). B. Solar array and radiator contingency retraction (15 minutes). C. Various EVA manual override tasks. D. SRMS unberthing of ITS P5, handoff to SSRMS, and SSRMS berthing of ITS P5 to ITS P4. E. P6 4B SAW retract.
6.5.3.4 The ISS with Shuttle docked shall be in a free drift configuration with the CMGs not controlling, Shuttle RCS inhibited and without ISS thrusters firing for the following activities:
None identified.
6.5.3.5 Solar Array Position For Critical Operations: A. P6 solar arrays shall be feathered and fixed at 210 degrees for channel 4B during Orbiter approach and docking and 150 degrees for channel 2B during Orbiter approach, docking, undocking, and separation while the Orbiter is within 121.92 m (400 ft). B. P4 solar arrays shall be feathered and locked at a SARJ angle of 0 degrees for channels 4A and 2A, at Beta Gimbal Assembly (BGA) angle of 270 degrees for channel 4A and 90 degrees for channel 2A while the Orbiter is within a distance of 182.88 m (600 ft) of the ISS for Orbiter approach and docking. C. P4 solar arrays shall be feathered and fixed at a SARJ angle of 90 degrees for channels 4A and 2A, at BGA angle of 70 degrees for channel 4A and 310 degrees for channel 2A while the Orbiter is within a distance of 182.88 m (600 ft) of the ISS for Orbiter undocking and separation. D. During P5 installation, P4 solar arrays shall be fixed at a SARJ angle of 0 degrees and BGA angles of 180 degrees for Channel 2A and 270 for Channel 4A.
6.5.3.6 The solar beta angle constraint during mated vehicle operations is required to be within +/-50 degrees (inclusive).
6.5.4 CONTINGENCY REQUIREMENTS 6.5.4.1 MCC-H and MCC-M shall build procedures, contingency timelines, and conduct training for the following non-EVA tasks: (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program
6-16 SSP 54014 WWW.NASAWATCH.COM Revision A Flight 12A.1 has determined that resources will not be applied to develop products/planning until the contingency is invoked). A. USOS and/or RS critical maintenance tasks as follows:
None identified. B. Contingency Shuttle separation from the ISS and re-rendezvous:
None identified.
6.5.4.2 MCC-H and MCC-M shall build procedures, contingency timelines, and provide pre-flight training for the EVA tasks to sufficient maturity to provide for the EVA response times designated. A. Class 1: All procedures, timelines and training are developed and certified to support an EVA response within 24 hours. When listing Class 1 items, a parenthetical should be added to denote the location of the ORU spare, or if pre-positioning is required. 1. EVA installation of P5. 2. P6 4B SAW retract. 3. DDCU R&R. 4. Main Bus Switching Unit (MBSU) R&R, reinstall on External Stowage Platform-2 (ESP-2). 5. Pump Module R&R, reinstall on ESP-2, transfer Integrated Assembly (IA) to ICC. 6. Contingency power cable routing for stranded MT. 7. Battery Charge/Discharge Unit (BCDU) remove and stow.
None identified. C. Class 3: For contingencies related to first flights hardware that are not time critical, skeleton EVA procedures will be developed preflight to support a Class 3 EVA. The EVA response time can be greater than two weeks and can be deferred to the stage or next available mission. The ISS Program has determined that additional resources will not be applied to further refine the training and integrated planning until the failure occurs. Subsequent flight listings for these hardware items will be contained in the GGR&C.
None Identified.
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6.5.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of recontact with ISS and of damage or injury following re-entry, procedures and training for the crew including worksite identification and desired jettison direction and velocity, and related hazard assessments.
6.5.5.1 Planned Jettison
The following items are planned for jettison during EVA in this flight: A. U.S.:
None identified. B. Russian:
None identified.
6.5.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew.
A. U.S.:
None identified. B. Russian:
None identified.
6.5.6 GROUND SYSTEMS REQUIREMENTS A. Ground support is required to operate SAMS-II, SDMS and MAMS sensors for DTO 257. (SAMS and MAMS availability will be assessed real time.)
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6.5.7 ISS REQUIREMENTS ON SHUTTLE DURING NONDOCKED TIME FRAME A. Three ISS Program Utilization payloads are integrated onto the Integrated Cargo Carrier (ICC) and are collectively identified as Space Test Program (STP)-H2, as listed below:
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6.6 FLIGHT 12A.1 UNDOCK TO FLIGHT 13A REQUIREMENTS (STAGE 12A.1)
This section identifies requirements applicable from Flight 12A.1 undock to Flight 13A dock, including requirements associated with 24 Progress-M undock, 25 Progress-M dock.
6.6.1
6.6.2 STAGE 12A.1 TASKS (IN DESCENDING PRIORITIZED ORDER)
These tasks, listed in order of ISS Program priority, are to be executed during this stage. The order of execution for these tasks in the nominal plan may vary, depending on timeline efficiencies. An ONS Plan (see Appendix J
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9. Lab Moderate Temperature Loop (MTL, Loop B) Heat Exchanger reconfiguration to the permanent External Thermal Control System (ETCS). [EVA] 10. Installation of cinches (and winches) on EEATCS aft radiator. [EVA] 11. Install shroud over EEATCS starboard radiator. [EVA] 12. Configure P6 EEATCS for dormancy.
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18. Perform high priority USOS/Russian payload operations (average of
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36. Perform medium priority USOS/Russian payloads operations.
None identified. 38. Perform SDTO 13005-U ISS Structural Life Validation and Extension for 13A Orbiter docking.
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E. APFR #5 Retrieval and relocation of TS to CETA Cart. F. APFR #5 Re-installation. G. APFR #6 Retrieval. H. APFR #6 Reinstallation. I. Deploy P3 UCCAS (Bay 20-Nadir). J. R&R S02B-D Remote Power Control Module (RPCM) for CMG-2. K. Patch Panel Reconfiguration for S02B-D RPCM. L. Preposition EVA equipment for Flight 13A as required. 48. Perform remaining maintenance (if crew time permits). [IVA] [Imagery] 49. Perform remaining USOS/Russian payload operations (if crew time permits). [IVA] 50. Perform SSRMS/Mobile Remote Servicer (MRS) Base System (MBS) On-Board Checkout Requirements (OCRs) per the priorities in Appendix H. [IVA] [Robotics] [Imagery] Ground] 51. Perform SDTO 13005-U during EVA (IWIS required) (if crew time permits).
6.6.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS
6.6.3.1 The ISS shall be in CMG control without ISS thrusters firing for the following activities: A. Retraction of EEATCS radiators.
6.6.3.2 The ISS shall be in free drift configuration with the CMGs not controlling and without ISS thrusters firing for the following activities:
None identified.
6.6.3.3 The 24 Progress-M shall undock from the DC 1 Nadir port.
6.6.3.4 The 25 Progress-M shall dock to the DC 1 Nadir port.
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6.6.3.5 The SSRMS shall be located on the MBS/MT at WS #2 prior to Flight 13A.
6.6.4 CONTINGENCY REQUIREMENTS
6.6.4.1 MCC-H and MCC-M shall build procedures, contingency timelines, and conduct training to allow the crew to perform the following non-EVA tasks: (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning until the contingency is invoked). A. USOS and/or RS critical maintenance tasks as follows:
None identified. B. Complete critical unfinished Flight 12A.1 assembly tasks as follows:
None identified. C. Remove/replace critical spares as follows:
None identified.
6.6.4.2 MCC-H and MCC-M shall build task specific procedures, contingency timelines, and conduct training to a high level sufficient to meet the following objectives:
• Identify task specific technical and safety issues.
• Identify on-board equipment required to perform the task.
• Determine the scope of effort required to prepare for the specific configurations, locations, and environmental conditions for the EVA.
