FLIGHT REQUIREMENTS DOCUMENT STS-300images.spaceref.com/news/2004/NSTS 17462-300 Rev-005 09...NSTS...

NSTS 17462-300 Revision 005

FLIGHT REQUIREMENTS DOCUMENT STS-300 SEPTEMBER 02, 2004 Launch On Need (LON) Crew Rescue

National Aeronautics and Space Administration LYNDON B. JOHNSON SPACE CENTER HOUSTON, TEXAS


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DESCRIPTION OF CHANGES TO

STS-300 FLIGHT REQUIREMENTS DOCUMENT

CHANGE PAGES NO. DESCRIPTION/AUTHORITY DATE AFFECTED Basic Issue/F17462-300-01 02/17/04 All Rev. 002 General Revision

F17462-300-002; -003; -004 Cargo Arrangement Drawing

05/18/04 All

Rev. 003 General Revision

F17462-300-005; - 006; -007; -008; -009; -010 07/01/04 All


F17462-011; -012; -013 07/30/04 All


F17462-015; -016; -019; -020; -021 09/02/04 All


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STS-300

FLIGHT REQUIREMENTS DOCUMENT

SEPTEMBER 2004

This version of the STS-300 Flight Requirements Document (FRD) reflects all changes approved by the NASA Space Shuttle Program as of the publication date.

APPROVED: APPROVED: Original signed 9/2/04

Original signed 9/3/04

_______________________ _______________________ S. NAT HARDEE BILL H. HOLLISTER USA FLIGHT MANAGER FLIGHT MANAGEMENT AND INTEGRATION UNITED SPACE ALLIANCE

DIRECTOR FLIGHT MANAGEMENT AND INTEGRATION UNITED SPACE ALLIANCE


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FOREWORD

This document contains the approved requirements for the STS-300 International Space Station flight. Deviations from the requirements marked with a single or double asterisk will require PRCB approval. Comments or questions concerning this document should be addressed to the United Space Alliance (USA) Flight Manager: USH-700C/S. Nat Hardee at 281/280-6901.

Basic document signed 04/06/2004 _______________________ John P. Shannon Manager, Flight Operations and Integration Office


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TABLE OF CONTENTS PARA TITLE PAGE 1.0 INTRODUCTION ....................................................................................................... 1 1.1 Policy ........................................................................................................................... 1 1.2 Flight Objective ........................................................................................................... 1 1.3 Change Procedure ........................................................................................................ 1 2.0 APPLICABLE DOCUMENTS .................................................................................... 1 3.0 PRIMARY FLIGHT REQUIREMENTS .................................................................... 4 3.1 General Flight Requirements ....................................................................................... 4 3.2 Cargo Requirements/Arrangement ............................................................................... 7 3.3 Space Shuttle Vehicle Configuration Requirements .................................................... 8 3.4 Integrated Activity/Functional Requirements ............................................................ 13 3.5 Flight Design Requirements ....................................................................................... 14 4.0 PLACARDS/CONSTRAINTS/LIMITATIONS ....................................................... 14 4.1 Integrated Orbiter/Crew/Payload Constraints/Limitations ......................................... 14 4.2 Space Shuttle Placards/Constraints/Limitations ........................................................ 15 5.0 SUPPLEMENTAL REQUIREMENTS ..................................................................... 15 5.1 Development Test Objectives .................................................................................... 15 5.2 Detailed Supplementary Objectives ........................................................................... 15 5.3 Human Exploration and Development of Space Technology Demonstrations ..................................................................................... 15 5.4 Data Collection .......................................................................................................... 16 6.0 PRIORITIES .............................................................................................................. 16 6.1 Generalized Priorities ................................................................................................. 16 TABLES TABLE TITLE PAGE 1 Vehicle Configuration .................................................................................................. 8 2 Mission Support Equipment/Configuration ................................................................. 9 3 Non-Standard Items ................................................................................................... 13 FIGURES FIGURE TITLE PAGE 1 Cargo Arrangement .................................................................................................... 16


