SSP_54059_54060-Baseline.docx

Increment Definition and Requirements Document for Increments 59 and 60

International Space Station Program

Baseline

February 2019

EAR 99. This document contains data within the purview of the United States (U.S.) Export Administration Regulations (EAR), 15 CFR 730-774, and is export controlled. The document may be used only in the International Space Station (ISS) program to fulfill responsibilities of the Parties or of a Cooperating Agency of an ISS Partner in furtherance of the ISS Intergovernmental Agreement. Re-transfer or disclosure to, or use by, any persons other than citizens of ISS Program International Partner countries, or use for any other purpose, requires prior U.S. Government authorization..

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract Number: NNJ12GA46C

SSP 54059_54060

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REVISION AND HISTORY PAGE

PREFACE

increment definition and requirements document for Increments 59 and 60 This document is the Increment Definition and Requirements Document for Increments 59 and 60. 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).

International Space Station Program increment definition and requirements document for Increments 59 and 60 Concurrence February 2019

SEE DIRECTIVE APPROVAL

SEE DIRECTIVE APPROVAL

Kirk A. Shireman Manager, International Space Station Program National Aeronautics and Space Administration

Alexey A. Strelnikov Director, Department of Human Space Programs, State Space Corporation Roscosmos

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SEE DIRECTIVE APPROVAL

SEE DIRECTIVE APPROVAL

Ken Podwalski Program Manager Canadian Space Station Program

Bernardo Patti ISS Program Manager European Space Agency

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INTERNATIONAL SPACE STATION PROGRAM

increment definition and requirements document for Increments 59 and 60

CONCURRENCE

February 2019

INTERNATIONAL SPACE STATION PROGRAM

increment definition and requirements document for Increments 59 and 60

CONCURRENCE

February 2019

INTERNATIONAL SPACE STATION PROGRAM

increment definition and requirements document for Increments 59 and 60

CONCURRENCE

February 2019

Prepared by:

Nancy Monsees

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increments 59 and 60 Engineer org

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increments 59 and 60 manager org

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increment integration and operations manager

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mission integration and operations office manager

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TABLE OF CONTENTS

APPENDIX

TABLE

FIGURE

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Introduction Purpose This document provides the assignment of flight dates, resources and accommodations, as well as defines the requirements for Increments 59 and 60. Requirements are provided for both joint International Space Station (ISS)/mated vehicle operations and ISS-only continuous operations stages of the increments.

The schedule for products (i.e., documentation, reviews, etc.) that must be developed to support Increments 59 and 60 is found in the SSP 50489, ISS Mission Integration Template. The requirements contained herein shall be used in the execution of the flight and stage Certification of Flight Readiness (CoFR) processes carried out by each ISS supporting organization.

Scope This document covers Increments 59 and 60. Increment 59 begins the day of 58 Soyuz docking. Increment 59 ends with the undocking of 57 Soyuz. Increment 60 begins the day after undocking of 57 Soyuz. Increment 60 ends with the undocking of 58 Soyuz.

This document is based on the ISS Flight Program definition, as specified in SSP 54100, Multi-Increment Planning Document.

This document defines the capabilities and objectives of Increments 59 and 60. This document also controls resource and accommodation allocations; requirements and priorities for ISS execution planning; ISS manifest:

Increment Definition and Requirements Document for Increment 57, Annex 1: Station Manifest:

SSP 5405757S

SSP 5405771P

Increment Definition and Requirements Document for Increment 59, Annex 1: Station Manifest:

SSP 54059-58S

SSP 5405972P

SSP 54059-Boe-OFT

SSP 54059NG-11

SSP 54059SpX-17 SSP 54059-SpX-Demo2 Increment Definition and Requirements Document for Increment 60, Annex 1: Station Manifest:

SSP 5406059S

SSP 5406060S

SSP 5406061S

SSP 5406073P

SSP 54060-Boe-CFT

SSP 54060HTV8

SSP 54060NG-12

SSP 54060SpX-18 On-orbit maintenance operations (SSP 54059_54060-ANX2, Increment Definition and Requirements Document for Increments 59 and 60, Annex 2: On-Orbit Maintenance Plan and Operations Support) ISS imagery requirements (SSP 54059_54060ANX3, Increment Definition and Requirements Document for Increments 59 and 60, Annex 3: Imagery Requirements) Medical operations (SSP 54059_54060ANX4, Increment Definition and Requirements Document for Increments 59 and 60, Annex 4: Medical Operations and Environmental Monitoring) Payloads (SSP 54059_54060-ANX5, Increment Definition and Requirements Document for Increments 59 and 60, Annex 5: Payload Tactical Plan).