• Provide the crew with the proper skill set required to perform the tasks given the on-board proficiency training assets available.
The readiness of these tasks will be based upon the generic development of the task procedures and timelines to a level that can be validated against a set of criteria. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning and the feasibility to perform those tasks on this flight/increment will be undetermined until the contingency is invoked. A. USOS and/or RS critical maintenance tasks as follows:
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4. SAW Manual Positioning 5. PFCS R&R
6. NH3 Leak Repair (FLAP and launch-on-need of, Trace Gas Analyzer (TGA))
None Identified.
6.6.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of recontact with ISS and of damage or injury following re-entry, procedures and training for the crew including worksite identification and desired jettison direction and velocity, and related hazard assessments.
6.6.5.1 Planned Jettison
The following items are planned for jettison during EVA in this stage: A. U.S.:
• P3 XPOP and RJMC Shrouds.
• Node 1 Zenith MDM Sunshade.
None identified.
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6.6.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew. A. U.S.: None identified. B. Russian: None identified.
6.6.6 GROUND SYSTEMS REQUIREMENTS
A. Ground Support is required to operate SAMS-II, SDMS and MAMS sensors for SDTO 13005-U. (SAMS and MAMS availability will be assessed real time.) B. Ground support is desired to operate Russian ALO for SDTO 13005-U.
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6.7 FLIGHT 13A REQUIREMENTS
This section identifies ISS requirements during Flight 13A. Detailed requirements and agreements between the ISS Program and the Space Shuttle Program as specified in NSTS 21509, International Space Station-13A Mission Integration Plan.
6.7.1
6.7.2 FLIGHT 13A TASKS (IN DESCENDING PRIORITIZED ORDER)
These tasks, listed in order of ISS Program priority, are to be executed during this flight. The order of execution for these tasks in this nominal plan may vary, depending on timeline efficiencies. The Flight 13A ONS Plan (in Appendix J
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5. Transfer critical items per Flight 13A TPL in Appendix I.
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C. Install S3 MT temporary stop. D. Stow S1 MT stop. 16. Perform activities to support Midodrine and PMDIS.
24. Transfer required O2 from the Orbiter to the ISS A/L HPGTs
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30. Perform SDTO 13005-U, ISS Structural Life Validation and Extension, for the 13A Orbiter Undocking (IWIS required if not performed for 12A.1 undocking). [IVA] [Ground] 31. The following EVA get ahead tasks do not fit in the existing EVA timelines; however, the EVA team will be trained and ready to perform should the opportunity arise. EVA/Mission Operations Directorate (MOD) has the flexibility to select the tasks to be completed based on efficiencies gained in performing the already scheduled required tasks. None Identified.
6.7.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS
6.7.3.1 The maximum rendezvous altitude for Flight 13A shall be 335 km (181 nmi).
6.7.3.2 The Orbiter shall dock at PMA-2.
6.7.3.3 The ISS with Shuttle docked shall be in CMG control without ISS thrusters firing as well as the Shuttle RCS inhibited for the following activities: A. SRMS unberthing of ITS S3/S4, handoff to SSRMS, and SSRMS berthing of S3/S4 to ITS S1 until SSAS capture and secure with at least 3 of four bolts. B. During SAW deploy or retract. C. During Photovoltaic (PV) Radiator deploy or retract. D. After the last SARJ Launch Lock has been removed and until at least 1 DLA is placed in the “Locked” position. E. During MT/Load Transfer Unit (LTU) latch transition open or closed. F. During Umbilical Mating Assembly (UMA) translation.
6.7.3.4 The ISS with Shuttle docked shall be in a free drift configuration with the CMGs not controlling, Shuttle RCS inhibited and without ISS thrusters firing for the following activities:
None identified.
6.7.3.5 The mated stack shall be in CMG only control with ISS and Shuttle thrusters inhibited (SM, Progress, or Soyuz and Shuttle Vernier Reaction Control System (VRCS) or Primary Reaction Control System (PRCS)) for the following conditions/activities:
None identified.
6.7.3.6 The mated stack will be limited to CMG only control with desat enabled using only ISS propulsive sources under the following conditions. The ISS propulsive sources that may be used are also constrained. The allowable propulsive control sources will be
6-31 SSP 54014 WWW.NASAWATCH.COM Revision A Flight 13A defined with flight specific analysis and documented in the appropriate mission or vehicle specific flight rules. A. Any motion or planned positions of the SRMS or SSRMS with the S3/S4 grappled and while clear of structure. B. Until all SSAS operations are nominally completed or until a minimum 3 of 4 bolts are fully engaged. C. During MT operations until latched at a worksite in the minimum required configuration. D. When either the S4 of P6 SAWs are not fully retracted or fully deployed and tensioned. E. If the S4 PVR is not fully retracted and cinched or fully deployed.
6.7.3.7 The mated stack may perform attitude control using Shuttle VRCS for the following conditions/activities: A. After SSAS Capture Latch fully closed. B. After SSAS bolt operations are completed and the minimum configuration of the CLA and bolt combinations are achieved. C. MT is unlatched with MT Brake engaged, SSRMS loaded or unloaded. D. If either S4 or P6 SAWs are either ready to deploy or re-latch or partially deployed and not tensioned as defined in Paragraph 6.4.3.13.C. E. If the S4 PVR is partially deployed which is defined as a radiator uncinched and unwinched and not fully deployed.
6.7.3.8 The mated stack may perform attitude control using Shuttle PRCS for the following conditions/activities: A. Any planned SRMS position with the S3/S4 element grappled when clear of structure. B. Any planned positions of the SSRMS with the S3/S4 grappled when clear of structure. C. After SSAS bolt operations are complete with any combination of 3 bolts at full torque. D. MT fully latched.
6.7.3.9 ISS reboost (SM, Progress) or Shuttle reboost (VRCS thrusters) is allowed during the following conditions/activities: A. After SSAS bolt operations are complete with any combination of 3 or 4 bolts
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B. MT fully latched. C. MT unlatched, brakes on, SSRMS unloaded. D. If either S4 or P6 SAWs are either ready to deploy or re-latch or partially deployed and the solar array blanket is not tensioned. E. If the S4 PVR is partially deployed which is defined as a radiator uncinched and unwinched and not fully deployed. 6.7.3.10 Shuttle and ISS crew exercise is not permitted during the following activities
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E. S4 solar arrays shall be feathered and fixed at a SARJ angle of
6.7.3.14 EVA operations on and to the S3/S4 cargo element will have the following limitations for the specified vehicle configurations
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C. No EVA operations are allowed outboard of the SARJ once the last SARJ Launch Lock is removed and until at least 1 DLA is placed in the “Locked” position. D. No maximum EVA loads are allowed while on the S3/S4 element or in conditions, which induce loads into the S3/S4 element for the following conditions: 1. Once the S4 SAW is unlatched and until the array is fully deployed with the solar array blankets fully tensioned. 2. Once the P6 solar array blanket has been untensioned and until the SAW has been fully retracted and the Blanket Box latched. 3. Once the S4 PVR has been uncinched and unwinched until the radiator is fully deployed.
6.7.3.15 The addition of truss elements outboard of the S4 SARJ are constrained to the following conditions
6.7.3.17 The ISS will maneuver to and maintain a specified attitude
6.7.4 CONTINGENCY REQUIREMENTS
6.7.4.1 Mission Control Center - Houston (MCC-H) and Mission Control Center - Moscow (MCC-M) shall build procedures, contingency timelines, and conduct training for the following non-EVA tasks: (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning until the contingency is invoked.): A. USOS and/or RS critical maintenance tasks as follows:
None identified. B. Contingency Orbiter separation from the ISS and re-rendezvous.