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APPENDICES APP TITLE PAGE A Retired (The Level A Groundrules and Constraints is a contractor deliverable and is published under separate cover.) B POWER, VIDEO AND DATA PLUG-IN PLAN ......................................................B-1 (Published after Crew Compartment Configuration Review (CCCR)) APPENDIX B PARA TITLE PAGE 1.0 INTRODUCTION .................................................................................................... B-1 1.1 Purpose ...................................................................................................................... B-1 1.2 Scope ......................................................................................................................... B-1 1.3 Change Procedure ..................................................................................................... B-1 1.4 Power Panel Reference ............................................................................................. B-1 2.0 PRE-ROUTED .......................................................................................................... B-1 3.0 ASCENT AND ENTRY ........................................................................................... B-1 4.0 ON-ORBIT ............................................................................................................... B-1 TABLE TABLE TITLE PAGE 1 Video Table .............................................................................................................. B-7 FIGURES FIGURE TITLE PAGE 1 Power Panel Reference ............................................................................................ N/A 2 Power Data Video - Pre-Routed ............................................................................... N/A 3-1 Power - Ascent ......................................................................................................... N/A 3-2 Power - Entry ........................................................................................................... N/A 4-1 Power - On-Orbit ...................................................................................................... N/A


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1.0 INTRODUCTION

1.1 Policy This document defines explicitly, or by reference, the Space Shuttle Program (SSP) authorized requirements to be implemented on the STS-300 Launch on Need (LON) Crew Rescue flight. Products generated to satisfy these requirements shall meet the schedules defined in the Flight Definition and Requirements Directive (FDRD), NSTS 07700 Volume III, and in the appropriate Integration Plans (IP’s). 1.2 Flight Objective The primary objective of the Launch on-Need (LON) Crew Rescue flight is to return a stranded STS-114 crew of 7 from the International Space Station (ISS) safely to earth within 90 days of this declared contingency. The LON flight would utilize the STS-121 vehicle (OV-104)/payload configuration without any payloads. The minimum turnaround from LON callup is 35 days. This is driven by pad turnaround with only one pad available (which is the case for ’04 and early ’05), the standard Flight Design I-Load Uplink/Day of Launch (DOL) processes, and training requirements. The payload bay will be configured without any payloads, but some residual cargo integration hardware may remain on the LON flight. The crew compartment will be configured with additional seats to support the return of up to 11 crewmembers. 1.3 Change Procedure All changes to this document will be processed in accordance with the procedures defined in the Configuration Management Requirements, NSTS 07700, Volume IV. 2.0 APPLICABLE DOCUMENTS The following documents of the current issue, or as specified, are applicable:

NSTS 07700 Volume II, Book 3

Space Shuttle Program International Space Station Program Memorandum of Agreement (SSPIA) No. 39 (latest rev)

NSTS 07700 Volume III

Flight Definition and Requirements Directive Ref.: Paragraphs 1.1 and 3.0

NSTS 07700 Volume IV

Configuration Management Requirements Ref.: Paragraph 1.3

NSTS 07700 Volume X, Book 3

Flight and Ground System Specification Ref.: Paragraph 3.1

NSTS 16725 Flight Test and Supplementary Objectives Document (FTSOD)

Ref.: Paragraphs 3.2, 3.3, 5.1, 5.2, 5.3, and 5.4


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NSTS 21000-IDD-ISS International Space Station Interface Definition Document NSTS 21075 Space Shuttle Operational Flight Design Standard Groundrules and

Constraints (Level B) Ref.: Paragraph 3.5

NSTS 21418 Remote Manipulator System Sideview Camera Integration Plan (IP)

Ref.: Paragraph 3.3 NSTS 21429 Operational Digital Television Integration Plan (IP)

Ref.: Paragraph 3.3 NSTS 21458 Standard Integration Agreement for all Space Shuttle Program and

International Space Station Program Missions Ref.: Paragraph 4.1

NSTS 21519 Launch On Need Crew Rescue Flight Mission Integration Plan (MIP)

and Annexes 1, 4, ICA, 8, OMRSD and TGHR Ref.: Paragraphs 3.1 and 3.2

NSTS 37389 Space Shuttle Systems Requirements Document (SRD) for the Enhanced

Launch Vehicle Imaging System (ELVIS) Ref.: Paragraphs 3.1 and 3.3

DATA-44 STS-300 Level A Groundrules and Constraints

Ref.: Paragraphs 3.1 and 3.5 JSC 08934 Shuttle Operational Data Book

Ref.: Paragraph 4.2 JSC 28056 Shuttle/ISS Video Processing Unit (VPU) Requirements and Definition