The above mentioned documents are published as separate documents and available in the Electronic Document Management System (EDMS) following ISS Program approval.

Precedence Information contained in this document shall be consistent with ISS Program documentation. If there are any discrepancies between this document and SSP 54100, SSP 54100 takes precedence. If there are any discrepancies between this document and the Consolidated Operations and Utilization Plan, 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 SSP 50200-02, Station Program Implementation Plan Volume 2: Program Planning and Manifesting. 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 54359_54360, Post Increment Evaluation Report for Increments 59 and 60 which will be published following increment completion.

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 Paragraph 3.4.

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.

Deviation/Waiver

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Documents Applicable Documents The following documents include specifications, models, standards, guidelines, handbooks, and other special publications. The documents listed in this paragraph are applicable to the extent specified herein. Inclusion of applicable documents herein does not in any way supersede the order of precedence identified in Paragraph 1.3 of this document.

The specific flight and/or Increment-related documents will be developed through the ISS change process and released into EDMS following ISS Program approval.

Volume 2: Program Planning and Manifesting Multilateral

(Note: This document will be published following increment completion.)

Multilateral

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.

Appendix: Dragon Cargo Interface Standard Requirements and Flight Environments

On-Orbit NASA Internal

Increment Introduction This section defines the Flight Program Summary, Increments 59 and 60 Summary, and also identifies existing or projected deviations to the Generic Groundrules, Requirements, and Constraints (GGR&C).

<Reserved> Increment FLight Summary Table 3.2-1, Increment Flight Summary, identifies planning data for all flights scheduled to visit the ISS during the increments.

The mission duration column lists the planned mission duration of each flight. The docked duration column lists the planned docked duration for each flight. Duration calculations are based on the calendar day difference between events.

All dates contained in Table 3.2-1 are shown in Greenwich Mean Time (GMT).

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Table 3.2-1 Increment Flight Summary (Page 1 of 3)

Increment 59 Definition

Vehicle/ISS

<FP TBR 3-8> Russian Flight Program is under review.

Launch occurs just prior to GMT midnight on 14 March 2019 with dock occurring just after GMT midnight on 15 March 2019.

<FP TBR 3-8>

Launch occurs just prior to GMT midnight on 14 March 2019 with dock occurring just after GMT midnight on 15 March 2019.

<FP TBR 3-90> Flight dates and durations are under review.

<TBR 3-3> USCV demonstration flights are for planning purposes only and have not been agreed to by Roscosmos.

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-8>

<FP TBR 3-8>

<FP TBR 3-90>

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-8>

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-8>

Table 3.2-1 Increment Flight Summary (Page 2 of 3)

Increment 60 Definition

Vehicle/ISS

<FP TBR 3-8> Russian Flight Program is under review.

Launch occurs just prior to GMT midnight on 04 July 2019 with dock occurring just after GMT midnight on 06 July 2019.

<FP TBR 3-8>

Launch occurs just prior to GMT midnight on 14 March 2019 with dock occurring just after GMT midnight on 15 March 2019.

<FP TBR 3-90> Flight dates and durations are under review.

<FP TBR 3-8>

<FP TBR 3-8>

<FP TBR 3-8>

Uncrewed Soyuz flight

<FP TBR 3-8>

<FP TBR 3-8>

<FP TBR 3-90>

<TBR 3-3> USCV demonstration flights are for planning purposes only and have not been agreed to by Roscosmos.

<FP TBR 3-90>

<TBR 3-3>

<FP TBR 3-8>

<FP TBR 3-90>

<TBR 3-3>

[1] HTV8 undock occurs in Increment 61.