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6.7.4.2 MCC-H and MCC-M shall build procedures, contingency timelines, and provide pre-flight training for the EVA tasks to sufficient maturity to provide for the EVA response times designated. A. Class 1: All procedures, timelines and training are developed and certified to support an EVA response within 24 hours. When listing Class 1 items, a parenthetical should be added to denote the location of the ORU spare, or if pre-positioning is required.
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22. EVA assisted deployment of S4 SAWs. 23. Remove and replace P4 or P6 PV DDCU. B. Class 2: For contingencies occurring during the docked time frame an EVA response is available on a subsequent EVA based on re-prioritization of the mission tasks. Published procedures and timelines are developed, but may require real time updates to match the flight specific failure. 1. Manually override the Blanket Box Motor Drive Amplifier (MDA). 2. Manually override the Beta Gimbal Anti-rotation Latch. 3. Perform SARJ DLA Back-off. 4. Manually release and jettison PV Radiator. 5. Remove and temporarily stow the BCDU on to an adjacent battery ORU for P4, P6 or S4.
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C. Class 3: For contingencies related to first flights hardware that are not time critical, skeleton EVA procedures will be developed preflight to support a Class 3 EVA. The EVA response time can be greater than two weeks and can be deferred to the stage or next available mission. The ISS Program has determined that additional resources will not be applied to further refine the training and integrated planning until the failure occurs. Subsequent flight listings for these hardware items will be contained in the GGR&C. 1. Remove and replace SARJ Trundle Bearing on P3 or S3. 2. Install Z1 Truss (Z1) - Y Bypass Jumpers to support P6 power requirements. 3. Install, and after restart, remove RACU Restart Cables. 4. Install Secondary Power Feedback Jumpers to support power channel keep-alive power for P4, P6, or S4. 5. Remove and replace UTA.
6.7.4.3 The S3/S4 cargo element will be returned for the following condition: A. S3/S4 cannot structurally support docking/undocking loads of visiting vehicles and the required structural integrity cannot be reasonably achieved through stage EVAs. Consideration will be made in real-time to return the S3/S4 cargo element if the element cannot be activated or safed to the minimal thermal survival configuration. 6.7.4.4 In the event of an ISS CMG failure while the S3/S4 element is attached to the SRMS/SSRMS, Shuttle attitude control using VRCS may be used with the S3/S4- SRMS/SSRMS in the following pre-analyzed, static configurations: A. Low or High Payload Bay (PLB) Hover position. B. At Handoff position. C. SRMS ungrapple/SSRMS grapple. D. S3/S4 pre-install position.
6.7.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of recontact with ISS and of damage or injury following re-entry, procedures and training for the crew including worksite identification and desired jettison direction and velocity, and related hazard assessments.
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6.7.5.1 Planned Jettison
The following items are planned for jettison during EVA in this flight: A. U.S.:
None Identified. B. Russian:
None identified.
6.7.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew. A. U.S.:
Manually release and jettison PV Radiator.
Manually release and jettison SAW. B. Russian: None identified.
6.7.6 GROUND SYSTEMS REQUIREMENTS
A. Ground support is required to operate SDMS, IWIS and EWIS for SDTO 13005-U and 15003-U. B. Ground support is highly desired to operate SAMS-II, MAMS, and Russian ALO sensors for SDTOs 13005-U and 15003-U. (SAMS and MAMS availability will be assessed real time.) C. Ground support is required to perform full functional checkout of S3/Bay 2, MT WS #1 in preparations for Flight 13A.1 assembly activities.
6.7.7 ISS REQUIREMENTS ON SHUTTLE DURING NONDOCKED TIME FRAME
A. Midodrine B. MAUI C. RAMBO
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6.8 FLIGHT 13A UNDOCK TO FLIGHT 14S REQUIREMENTS (STAGE 13A)
This section identifies requirements applicable from Flight 13A undock to Flight 14S dock, including requirements associated with 23 Progress-M undock
6.8.1
6.8.2 STAGE 13A TASKS (IN DESCENDING PRIORITIZED ORDER)
These tasks, listed in order of ISS Program priority, are to be executed during this stage. The order of execution for these tasks in the nominal plan may vary, depending on timeline efficiencies. An ONS plan (See Appendix J
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10. Perform USOS/Russian maintenance activities for those systems with redundancy. [IVA] [Imagery] 11. Perform software transition from Command and Control System (CCS) R4 to CCS R6. [Ground] 12. Perform software transition from Portable Computer System (PCS) R9 to PCS R10. [Ground] [IVA] 13. Perform software transition from Internal Systems (INT) R2 to INT R3. [Ground] 14. Perform P6 DCSU Firmware Uplink. [Ground] 15. Perform IMS audits as needed (up to 30 hours per increment, if crew time permits). 16. Perform SDTO 13006-U/R, Forcing Function Definition and Microgravity Allocation of Crew Resistive Exercises, during a nominal Russian Force Loader exercise session (IWIS if not collected during 12A.1 stage).
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29. Perform SDTO 13006-U/R, Forcing Function Definition and Microgravity Allocation of Crew Resistive Exercises, during a nominal Interim Resistive Exercise Device (IRED) exercise session (IWIS required).
6.8.3 ISS/VEHICLE ORBITAL AND CONFIGURATION REQUIREMENTS
6.8.3.1 The 23 Progress-M shall undock from the SM Aft port.
6.8.3.2 The ISS shall be in CMG control without ISS thrusters firing for the following activities:
None identified.
6.8.3.3 The ISS shall be in free drift configuration with the CMGs not controlling and without ISS thrusters firing for the following activities:
None identified.
6.8.4 CONTINGENCY REQUIREMENTS
6.8.4.1 MCC-H and MCC-M shall build procedures, contingency timelines, and conduct training to allow the crew to perform the following non-EVA tasks: (The items listed below are for unique tasks or first implementation of new tasks. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning until the contingency is invoked). A. USOS and/or RS critical maintenance tasks as follows: None identified. B. Complete critical unfinished Flight 13A assembly tasks as follows: 1. Deploy S4 PVR and activate S4 active thermal system. 2. Deploy S4 SAW.
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3. Thermal condition, recondition, and charging of Channel 1A and 3A batteries within 8 days after launch. 4. Verify 1A and 3A SAW positioning capability to support docking and undocking operations for visiting vehicles. 5. Reconfigure P6 for survival power and retract P6 starboard (Channel 2B) SAW. C. Remove/replace critical spares as follows:
None identified.
6.8.4.2 MCC-H and MCC-M shall build task specific procedures, contingency timelines, and conduct training to a high level sufficient to meet the following objectives:
• Identify task specific technical and safety issues.
• Identify on-board equipment required to perform the task.
• Determine the scope of effort required to prepare for the specific configurations, locations, and environmental conditions for the EVA.
• Provide the crew with the proper skill set required to perform the tasks given the on-board proficiency training assets available.
The readiness of these tasks will be based upon the generic development of the task procedures and timelines to a level that can be validated against a set of criteria. For contingency tasks not listed below, products/planning are already in place from previous flights/stages, or the ISS Program has determined that resources will not be applied to develop products/planning and the feasibility to perform those tasks on this flight/increment will be undetermined until the contingency is invoked. A. USOS and/or RS critical maintenance tasks as follows:
The tasks listed in paragraph 6.6.4.2 are still applicable. B. Complete critical unfinished Flight 13A assembly tasks as follows: 1. Install or complete installation of S3 to S1. 2. Perform S1 to S3 utility connections and activation. 3. Uncinch S4 PVR in preparation for IVA activities to deploy S4 PVR and activate S4 active thermal system. 4. Configure ISS and S4 Element for S4 (Channel 1A and 3A) in prep for IVA activities to deploy SAW. 5. Configure/activate the starboard SARJ. a. Install 4 of 4 AJIS Struts. b. Install 4 SARJ Brace Beams.