Document Ref.: Paragraph 3.3

JSC 28290 Video Processing Unit (VPU)/Wireless Video Systems (WVS) Interface

Box (WIB) Interface Control Document (ICD) Ref.: Paragraph 3.3

JSC 29097 Project Technical Requirements and Verification Matrix for the Micro-

Triaxial Accelerometer Unit (Micro-TAU) and Micro-Strain Gauge Unit (Micro-SGU) Ref.: Paragraph 3.3

SGD32100594 Crew Compartment Configuration Drawing (CCCD) Core

Ref.: Paragraph 3.3 SGD32104491 STS-300 Crew Compartment Configuration Drawing

Ref.: Paragraph 3.2 TDDP-300 Trajectory Design Data Package

Ref.: Paragraph 3.5


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V072-201000 Mission Equipment Cargo Support Launch Site Installation (MECSLSI) - ISS Standard Ref.: Paragraphs 3.0, 3.2, and 3.3

V072-200XXX STS-300 MECSLSI

Ref.: Paragraph 3.2 ICD-A-21264 Shuttle Orbiter/OIU Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-21293 Tools for Rendezvous and Docking (TRAD)

Ref.: Paragraph 3.3 ICD-A-21321 Shuttle Orbiter/APCU Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21342 Shuttle Orbiter/ODS-ISS Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21402 Shuttle Orbiter/Stand Alone Acceleration Measurement Device (SAAMD)

and Wideband Stand Alone Acceleration Measurement Device (WBSAAMD) Cargo Element Interfaces Ref.: Paragraph 3.3

ICD-A-21403 Shuttle Orbiter/SSV Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21418 Shuttle Orbiter/RSC Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21420 Shuttle Orbiter/VPU Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21429 Shuttle Orbiter/Digital Television (DTV) Cargo Element Interfaces

Ref.: Paragraph 3.3 ICD-A-21449 Shuttle Orbiter/Minicam/Downlink Cargo Element Interfaces

Ref: Paragraph 3.1 ICD-A-21519-OOR Mission ISS-Launch On Need Crew Rescue Shuttle/ISS On-Orbit

Interface Requirements Ref.: Paragraph 3.2

ICD-3-0018-08 Orbiter Boom Sensor System (OBSS)

Ref.: Paragraph 3.3 ICD-3-0029-08 Camera Installation - Separation Monitor, ET/Orbiter

Ref.: Paragraph 3.3


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ICD-3-0049-17 Micro-Wireless Instrumentation System (Micro-WIS) Triaxial Accelerometer Unit (Micro-TAU), Strain Gauge Unit (Micro-SGU) and Wide-band Micro-TAU (WB Micro-TAU) Ref.: Paragraph 3.3

ICD-3-0049-19 Wing Leading Edge (WLE) Enhanced Wide Band Micro-Triaxial

Accelerometer Unit (EWB MTAU) Ref.: Paragraph 3.3

ICD-3-0057-01 Wireless Video System (WVS)

Ref.: Paragraph 3.3 ICD-3-0061-16 Space to Space Orbiter Radio (SSOR)

Ref.: Paragraph 3.3 3.0 PRIMARY FLIGHT REQUIREMENTS Flight Definition and Requirements Directive (FDRD) controlled requirements are indicated by a single asterisk (*). Requirements impacting ISS Vehicle standardization (reference ISS Std MECSLSI V072-201000, PRCB Directive S061487, PRCB Directive S061751, and DMICB CR M8863) are indicated by a double asterisk (**). Changes to either single or double asterisk items are under PRCB control. 3.1 General Flight Requirements

a. Launch Date: No earlier than (NET) May 05, 2005* Eastern Daylight Time (EDT) / NET TBD Greenwich Mean Time (GMT) but No Later Than (NLT) callup + 90 days.