<FP TBR 3-90>

Uncrewed Soyuz flight

<FP TBR 3-8>

Table 3.2-1 Increment Flight Summary (Page 3 of 3)

Increment 60 Definition

Vehicle/ISS

<FP TBR 3-8>

<FP TBR 3-8>

Increment Summary Increment 59 begins the day of 58 Soyuz docking, which increases the Expedition crew from three to six. The Expedition 59 crew consists of three crewmembers from 57 Soyuz and three crewmembers from 58 Soyuz. The 57 Soyuz crewmembers will have been on ISS as part of the Expedition 58 crew during Increment 58. Approximately 4 months into Increment 59, 57 Soyuz undocks ending Increment 59. The next day, Increment 60 begins with the three crewmembers from 58 Soyuz including the new Commander. These crewmembers will have been on ISS as part of Expedition 59 for approximately 4 months. Expedition 60 crewmembers increase to six with the docking of 59 Soyuz approximately 10 days later. Approximately 2.5 months into Increment 60 the uncrewed 60 Soyuz docks to the MRM2 port; 60 Soyuz remains docked to the ISS for approximately 12 days. Approximately 1 month after 60 Soyuz undocks, 61 Soyuz docks, increasing the ISS crew to eight. Approximately 3.5 months into Increment 60, 58 Soyuz undocks and Increment 60 ends.

Table 3.3-1, Increments 59 and 60 Crew Plan, identifies the Crew Plan.

TABLE 3.3-1 Increments 59 and 60 Crew Plan

Expedition 60 Crew

USCV Visiting Crew

Deviations to the Generic Groundrules, Requirements, and Constraints Document Deviations to SSP 50261-01 Identified for Increments 59 and 60 The following deviations to SSP 50261-01 have been identified for Increments 59 and 60:

A. SSP 50261-01, Section 13.1.1 Emergency Egress Path (Requirement) “The integrated ISS internal configuration within each applicable non laboratory module shall maintain a Non-Laboratory Crew Translation Path (CTP) during all ISS operations for routine (non-emergency) movement of the crew within the module. The Non-Lab CTP is defined as a 32 by 72 inch [81 by 183 centimeter (cm)] rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.2-1. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Non-Lab CTP at all times from hatch to hatch, while terminal module shall maintain a Non-Lab CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: ISS Experience protrudes into Emergency Egress Path (EEP) Effectivity: Increments 58 through 61 Refer to Rationale and Risk Mitigation in: Deviation # 20816 B. SSP 50261-01, Section 13.1.2 Non Laboratory Crew Translation Path (Requirement) “The integrated ISS internal configuration within each applicable non laboratory module shall maintain a Non-Laboratory CTP during all ISS operations for routine (non-emergency) movement of the crew within the module. The Non-Lab CTP is defined as a 32 by 72 inch (81 by 183 cm) rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.2-1. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Non-Lab CTP at all times from hatch to hatch, while terminal module shall maintain a Non-Lab CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: ISS Experience protrudes into Non-Lab CTPs.

Effectivity: Increments 58 through 61 Refer to Rationale and Risk Mitigation in: Deviation # 20816 C. SSP 50261-01, Section 13.1.3 Laboratory Crew Translation Path (Requirement) “The integrated ISS internal configuration within each applicable laboratory module shall maintain a Laboratory CTP during all ISS operations for routine (non-emergency) movement of the crew within the module. The Lab CTP is defined as a 50 by 72 inch (127 by 183 cm) rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.3 1. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Lab CTP at all times from hatch to hatch, while terminal modules shall maintain a Lab CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: ISS Experience Protrudes into Lab CTP.

Effectivity: Increments 58 through 61 Refer to Rationale and Risk Mitigation in: Deviation # 20816 D. SSP 50261-01, Section 13.1.3 Laboratory Crew Translation Path (Requirement) “The integrated ISS internal configuration within each applicable laboratory module shall maintain a Laboratory CTP during all ISS operations for routine (non-emergency) movement of the crew within the module. The Laboratory CTP is defined as a 50 by 72 inch (127 by 183 centimeters [cm]) rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.3 1. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Laboratory CTP at all times from hatch to hatch, while terminal modules shall maintain a Laboratory CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: Japan Aerospace Exploration Agency (JAXA) Mouse Missions Glove Box CTP Protrusion. The Glove Box will be deployed during the week before SpaceX (SpX) arrival for checkout and to ensure readiness for use immediately upon bringing the mice into the Japanese Experiment Module (JEM). The Glove Box will remain continuously deployed through the end of the SpX berthed mission.