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c. Engage Pinion Gears of both Starboard DLAs. d. Remove Launch Locks. e. Remove Launch Restraints. 6. Complete EVA tasks necessary to enable MT/CETA starboard translation path to MSS/WS #1. a. Remove and stow S3 Keel and Drag Link. b. Remove S3 SVS Target. c. Install S3 MT temporary stop. d. Stow S1 MT stop. e. Remove S3 Remote Power Distribution Assembly (RPDA) covers. C. Remove/replace critical spares as follows:
None Identified.
6.8.5 JETTISON REQUIREMENTS
Planning and product development will be performed to support jettison of the following items during EVA. This will include trajectory analysis to ensure acceptable low risk of recontact with ISS and of damage or injury following re-entry, procedures and training for the crew including worksite identification and desired jettison direction and velocity, and related hazard assessments.
6.8.5.1 Planned Jettison
The following are items planned for jettison during EVA in this stage: A. U.S.: None identified. B. Russian: None identified.
6.8.5.2 Contingency Jettison
The following items may require jettison if they cannot be configured safely to allow vehicle dockings or maneuvers or if their continued operation poses a hazard to the EVA crew. A. U.S.:
None identified.
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B. Russian: None identified.
6.8.6 GROUND SYSTEMS REQUIREMENTS
A. Ground Support is required to operate SDMS, IWIS and EWIS for SDTOs 13004-U, 13005-U, 13006-U/R and 15003-U. B. Ground support is highly desired to operate SAMS-II, MAMS and Russian ALO sensors for SDTOs 13004-U, 13005-U, 13006-U/R and 15003-U. (SAMS and MAMS availability will be assessed real time.)
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APPENDIX A
ACRONYMS AND ABBREVIATIONS
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APPENDIX A - ACRONYMS AND ABBREVIATIONS
AC Assembly Complete ACU Arm Computer Unit AJIS Alpha Joint Interface Structure A/L Airlock ALO Optical Linear Accelerometers ALTEA Anomalous Long Term Effect of Astronauts ANDE Atmospheric Neutral Density Experiment APFR Articulating Portable Foot Restraint APPC
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DQA Document Quality Assurance DTO Development Test Objective EarthKAM Earth Knowledge Acquired by Middle School EAS Early Ammonia Servicer ECLSS
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IA Integrated Assembly ICC Integrated Cargo Carrier IDRD Increment Definition and Requirements Document IEA Integrated Equipment Assembly IELK Individual Equipment Liner Kit IFHX Interface Heat Exchanger IM Increment Manager IMS Inventory Management System INT Internal Systems IP International Partner IRED Interim Resistive Exercise Device ISL
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MCC-M Mission Control Center - Moscow MCOP Multilateral Crew Operations Panel MCU MBS Computer Unit MDA Motor Drive Amplifier MDM Multiplexer/Demultiplexer MDSF Manipulator Development and Simulation Facility MELFI Minus Eighty Degree Laboratory Freezer for ISS MEPSI Micro-electromechanical System-Based Pico Satellite Inspector MIC Mission Integration Contract ml Milliliters MLE Middeck Locker Equivalent MLI Multilayer Insulation MMOD Micro Meteoroid Orbital Debris MOD Mission Operations Directorate MORD Medical Operations Requirements Documents MPLM Multi-Purpose Logistics Module MRS Mobile Remote Servicer MSG Microgravity Science Glovebox MSS Mobile Servicing System MT Mobile Transporter MTL Moderate Temperature Loop
N2 Nitrogen N/A Not Applicable NASA National Aeronautics and Space Administration NDD Normal Data Dump NET No Earlier Than NH3 Ammonia nmi nautical mile NSTS National Space Transportation System
O2 Oxygen OBT Onboard Training OCA Orbital Communications Adaptor OCR On-orbit Checkout Requirement OGS Oxygen Generation System OL Outboard Lower ONS Off-Nominal Situation ORCA Oxygen Recharge Compressor Assembly ORU Orbital Replacement Unit P Port PAO Public Affairs Office PAS Payload Attach System PCS Portable Computer System PCU Power Conversion Unit PD Payload Developer
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PFCS Pump Flow Control Subsystem PFE Periodic Fitness Evaluation PIER Post Increment Evaluation Report PIO Projects Integration Office PLA Picosat Launcher Assembly PLB Payload Bay PMA Pressurized Mating Adapter PMCA Power Management Control Application PMDIS Perceptual Motor Deficits In Space PRCS Primary Reaction Control System PRD Payload Retention Device PRLA Payload Retention Latch Assembly PTS Portable Test System PV Photovoltaic PVCU Photovoltaic Controller Unit PVR Photovoltaic Radiator PVRGF Photovoltaic Radiator Grapple Fixture PVTCS Photovoltaic Thermal Control System RACU Russian-to-American Converter Unit RAFT Radar Fence Transponder RAM Radiation Area Monitor RAMBO Ram Burn Observation RCS Reaction Control System Ref Reference RJMC Rotary Joint Motor Controller ROS
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SARJ Solar Alpha Rotary Joint SAW Solar Array Wing S-Band 1550 to 5200 Megahertz SDBI Short Duration Bioastronautics Investigation SDMS Structural Dynamic Measurement System SDTO Station Development Test Objective SE Subelement SEM Space Experiment Module SHLR Spacehab Logistics Rack SM Service Module SMDP Service Module Debris Panels SORR Stage Operations Readiness Review SPIP Station Program Implementation Plan SRMS Shuttle Remote Manipulator System SRP Safety Review Panel SSAS Segment-to-Segment Attach System SSC Station Support Computer SSCB Space Station Control Board SSCN Space Station Change Notice SSP Space Shuttle Program SSPCB Space Station Program Control Board SSPL Space Shuttle Picosat Launcher SSPTS Station/Shuttle Power Transfer System SSRMS Space Station Remote Manipulator System SSU Sequential Shunt Unit STP Space Test Program STS Space Transportation System SVS Space Vision System SWAB Surface, Water, Air Biocharacterization SWG System Working Group TBD To Be Determined TBR To Be Resolved TCS Thermal Control System TDRS Tracking and Data Relay Satellite TESS Temporary Early Sleep Station TGA Trace Gas Analyzer TMA Transport Modified Anthropometric TPL Transfer Priority List TPS Thermal Protection System TRAC Test of Reaction and Adaptation Capability TROPI
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UCCAS Unpressurized Cargo Carrier Attach System ULF Utilization Logistics Flight UMA Umbilical Mating Assembly U/R US/Russian U.S. United States USOS United States On-orbit Segment UTA Utility Transfer Assembly VIPeR Vehicle Integrated Performance and Resources VIS
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APPENDIX B
GLOSSARY OF TERMS
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APPENDIX B - GLOSSARY OF TERMS
ACCOMMODATIONS Launch vehicles or ISS physical locations where utilization or system items are stowed or installed. The following specific types of accommodations are recognized (the unit of measure of the accommodation is shown in parentheses): A. Rack locations (number) B. MLEs C. CTBEs D. Pressurized volume (RVE) E. Unpressurized volume (cubic feet) F. Truss attach points (number) G. Experiment Module Exposed Facility attach points (number) H. Experiment Logistics Module Exposed Section attach points (number)
ALLOCATION The portioning of resources and accommodations to the ISS users. Total ISS resources and accommodations are allocated between system and utilization. Utilization resources and accommodations are allocated between IPs.
ASSEMBLY PHASE Refers to the time period starting with First Element Launch (FEL) and ending with the landing of the last flight in the Assembly Sequence.
CARGO CARRIER Element of a transportation vehicle that provides capability to carry cargo.
CHECKOUT To ensure that the rack performs its intended functions with respect to data, power, Thermal Control System (TCS), etc.