b. Launch Window: The launch time on NET May 05, 2005* is TBD EDT which is NET

TBD GMT. The launch window duration is 10 minutes. Detailed launch window information is included in Level A Groundrules and Constraints. The launch window will not be restricted by lighted launch or Beta constraints. c. Launch Period: The launch period begins 10 minutes before the launch window opens and

ends 10 minutes after the launch window closes. d. Launch Site: John F. Kennedy Space Center (KSC), Pad B*, MLP-3*

e. Inclination: 51.6 degrees*

f. Altitude: Insertion altitude (direct insertion*) 122 nautical miles (nm)* Perigee 85 nm ISS Stage rendezvous altitude 190 nm g. Space Shuttle Main Engine (SSME) Performance Plan: 104.5% nominal*,

104.5% intact abort*


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h. Crew Size: 4 up/11 down* Workshift: single shift i. Flight Duration: 6+2+2 *. Nominal duration is 6 days with 2 docked days. The capability

will be provided for 2 fully operational backup days (additional docked days) for off-nominal mission activities or Flight Day (FD) 4 rendezvous. Consumables, crew provisions, and planning will assume a FD 3 rendezvous. Rendezvous phasing limit calculations will also protect FD4 rendezvous capability from either a FD 3 or FD4 launch pane. The capability will also be provided for two additional days for orbiter contingency operations and weather avoidance.

j. Landing Sites:

1. Nominal End-of-Mission (EOM): Primary - KSC*

First Alternate - Edwards Air Force Base (EAFB) Second Alternate (Backup weather alternate) - White Sands Space Harbor (WSSH)

2. Aborts:

(a) Return to Launch Site (RTLS): KSC

(b) Transoceanic Abort Landing (TAL): Primary - Zaragoza*, Alternates - Moron and Istres

(c) Abort-Once-Around (AOA): Primary - KSC, Alternate - WSSH

(d) Emergency: The Emergency Landing Sites (ELS) available for this flight are

listed in the Level A Groundrules and Constraints. Reference NSTS 07700 Volume X, Book 3, for specific information on all Space Shuttle Landing Sites.

k. Flight-Unique Ground Support Requirements

Note: For each payload, detailed handling requirements are controlled by the MIP/PIP and/or Annexes 8 and OMRSD and/or mission-unique Time-critical Ground Handling Requirements (TGHR) table.

1. Launch Site Support Requirements:

(a) The capability to deploy the radiators on orbit is required. 2. Landing Site Support Requirements:

(a) None identified 3. Flight Unique Ferry Requirements:

(a) None identified


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l. Extravehicular Activity (EVA): Crew provisions shall support the performance of 2 two-crewmember EVA's to accomplish the following contingency EVA tasks. There are no scheduled or unscheduled EVAs. Orbiter consumables for the two orbiter based contingency EVA's will be taken from the consumables budgeted for the contingency hole in cabin (GN2) and the two orbiter contingency and weather avoidance days (O2).

1. Zero scheduled EVA's 2. Zero unscheduled EVA's 3. Two orbiter based contingency EVA's, if required, to perform the following

contingency tasks: (a) Release ODS Capture latches (b) Stow radiators (c) Close and/or latch the payload bay doors (PLBD) (d) Realign the Ku-band antenna gimbals (e) Perform an SRMS joint alignment, an SRMS and/or Boom tiedown, or an

MPM stow. (f) Manually release the SRMS or SSRMS grapple fixture, as applicable, in

support of the cargo element (CE) berthing and stage berthing (g) Manually separate the Orbiter Docking System (ODS) from the ISS along

the 96-bolt interface plane. (Note: The 96-bolt tools are stowed on the Node following ISS-2A mission.)

(h) TPS Repair

m. Television and Photography Requirements:

1. Live television (TV) downlink or video tape recorder (VTR) taping and/or downlink of crew activities and spacecraft functions, (especially those associated with payload deployment and functions) are required for documentary purposes. A window of opportunity for PAO events of up to 30 minutes of the appropriate communication coverage is required on each full, non-EVA, non-rendezvous flight day to accomplish these objectives. In addition, when possible, TV views of the Earth from orbit should be obtained.