Effectivity: Permanent Refer to Rationale and Risk Mitigation in: Deviation # 20782 E. SSP 50261-01, Section 13.1.3 Laboratory Crew Translation Path (Requirement) “The integrated ISS internal configuration within each applicable laboratory module shall maintain a Laboratory CTP during all ISS operations for routine (non-emergency) movement of the crew within the module. The Laboratory CTP is defined as a 50 by 72 inch (127 by 183 cm) rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.31. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Laboratory CTP at all times from hatch to hatch, while terminal modules shall maintain a Laboratory CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: The deployed Rodent Transporters with attached Animal Access Unit (AAU) for initial and second rodent transfer and emergency euthanasia operations result in violations of the CTP in the US Laboratory.

Effectivity: Valid during Rodent Research operations (planned or contingency).

Refer to Rationale and Risk Mitigation in: Deviation 20777_R2 F. SSP 50261-01, Section 13.1.3 Laboratory Crew Translation Path (Requirement) “The integrated ISS internal configuration within each applicable laboratory module shall maintain a Laboratory CTP during all ISS operations for routine (non-emergency) movement of the crew within the module. The Laboratory CTP is defined as a 50 by 72 inch (127 by 183 cm) rectangular path with 16 inch (40.6 cm) radius corners as shown in Figure 13.1.31. The path may bend and curve along the length of the modules and may be encroached upon by momentary protrusions, operating volume for crewmembers at worksites, and maintenance operations. Through modules shall maintain a Laboratory CTP at all times from hatch to hatch, while terminal modules shall maintain a Laboratory CTP from the hatch up to the portion of the module a crewmember can access.”

Violation: In all orientations examined, the Airway Monitoring payload setup protrudes into the Crew Translation Path of the US Laboratory in violation of the Laboratory Crew Translation Path as defined in SSP50261-01 Generic Groundrules, Requirements, and Constraints.

Effectivity: Violation is valid until the Airway monitoring science campaign is completed.

Refer to Rationale and Risk Mitigation in: Chit 15747 G. SSP 50261-01, Section 13.3.2 Localized Critical Controls (Requirement) “Visual Access to the Inter-module Ventilation (IMV) Remote Manual Override (RMO) shall be defined by a volume encompassing the base of the black ring of the IMV RMO and extending out 17.5 inches away from the panel as seen in Figure 13.3.2 -1. Physical access to the IMV RMO shall be defined by the ability of the crew to extend and rotate the IMV RMO handle through the full range of motion within 10 seconds. The time to extend and rotate the IMV RMO handle does not require on-orbit verification. The physical access volume required for full rotation of the extended IMV RMO handle is shown in Figure 13.3.2-1. Rigid hardware, such as hardware attached via seat track adaptors or requiring the use of tools or a procedure for removal, shall not be placed within the volume for manual IMV RMO access as this may impede manual IMV RMO operation within 10 seconds.”

Violation: Stowage blocks Node 2 IMV RMOs.

Effectivity: May 1, 2019 Refer to Rationale for Acceptance in: NCR-ISS-STO-N2-001 Rev. D H. SSP 50261-01, Section 13.3.2 Localized Critical Controls (Requirement) “Visual Access to the IMV RMO shall be defined by a volume encompassing the base of the black ring of the IMV RMO and extending out 17.5 inches away from the panel as seen in Figure 13.3.2 -1. Physical access to the IMV RMO shall be defined by the ability of the crew to extend and rotate the IMV RMO handle through the full range of motion within 10 seconds.“ Violation: Plant Habitat Growth Chamber Protrudes into the JEM IMV RMO Visual Access Volume.

Effectivity: Violation is valid while Plant Habitat is installed at EXpedite the PRocessing of Experiments for Space Station (EXPRESS) Rack (ER)-5 within JEM.

Refer to Rationale for Acceptance in: Chit 15793 (Approved at the ISS Mission Management Team (IMMT) on November 2, 2017).

I. SSP 50261-01, Section 13.3.4 Portable Fire Extinguishers (PFE), Portable Breathing Apparatuses (PBA), and Gas Masks (Requirement) “Access to PFEs, PBAs and gas masks which are typically mounted behind hinged doors in the modules, shall be defined by a free volume reserved to open the PFE and PBA doors and to remove the equipment. For locker based PBA/PFE stowage locations, the volume shall be described as the rectangular protrusion encompassing the PFE/PBA locker and door with the door open to its full swing envelope. For nonlocker based PFE/PBA stowage location, the volume shall be described as the minimum rectangular protrusion bounding the emergency equipment and restraints. The volume for both locker and non-locker based equipment shall be 28 inches (71 centimeters) deep.”