CONSOLIDATED OPERATIONS AND UTILIZATION PLAN The strategic document that defines the system and utilization activities planned for the ISS. On an Increment basis, it establishes the amount of resources and accommodations allocated to and subscribed by system and each International Partner for utilization, and reflects the planned amounts of supporting services from other Programs that are available and subscribed. The Consolidated Operations and Utilization Plan also provides specific direction and guidance to tactical planning regarding Consolidated Operations and Utilization Plan implementation.
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CONTINGENCY EXTRAVEHICULAR ACTIVITY An unplanned EVA required to support the safe return of the vehicle and crew and/or restore critical systems/functions.
CREW DAYS IN SPACE The time period from launch of a crew rotation vehicle to landing of the vehicle which returns that crew.
CREW DAYS ON THE ISS The time period from docking of a crew rotation vehicle to undock of the vehicle which returns that crew.
EXECUTION PLANNING The planning that occurs 18 months before the start of an increment through real-time operations.
FLIGHT For Shuttle flights, the term “Flight” refers to the sequence of events that takes place between the lift-off and landing of the Shuttle. For permanent Russian Elements flights, the term refers to the sequence of events that takes place between the lift-off of the element through completion of docking to the ISS. For replaceable IP Element flights, the term refers to the sequence of events that take place between lift-off and entry/landing of the element.
HARD COMMIT Amount of resources allocated to utilization based on specified ISS Program system capabilities.
INCREMENT (Also known as Expedition.) A specific time period which combines different operations such as assembly, scientific research, testing, logistics, maintenance, and other ISS system and utilization operations. The initial unmanned timeframe and subsequently, the timeframe of each crew expedition. During the assembly phase, an increment is defined as a period supporting crew rotation. The duration of an increment is the time period from the launch of a designated Expedition crew to the undocking of the return vehicle for that Expedition crew.
INSTALL Complete the structural attachment and, if applicable, connect utilities.
INTEGRATED TRUSS SEGMENT An un-pressurized structural element of the ISS that includes ground-installed electrical, thermal, communications, command, and data components. Examples are Zenith (Z)1 and Starboard (S)0.
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INTERNATIONAL PARTNER Denotes the international space agencies who are jointly involved in the development of the ISS. These agencies include the Canadian Space Agency (CSA), European Space Agency (ESA), Japan Aerospace Exploration Agency (JAXA), and the Federal Space Agency (Roscosmos).
JETTISON The intentional manual release of an object during an EVA such that the object safely separates from ISS and eventually re-enters through earth’s atmosphere. Jettisons may be planned, to achieve waste disposal or scientific objectives, or in response to a contingency, such as inability to install or safely stow or return an item.
LAUNCH VEHICLE A transportation vehicle that provides provisions, crew and/or hardware to the ISS (a Soyuz or Progress for example).
NONRECOVERABLE CARGO Cargo that is designated as cargo that will either be destroyed upon reentry or when it is returned to Earth (e.g., Shuttle/ISS trash).
OBJECTIVES High-level goals that do not specify any particular activity. For an IDRD, each increment will have objectives. During assembly, the main system objectives are building, activating, and supporting the ISS. Examples of utilization objectives during assembly are installing and activating research facility racks and performing research operations.
PLANNING PERIOD Approximately one calendar year of ISS activity. A planning period is comprised of one or more increments.
RACK VOLUME EQUIVALENT A unit of volume that equals 36.0 cubic feet or 1.0193 cubic meters.
RECOVERABLE CARGO Cargo that is removed from the ISS and returned to Earth to be refurbished for future use, samples for evaluation, or items to be examined as part of sustaining engineering.
RESOURCES Identifies a particular subset of ISS on-orbit capabilities used in support of system and utilization operations. It includes the following: A. Average power kW B. Crew time (hours) C. Communications
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D. On-orbit accommodations (pressurized and unpressurized) E. Transportation Mass F. Transportation Volume
SCHEDULED EXTRAVEHICULAR ACTIVITY An EVA planned prior to the start of an increment or flight/stage with nominal crew training and included on the nominal mission timeline.
SHORT DURATION BIOASTRONAUTICS INVESTIGATION A medical research payload that will be flown and returned in a pressurized volume on the same Shuttle flight, involves a Shuttle (non-ISS) crewmember(s) as the test subject, and does not require any ISS resources (e.g., ISS crew time, ISS power, ISS communications) to accomplish the research objective. Responsibility for manifesting and prioritizing Short Duration Bioastronautics Investigations (SDBIs) with respect to the other ISS payloads resides with the ISS Payloads Office. However, responsibility for planning SDBI activities and resources during the mission, as well as Certification of Flight Readiness (CoFR) for the SDBIs, resides with the Space Shuttle Program and will be accomplished in accordance with Space Shuttle Program processes and procedures.
SOFT COMMIT Amount of resources estimated to be available to utilization based on either estimated capabilities above specified conditions/assumptions, a reduction of system reserves, or both.
STAGE Period of on-orbit configuration of the ISS after each flight which adds capability to the ISS. This can also refer to a designated period between launch vehicles defined by the ISS Program for requirement documentation and planning purposes.
SYSTEMS A group of Hardware (H/W) that collectively supports or provides capabilities to the orbiting ISS, In general, anything other than utilization. Specifically included in this set are assembly, logistics/maintenance environmental support, power, etc.
TASK TYPE DESIGNATOR
Identifies categories for mission task requirements and include: [Extravehicular Activity (EVA)], Intravehicular Activity (IVA)], [Robotics], [Utilization], [Ground], [Attitude (ATT)], [Jettison], [Imagery]
TRANSFER To remove H/W and/or provisions from one vehicle or module and place onto another vehicle or module.
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TRANSFER VEHICLE A transportation vehicle that provides capability to move mass and volume from the insertion orbit to ISS and from ISS to reentry.
UNSCHEDULED EXTRAVEHICULAR ACTIVITY An EVA resulting from unforeseen developments during a mission and not included in the nominally scheduled mission activities, but which may be required to achieve ISS Program mission success.
UTILIZATION The set of requirements associated with research experiment integration.
VALIDATION The process of formally approving the developed process, services, or products at the conclusion of operational test and evaluation. This approval indicates developed processes, services, or products satisfy their intended operational mission.
VERIFICATION The activities which assure that each level of requirements (including test requirements) or specifications correctly echoe the intentions of the immediately superior level of requirements.