Violation: PFE and PBA in the JEM Experiment Logistics Module - Pressurized Section (JLP) overhead end are inaccessible with cargo stowed in the JLP.

Effectivity: Permanent Refer to Rationale for Acceptance in: NCR-JAXA-PMMN-0018 J. SSP 50261-01, Section 13.3.4 PFE, PBA, and Gas Masks (Requirement) “Access to PFEs, PBAs and gas masks which are typically mounted behind hinged doors in the modules, shall be defined by a free volume reserved to open the PFE and PBA doors and to remove the equipment. For locker based PBA/PFE stowage locations, the volume shall be described as the rectangular protrusion encompassing the PFE/PBA locker and door with the door open to its full swing envelope. For nonlocker based PFE/PBA stowage location, the volume shall be described as the minimum rectangular protrusion bounding the emergency equipment and restraints. The volume for both locker and non-locker based equipment shall be 28 inches (71 centimeters) deep.”

Violation: ISS Experience protrudes into PBA/PFE Keep Out Zone (KOZ)s and 12.8 inches when flexible hoses are extended to the greatest possible dimensions.

Effectivity: Increments 58 through 61 Refer to Rationale and Risk Mitigation in: Deviation # 20816 K. SSP 50261-01, Section 13.3.5 Fire Suppression Ports (Requirement) “Fire suppression port access shall be defined by the ability of the crew to insert the PFE nozzle to the fire suppression access port within 30 seconds. The time to access and insert the PFE nozzle into the fire port does not require on-orbit verification. The volume of a PFE is shown in Figure 13.3.5-1. Rigid hardware, such as hardware attached via seat track adapters or requiring the use of tools or a procedure for removal, shall not be placed over fire ports as this may impede access to the fire port within 30 seconds.”

Violation: JLP has a fire suppression port in the overhead end. It is inaccessible due to cargo stowed in the JLP.

Effectivity: Permanent Refer to Rationale for Acceptance in: NCR-JAXA-PMMN-0017 L. SSP 50261-01, Section 13.3.6 Crew Quarters (Requirement) “Access to Portable Fire Extinguisher (PFEs, PBAs and gas masks which are typically mounted behind hinged doors in the modules, shall be defined by a free volume reserved to open the PFE and PBA doors and to remove the equipment. For locker based PBA/PFE stowage locations, the volume shall be described as the rectangular protrusion encompassing the PFE/PBA locker and door with the door open to its full swing envelope. For non-locker based PFE/PBA stowage location, the volume shall be described as the minimum rectangular protrusion bounding the emergency equipment and restraints. The volume for both locker and non-locker based equipment shall be 28 inches (71cm) deep.”

Violation: ISS Experience protrudes into Crew Quarters KOZ.

Effectivity: Increments 58 through 61 Refer to Rationale and Risk Mitigation in: Deviation # 20816 M. SSP 50261-01, Section 13.7 A Hardware Operable Volume (Requirement) Irregular cadence that occurs during high force squat exercises place Advanced Resistive Exercise Device (ARED) bar in a configuration that could contact the Toilet Stall and Handrail Offset Bracket on the starboard seat tracks. However, nominal ops/rhythmic squats regardless of the load, do not nominally produce VIS motion that would result in contact between ARED and the Toilet Stall and Handrail Offset Bracket.

Violation: The handrail on the N3 Forward radial port starboard seat track is in violation of the ARED Hardware Operable Volume. A Handrail Offset Bracket will replace the current handrail configuration and will also cause a violation of the Hardware Operable Volume Requirement, though it will be a smaller, more localized protrusion.

Effectivity: Until installation of the port Universal Waste Management System (UWMS) toilet stall.

Rationale for Acceptance: WVR_20812 grants approval to both configurations and was approved at the 10/16/18 SSPCB.

N. SSP 50261-01, Section 9.1.2 Mission Duration (Requirement) Soyuz mission duration will be no more than 200 days calculated from launch to landing.

Violation: 57S is planned for 204 day duration; 58S is planned for 203 day duration.

Effectivity: 57S and 58S Refer to Rationale and Risk Mitigation in: Deviation # <TBR 3-2> Violations to SSP 50261-01 groundrules during Increments 59 and 60, if identified, are listed on the Increments 59 and 60 Management Team SharePoint site which can be found at https://iss.sp.jsc.nasa.gov/Int/OC/II/59-60/SitePages/Increment%2059-60%20Management%20Team.aspx.