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APPENDIX C
OPEN WORK
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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 item is inserted as a placeholder wherever the 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.,
TABLE C-1 TO BE DETERMINED ITEMS (PAGE 1 OF 3)
TBD Section Description Status 1-1 1.2, 2.1 SSP 54014-13S Annex 1 has not been published. Open 1-2 1.2, 2.1 SSP 54014-12A.1 Annex 1 has not been published. Open 1-3 1.2, 2.1 SSP 54014-23P Annex 1 has not been published. Open 1-4 1.2, 2.1 SSP 54014-13A Annex 1 has not been published. Open 1-6 1.2, 2.1 SSP 54014-24P Annex 1 has not been published. Open 1-7 1.2, 2.1 SSP 54014-25P Annex 1 has not been published. Open 1-8 1.2, 2.1 SSP 54013-12S Annex 1 has not been published. Closed 1-9 1.3, 2.1 SSP 543XX, Post Increment Evaluation Report for Increment 14, has not Open been published. 1-10 1.2, 2.1 SSP 54013-22P Annex 1 has not been published. Open 1-11 1.2, 2.1, SSP 540XX has not been published. Open Table 3.3-1 1-13 1.2, 2.1 SSP 54014-ANX 2 has not been published. Closed 1-14 1.2, 2.1 SSP 54014-ANX 3 has not been published. Open 1-15 1.2, 2.1 SSP 54014-ANX 4 has not been published. Closed 1-16 1.2, 2.1 SSP 54014-ANX 5 has not been published. Open 1-17 1.2 Increment 15 Flight program to be determined Open 2-1 2.2 SSP 543XX has not been published. Open 2-2 1-2, 2.1 Progress vehicle designator to be determined. Closed 3-4 Figure 3.1-1, Flight Engineer position assignments have not been determined. Closed Table 3.3-1, 6.3.2, 6.4.2, 6.5.2, 6.8.2 3-5 Figure 3.1-1 EVA dates have not been determined. Open 3-6 Figure 3.1-1, Russian EVA plans have not been determined. Closed Table 3.3-1, 6.8.2
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TABLE C-1 TO BE DETERMINED ITEMS (PAGE 2 OF 3)
TBD Section Description Status 3-7 Figure 3.1-1, Date of 13S relocation from SM aft port to FGB nadir port is not yet defined. Open Table 3.2-1, Table 3.3-1, 6.4.2 3-8 Table 3.3-1, NASA Utilization Objectives are undefined. Open 6.4, 6.4.2 3-9 Table 3.3-1, Russian Utilization Objectives are undefined. Open Table 4.2-1 3-10 Table 5.0-2 ESA Utilization Objectives are undefined. Closed 3-11 Table 3.3-1, Visiting Crew Utilization Objectives are undefined. Open 6.2.2, 6.3.2, Appendix K 3-12 Table 3.3-1 Increment 14 crew assignments are to be determined. Closed 3-13 Table 3.3-1, Final approval pending flight specific analysis. Open 6.5.2, 6.5.7, 6.7.2, 6.7.7 3-14 Table 3.3-1, Hardware development may not support delivery to ISS for task execution in Open 6.4.2 this stage 4-1 4.2, Crew time allocations will be updated when the Flight Program dates are Open Table 4.2-1 agreed upon. 4-3 Table 4.4-1 VIPeR has no funding for analysis and no customer for this data has been Open identified. 4-4 6.5.2, 6.7.2 Timing allocated for USOS payloads during Shuttle docked operations is Open being assessed. 4-5 Table 4.2-1, Timing allocated for RS payloads during Shuttle docked operations is being Open 6.5.2, 6.7.2 assessed. 5-1 Table 5.0-1(A) Power Allocation for Utilization has not been determined. Open 5-2 Table 5.0-1 Mass and Volume quantities for Dry Cargo to be determined. Open 5-3 Table 5.0-1 Mass and Volume quantities for Descent to be determined. Open 5-4 Table 5.0-1 Russian Allocation has not been determined. Closed 5-5 Table 5.0-1 Under evaluation based on maintenance internal requirements. Closed 5-6 Table 5.0-1 Crew provisions allocations will be worked through the consumables team Closed for each flight once the Flight Program is approved. 5-7 Table 5.0-1 Water transfer to ISS to be determined. Open 5-8 Table 5.0-1 Mass quantities for propellant to be determined. Open 5-9 Table 5.0-1 Mass quantities for gas to be determined. Open 5-10 Table 5.0-1 Water quantities to be determined. Open 5-11 Table 5.0-1 Allocations are not currently applicable due to constrained Open upmass/downmass. Changes to the currently baselined manifest will be worked based on priorities. Applicability of this section of the table for Flights 12A.1 and 13A is under review. 5-12 Table 5.0-2 This table is currently being reviewed for relevance as part of the IDRD Open Blank Book Survey 6-1 6.2.1 Russian utilization experiments to be determined. Closed 6-5 6.7.3.14 Dimensions from S3/S1 for which EVA operations are limited are to be Open determined. 6-6 Table 3.3-1, Russian EVA tasks to be determined. Closed 6.8.2
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TABLE C-1 TO BE DETERMINED ITEMS (PAGE 3 OF 3)
TBD Section Description Status 6-7 6.8.2 Crew time for Increment 14 has not been determined. Open 6-9 6.5.2, 6.7.2 ISS reboost altitude for Shuttle is to be determined. Open 6-10 6.5.2, 6.5.6 DTO 257 has been disapproved by the SRP as currently written. Open SSCN 8459, update is in review. 6-11 6.6.2 Work to be determined if Node Unity Label can be returned is ongoing. Closed 6-12 6.7.2 Utilization has no allocation on this flight at this time. Closed 6-13 6.7.2 EAS EVA task is being assessed. Closed 6-14 6.7.3.9, Specific attitude requirements for Flight 13A have not been determined. Open 6.7.3.17 6-15 6.3.2, 6.6.2 Russian review of this SDTO is still in work. Open 6-16 6.6.2 ORCA launch on 12A is under review. Open 6-17 6.6.2 This hardware has not been approved on the 12A manifest. Open A-1 Appendix A To be determined by book manager. Open D-1 Appendix D On-Orbit rack descriptions to be provided at a later date. Open H-1 6.4.2, 6.6.2, OCR’s will be provided at a later date. Closed 6.8.2 Appendix H I-1 6.5.2, 6.7.2 12A.1 and 13A transfer priority lists are under review. Open Appendix I J-1 6.3.2, Flight 13S Off Nominal Situations are undefined. Open Appendix J J-2 6.4.2, Stage 13S Off Nominal Situations are undefined. Open Appendix J J-3 6.5.2, Flight 12A.1 Off Nominal Situations are undefined. Open Appendix J J-4 6.6.2, Stage 12A.1 Off Nominal Situations are undefined. Open Appendix J J-5 6.7.2, Flight 13A Off Nominal Situations are undefined. Open Appendix J J-6 6.8.2, Stage 13A Off Nominal Situations are undefined. Open Appendix J K-1 Section 6.3.2, To be provided at a later date. Closed Appendix K
Table C-2 lists the specific To Be Resolved (TBR) issues in the document that are not yet known. The TBR issue 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.,
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TABLE C-2 TO BE RESOLVED ITEMS (PAGE 1 OF 3)
TBR Section Description Status FP 3-6 Figure 3.1-1, This date has been identified as No Earlier Than (NET) by the Shuttle Open Table 3.2-1, Program. Table 3.3-1, Table 5.0-1, Table 5.0-2 FP 3-7 Figure 3.1-1, Dates are under review to resolve GGR&C conflicts. Open Table 3.2-1, Table 5.0-1, Table 5.0-2, 6.4, 6.4.2, 6.4.3.3, 6.4.3.4 FP 3-8 Figure 3.1-1, Russian Flight Program is under review. The Russian Flight Program may Open Table 3.2-1, change due to absent Partner commitments for crew rotation, crew rescue, Table 3.3-1, and ISS habitation. Table 5.0-1, Table 5.0-2, 6.4.2, 6.4.3.3, 6.4.3.4, 6.4.3.5, 6.6.2, 6.6.3.3, 6.6.3.4, 6.8, 6.8.2, 6.8.3.1 FP 3-11 Table 3.2-1 Shuttle Flight Program is under review. Closed FP 3-23 Figure 3.1-1, Shuttle docking altitude is under review. Closed Table 3.2-1, 6.5.3.1, 6.7.3.1 FP 3-29 1.2, Crew rotation plan is under review. Closed Figure 3.1-1, Table 3.3-1, 6.3.2 FP 3-31 Table 3.2-1 Launch Date under review with Shuttle Program. Closed 4-1 Table 4.4-1 Power balance and allocation to be provided. Closed 5-1 Table 5.0-1 Allocation to Utilization is under review pending LPM and IM approval. Closed 5-2 Table 5.0-1, O2 transfer is currently under review. Open 6.5.2, 6.7.2 5-3 Table 5.0-1, N2 transfer has not been assessed. Open 6.5.2 5-4 Table 5.0-1 13A Descent allocation is being assessed. Closed 6-1 6.7.4.2 Program to verify clearance limitations. Open 6-2 6.4.4.2, Increment 14 specific contingency tasks to be resolved by SWG. Closed 6.6.4.2, 6.8.4.2
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TABLE C-2 TO BE RESOLVED ITEMS (PAGE 2 OF 3)
TBR Section Description Status 6-5 6.7.3.11 Angles to be provided by VIPeR. Open 6-8 6.7.3.10, Final list of constraints pending 13A Flight specific analysis. Constraints list Open 6.7.3.12, are compiled from current 9A, 11A, and 12A constraints for related 6.7.3.13, hardware. 6.7.3.14, 6.7.3.15, 6.7.3.16 6-10 6.7.4.2 Class 1 definition is currently under review. Open 6-11 6.7.2 Loads analysis is being reviewed to determine if Beta Gimbal locking is Open required for this operation. 6-12 6.6.5.1 Pending analysis and approval by program that these items can safely be Open Jettisoned. 6-15 6.7.4.2 Class is under review at each location. Open 6-16 6.7.4.2 Class and spare availability are under review. Open 6-17 6.8.2 Pending inputs from Avionics and Software. Closed 6-18 6.7.3 Content is under review for level of detail to be included in this section. A Open Mission Integration and Operations action is in already in work, resolutions is expected to be included in the next IDRD CR. 6-19 6.4.4.2, Tasks are not currently certified due to hardware constraints. Open 6.5.4.2, 6.6.4.2, 6.7.4.2 6-20 6.6.4.2 On-Orbit hardware deficiencies may preclude successful Heat Exchanger Open R&R. 6-21 6.7.4.2 Potential issues related to battery discharge to be resolved. Open 6-22 6.8.4.2 Forward work remains on the following to address the generic list of R&R Closed tasks to be captured in a future GGR&C list. At that time, those listed below that are in that category will migrate to the new GGR&C. A subset of the unique tasks for Flight 13A will remain. 6-23 6.8.4.2 Tool availability in question. Closed 6-24 6.4.2, 6.6.2, GGR&C CR to reduce medop allocation from 12 to 10 hours has not been Open 6.8.2 approved 6-25 6.4.2 Pending conclusion of discussions regarding location of the parent task. “It Open is included in the Annex 3 table for the purpose of training and crew time allocation.” 6-26 6.4.4.2, SAW retraction only approved safing method for SSU R&R. An SSU shunt Open 6.6.4.2 plug is under development and may be used as an EVA tool to safe the SSU for R&R. 6-27 6.4.4.2, The readiness of these tasks is based upon generic development of the Open 6.6.4.2, procedures to a level that can be validated against a set of criteria. 6.8.4.2 Definition and program agreement on the criteria determining generic task readiness needs to be resolved. Final development of these procedures will be required based upon actual configurations, locations and environmental conditions. 6-28 6.8.2 Assessment in work to move these s/w upgrades to Stage 12A.1 Closed
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TABLE C-2 TO BE RESOLVED ITEMS (PAGE 3 OF 3)
TBR Section Description Status 6-29 Table 3.3-1, Flight 13A EVA Team is assessing the ability to add this task. Open 6.6.2, 6.7.2 6-30 6.6.2, 6.8.2 In the event that Flight 13A does not launch in this increment, the high Open priority utilization allocations for this timeframe currently defined as Stage 12A.1 and 13A will be 6.0 hours per week and 20 hours per week, respectively. In the event that Flight 13A does not launch in this increment, the medium priority utilization allocation for the timeframe currently defined as Stage 13A will be 17 hours per week. In the event that Flight 13A does not launch in this increment , the high and the low priority PAO crew time allocations for the timeframes currently defines as Stages 12A..1 and 13A will be 2.5 hours per week, respectively.
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APPENDIX D
TOPOLOGIES
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D.1 GENERAL
This appendix provides an overview of the internal on-orbit topologies for Node 1, the US Lab, and the Joint Airlock. Figures are included for the planned rack locations. Subrack topologies are included for the EXpedite the PRocessing of Experiments to the Space Station (EXPRESS) Racks located in the US Lab.
D.2 ON-ORBIT RACK DESCRIPTIONS
Table D.2-1, On-Orbit Rack Descriptions
TABLE D.2-1 ON-ORBIT RACK DESCRIPTIONS
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D.3 NODE 1 TOPOLOGY
Figure D.3-1, Increment 14 Node 1 Topology, shows a high level overview of the Node 1 on-orbit topology during Increment 14. Refer to Table D.2-1 for a definition of the rack SE numbers.
AFTFORWARDZ1 TrussCupola*OVERHEADSTARBOARDDECKPORTNode 3** Shading indicates a future interfaceAirlockNOD1O4NOD1S4NOD1D4NOD1P4ZSRSE#110ZSRSE#116RSRSE#381ZSRSE#111
FIGURE D.3-1 INCREMENT 14 NODE 1 TOPOLOGY
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D.4 UNITED STATES LABORATORY TOPOLOGY
Figure D.4-1, Increment 14 United States Laboratory Topology, shows a high level overview of the US Lab on-orbit topology during Increment 14. Refer to Table D.2-1 for a definition of the rack SE numbers.
LAB1O1 LAB1O2 LAB1O3 LAB1O4 LAB1O5 LAB1O6
EXPRESS#2 EXPRESS#3 ZSR EXPRESS#1 MELFI DDCU#2 (ARIS) (ARIS) SE#117 OVERHEAD SE#14 SE#25 SE#9 SE#15 SE#16
Cupola MSS/ CCAA/ TESS HRF#1 MSG EXPRESS#5 Avionics & Moderate STARBOARD SE#27 SE#13 SE#18 SE#23 Console TCS SE#3 SE#12 LAB1S1 LAB1S2 LAB1S3 LAB1S4 LAB1S5 LAB1S6 FORWARD AFT
Avionics Avionics Window Temp Avionics #1/ ARS Cond H2O DECK #2 #3 CHeCS SE#8 SE#5 SE#6 SE#28 SE#4 LAB1D1 LAB1D2 LAB1D3 LAB1D4 LAB1D5 LAB1D6 LAB1P1 LAB1P2 LAB1P3 LAB1P4 LAB1P5 LAB1P6 Lab MSS/ PORT EXPRESS#4 HRF#2 ZSR DDCU#1 Avionics & CCAA/ SE#114 SE#17 SE#7 Console Low TCS SE#417 SE#2 SE#11
FIGURE D.4-1 INCREMENT 14 UNITED STATES LABORATORY TOPOLOGY
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D.5 JOINT AIRLOCK TOPOLOGY
Figure D.5-1, Increment 14 Joint Airlock Topology, shows a high level overview of the Airlock on-orbit topology during Increment 14. Refer to Table D.2-1 for definitions of rack SE numbers.
Cabin Air Equipment SE#193
A/L Avionics SE#194
FIGURE D.5-1 INCREMENT 14 JOINT AIRLOCK TOPOLOGY
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APPENDIX E
INCREMENT CONFIGURATIONS
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APPENDIX E - INCREMENT CONFIGURATIONS
The configuration plans for flight and stage are in JSC 26557, On-orbit Assembly, Modeling, and Mass Properties Data Book, also known as Blue Book, accessible through Electronic Document Management System (EDMS).
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APPENDIX F
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APPENDIX G
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APPENDIX H
ON-ORBIT CHECKOUT REQUIREMENTS [Items for Russian Review will be identified with (RUSSIAN)]
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APPENDIX H - ON-ORBIT CHECKOUT REQUIREMENTS
Appendix H contains a listing of those MSS OCRs that can be completed during this increment. All Tables have been scrubbed to eliminate completed OCRs or OCRs that cannot be accomplished within this increment. Table H-1 Part 1 of this plan contains SSRMS OCRs from the previous increment not completed and carried forward. Table H-2 contains MBS OCRs. Table H-3 contains MSS Periodic checkout tasks due for completion within this increment.