ISS Altitude Strategy The ISS will perform reboosts as required and maintain the altitude strategy outlined in the Protocol between NASA and Roscosmos on Increasing ISS Altitude to 419 kilometers (km)s signed October 1, 2018. The following graph, Figure 3.5-1, shows an overview of the ISS altitude strategy for these increments per NASA/Roscosmos agreements.

Figure 3.5-1 ISS Altitude Profile

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On-Orbit Resource Assumptions and Allocations This section defines the allocation of the on-orbit ISS capabilities between systems and utilization across the increments. Allocations are limited to power, crew time, and onorbit accommodation which includes on-orbit stowage volume allocations. Sub-allocations of utilization allocations are provided in the SSP 54059_54060-ANX5. Any non-standard requirements of resources are also provided in Paragraph 4.4. The allocation guidelines are baselined in the SSP 5026101. All data contained in this section represent operational requirements.

Power Balance and Allocations Table 4.1-1, Power Balance and Allocations, summarizes ISS power capability for each flight/stage in the increments as power is generated by the Electrical Power Systems (EPS) of the United States On-orbit Segment (USOS), Functional Cargo Block (FGB), and Russian Segment (RS) for the Flight Attitude Plan specified. The table also shows the integrated systems demands and allocations for the three ISS EPS groups. The USOS power consumption includes the United States elements, the European Columbus elements, the JEM elements, and the Canadian robotics elements. The RS supply and distribution group includes the Russian elements of the ISS. The FGB includes only the FGB and, for analysis purposes, is considered to be separate from the RS.

Power consumptions are representative, and are based on assumed operational modes and the Flight Attitude Plan included in this table. The Flight Attitude Plan represents the attitudes for flights and stages approved by the Program which satisfy the positive energy balance requirement and optimize power availability for Utilization. It includes only X-axis into the Velocity Vector (XVV) Local Vertical Local Horizontal (LVLH) attitude. This plan does not contain attitudes used for proximity operations, stage Extravehicular Activities (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 XVV symbol in Flight Attitude Plan section of the table refers to an attitude defined as +X-axis toward the Velocity Vector with the +Z-axis Nadir.

The solar beta angle rates are divided into three categories: low, mid and high. Low Beta range is defined as |β|<= 37 degrees. Mid Beta range is defined as |β| >37 and <52 degrees. High Beta range is defined as |β|>=52 degrees.

Table 4.1-1 also shows power transfer in kilowatts (kW) between the power supply and distribution systems of the USOS, FGB, and RS for the Flight Attitude Plan specified. A primary purpose of this table is to identify power generation versus systems demand by the USOS, FGB, and RS and to identify how much power needs to be transferred during different flights and stages. The power transfer allocation values are based on RS and FGB core system power deficits. All values are from the output of the ISS USOS EPS. However, due to inability to limit power transfer via converters to the RS and FGB, numbers are shown in converter incremental values that reflect the maximum transfer capacity at the converter saturation point.

The RS power margins (allocations to utilization) are a result of USOS power transfers and are calculated as the difference in the total converter increment value transferred at the output of the converters and the core systems deficit for the identified time period. During real time operations the Mission Control Center - Houston (MCC-H) may consider cycling the converters to recover power transfer above allocation if needed, and the RS Mission Control Center - Moscow (MCC-M) will be notified in advance when cycling will be executed. During the pre-mission planning process and real time operations, 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.

The USOS power allocation to utilization will be sub-allocated to the NASA, European Space Agency (ESA), JAXA, and Canadian Space Agency (CSA) utilization programs through the Multilateral Research Integration Control Board (MRICB) and the allocations will be documented in SSP 54059_54060ANX5.

TABLE 4.1-1 POWER BALANCE AND ALLOCATIONS

(kW) Total Capability [1] Power Consumption (kW) Allocation to Systems [2] [4]

Allocation to Systems [2] Power Margin (kW) Allocation to Utilization

Increment 59_60

NOTES:

Generic

Flight/Stage Specific

Legend

L Low beta angle range

M Mid beta angle range

H High beta angle range

Crew Time Crew time calculation assumptions and allocations are based on SSP 50261-01 Appendix E, Crew Time Analysis Generic Groundrules.

Table 4.2-1, Crew Time Calculation Assumptions, shows the data used to calculate crew time capability.