With the exception of Periodic and Conditional OCRs, the tasks in this matrix, as well as those planned in other increments, must be completed for CSA to consider the SSRMS and MBS fully commissioned.
Periodic/Data Trending checkout tasks are described where ‘start of life’ baseline data sets are required in this Increment. Periodic checkouts will be further addressed in the IDRDs for subsequent Increments.
Changes to requirements should be addressed to CSA via the Manager, Mission Operations. Changes to requirements during real-time operations should be addressed to the ISS Management Center.
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TABLE H-1 REMAINING SSRMS ON-ORBIT CHECKOUT REQUIREMENT TASKS FROM PREVIOUS INCREMENTS (PAGE 1 OF 2)
Checkout Description Type of OCR Required Priority and Required Operations- Comments Task (Note 3) Phase (Joint Operations/Stage (Note 4) Operations, Options) (Notes 5-8) One-Time Periodic Conditional Desirable Highly Mandatory Crew Time and Activation Desirable (Note 6) Special MCC/ISS/ Shuttle
From SSP 54102 Resources
Part 1: OCR Number (Notes 10-13) 6 FMS FMS data is collected at X Assembly 10 minutes Some data was characterization valuable dynamic motion operations additional crew collected during PP2 during nominal opportunities (i.e., pre- with time at each and PP4 data dynamic operations identified which provide large/heavy opportunity collection is highest (i.e., a constrained rich FMS data). payloads (concurrent with priority on LEE A tip APPC, heavy Required to close out handled by nominal/other Ops redundant string and payload SSRMS; like DTO 264 LEE B tip Prime NASA/CSA agreements stops/starts). until during Flight 9A string for which no for Waivers and CoFR complete payload loaded data has - For BITE check, Exceptions related to the maneuvers) been collected. truth model FMS/FMA validation Additional - Data from both opportunities will be identified and agreed strings and both LEEs required to serve for FMS raw or reported data (see comments for priorities) collection using Normal Format - Remaining LEE/ Telemetry, with EDD String or NDD desirable. combination This will also provide - LEE A - data for MDSF model Redundant validation, FMS BITE tolerance adequacy. - LEE B - Prime
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TABLE H-1 REMAINING SSRMS ON-ORBIT CHECKOUT REQUIREMENT TASKS FROM PREVIOUS INCREMENTS (PAGE 2 OF 2)
Checkout Description Type of OCR Required Priority and Required Operations- Comments Task (Note 3) Phase (Joint Operations/Stage (Note 4) Operations, Options) (Notes 5-8) One-Time Periodic Conditional Desirable Highly Mandatory Crew Time and Activation Desirable (Note 6) Special MCC/ISS/ Shuttle
From SSP 54102 Resources
Part 1: OCR Number (Notes 10-13) 45 SSRMS Thermal Thermal trending data X X FMS thermal drift Data Analysis has been collected on data is needed to both strings and LEEs. optimize and adjust FMS Thermal Drift Analysis of the data has the thermal Analysis indicated additional data compensation For FMS collections will be algorithm in the objectives, test is required: SSRMS software, as eventually required FMS Saturation well as to with each LEE as troubleshoot the LEE Troubleshooting tip (as well as both A Prime sensor strings). These will be detailed saturation issue. using the Chit process, Secondary Data collection for referencing this parent objectives; brief periods of LOS requirement. SSRMS Thermal during the selected FMS saturation Trending orbit will be troubleshooting was acceptable. Baseline data for performed on June 9/10, Required to close out thermal models 2003. One more test NASA/CSA LEE rigidize load remains to see if the FMS retains its calibration agreements for cell drift analysis waivers and CoFR status when temperature falls below 5 degrees exceptions related to the FMS/FMA. Celsius, and to check performance with the new Thermal Protection Kit. 57 Joint Direct Drive SSRMS Joints are driven X Within 1 year of 60 minutes crew Test using modified JCS to uplink of time (estimated); provide direct drive to required this could be motors. This will provide configuration reduced/ individual joint file changes eliminated with performance baseline for MSS Ground trending and degradation Control assessment.
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TABLE H-2 MRS BASE SYSTEM ON-ORBIT CHECKOUT REQUIREMENTS
Task Checkout Task Description Type of OCR Required Priority and Required Operations-Phase Comments Number (Joint Operations/Stage Operations, Options) One-Time Periodic Conditional Desirable Highly Mandatory Special Activation Desirable MCC/ISS/ Shuttle Resources
TABLE H-3 PERIODIC ON-ORBIT CHECKOUT REQUIREMENT TASKS
Checkout Description Type of OCR Required Priority and Required Operations-Phase Comments Task (Note 3) (Joint Operations/Stage Operations, Options) (Note 4) (Notes 5-8) One-Time Periodic Conditional Desirable Highly Mandatory Crew Time Activation Desirable (Note 6) and Special MCC/ISS/ Shuttle Task Number Resources (Notes 10-13) MSS Detection of CLA Determination of X Annually MCC-H only Setup details are in Camera and CLPA source of defects accordance with OCR 001 camera is accomplished CSA Camera OCR deterioration by viewing white Plans: SSRMS from Dead and black surfaces OCRs 001/003 and Pixels/ since this is where MBS OCR 001. Contamination/ defects are most Micrometeoroid apparent. Debris damage. Determination of source of defects is performed offline. MSS Determination of Cycle power to X Annually MCC-H only Set-up details are Camera whether a single camera lights in accordance with OCR 002 bulb has failed while observing CSA Camera OCR on the light via separate Plans: SSRMS assembly camera view. OCRs 002/004 and MBS OCR 002.
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APPENDIX I
SHUTTLE FLIGHT TRANSFER PRIORITY LIST [Items for Russian Review will be identified with (RUSSIAN)]
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APPENDIX I - SHUTTLE FLIGHT TRANSFER PRIORITY LISTS
I.1 12A.1 TRANSFER PRIORITY LIST
I.2 FLIGHT 13A MIDDECK LAUNCH AND RETURN PRIORITIES
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APPENDIX J
OFF-NOMINAL SITUATIONS [Items for Russian Review will be identified with (RUSSIAN)]
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APPENDIX J - OFF-NOMINAL SITUATION
TABLE J.1 FLIGHT 13 SOYUZ OFF NOMINAL SITUATIONS
TABLE J.2 STAGE 13 SOYUZ OFF NOMINAL SITUATIONS
TABLE J.3 FLIGHT 12A.1 OFF NOMINAL SITUATIONS
TABLE J.4 STAGE 12A.1 OFF NOMINAL SITUATIONS
TABLE J.4 FLIGHT 13A OFF NOMINAL SITUATIONS
TABLE J.4 STAGE 13A OFF NOMINAL SITUATIONS
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APPENDIX K
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APPENDIX K -
Table K-1, USOS Resources to be Provided for 13S Visiting Crewmember, is limited to the below-listed and agreed-to resources that NASA will provide to the 13S visiting crewmember during this mission on 13 Soyuz. The listing of utilization to be performed during the 13 Soyuz mission will be provided via Rocket Space Corporation - Energia (RSC-E) and is listed in the main document under Section 6.2.2
TABLE K-1 USOS RESOURCES TO BE PROVIDED FOR 13S VISITING CREWMEMBER
Resource Agreements E-mail None IP Phone None Timeline None Procedures None Lab Facilities None Ham None * Not solely a USOS resource - International Hardware Imagery None PAO None Medical None Crew Provisions: None Exercise Equipment None Video Down None Up/Downlink Data (includes OCA) None Ground Support None Preflight Crew Training for Prime and Standard Soyuz Visiting Crew training Backup 13S Visiting Crewmembers
K-2