2. Still photography of crew activities in the orbiter, spacecraft functions,

accommodations, and mission-related scenes of general public and historical interest is required for documentary purposes. Photos of Earth views should be obtained by the crew.

3. Provide the capability to record minicam video during ascent (Aft location looking

forward). 4. Provide the capability to document flight crew ingress into the orbiter on launch day

using live drag-on GSE TV. 5. Provide the capability to record and downlink minicam or video during descent and

landing (Heads Up Display (HUD) Bracket). 6. Umbilical Well Camera Photography (Motion and Still)


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(a) High speed motion photography using two 16 mm film umbilical well cameras is

required for post flight imagery analysis of SRB and ET configuration and separation.

(b) High resolution still photography using the umbilical well still camera is required

for post ET separation imagery analysis of the ET TPS and ET configuration. Any acquired digital still imagery of the ET shall be retrieved from the umbilical camera by the crew via laptop interface and downlinked within 24 hours after ET separation to enable early inspection of the ET for potential debris sources or anomalous events.

(c) An 11 second +X translation maneuver is required to obtain enhanced high-

resolution photography using umbilical well cameras. 7. The ET shall be photographed using a crew handheld digital still camera with 400

mm lens and video camcorder beginning as soon as possible following ET separation and continuing up to 20 minutes after ET separation. Following the new MPS dump pitch maneuver, the crew will record imagery of all attainable ET surfaces dependent upon ET tumbling and favorable lighting. Any acquired digital still and video imagery of the ET shall be downlinked within 24 hours after ET separation to enable early inspection of the ET for potential debris sources or anomalous events.

3.2 Cargo Requirements/Arrangement a. Cargo Requirements:

1. Deployable: (a) None identified

2. Retrievable:

(a) None identified

3. Attached: (a) Reference Table 2 item 3

4. Crew Compartment:

(a) None identified b. Cargo Arrangement:

Development Test Objectives (DTO’s), Detailed Supplementary Objectives (DSO’s), and Human Exploration and Development of Space (HEDS) Technology Demonstrations (HTD’s) hardware flying in the cargo bay should be baselined at the appropriate Configuration Control Board (CCB) no later than Cargo Integration Review (CIR) or 2 weeks after manifest approval by the Flight IPT, whichever is later. DTO /DSO/HTD hardware flying in the crew compartment should be baselined at the appropriate CCB not later than launch minus (L-) 120 days or 2 weeks after manifest approval by the Flight IPT, whichever is later. Note that hardware flying in a Spacehab/MPLM may have to be baselined earlier to support hardware delivery dates.


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1. Payload Bay Reference - MECSLSI V072-200XXX (See Figure 1) and MECSLSI V072-201000 2. Crew Compartment Reference - Crew Compartment Configuration Drawing SGD32104491

Stowage requirements for manifested payloads can be found in the appropriate MIP’s, PIP’s, and Interface Control Annexes (ICA’s). Stowage requirements for DTO’s/DSO’s/ and HTD’s can be found in the FTSOD, NSTS 16725. Stowage requirements for EVA support equipment can be found in the flight-specific EVA Support Equipment List (ESEL) managed by the EVA Project Office. The cable interfaces with the orbiter for power (ascent/descent and on-orbit), video and data are documented at the Crew Compartment Configuration Review in the form of plug-in plans and video table, which are found in Appendix B, Power, Video and Data Plug-In Plan. (a) Unique stowage requirements for this flight are noted below:

(1) An additional 0.5 MLE is required to accommodate the Flight Data File stowage.

(2) Crew Support Locker 1 MLE

(3) The following middeck payloads require approximate, flight-unique

stowage as noted: None identified (4) The following DTO's /DSO's/HTD’s require approximate, flight-

unique stowage as noted: None identified

3.3 Space Shuttle Vehicle Configuration Requirements

The following matrices lists the flight-unique configuration and support equipment required for this flight. Directives from LSRRs/LSFRs/Delta LSFRs, Noon PRCBs, and DMICBs authorize the flight specific mission/mods for Shuttle Elements (Orbiter, ET, SRB, and RSRM), e.g. the ET/SRB ELVIS configuration, for implementation in mission unique MECSLSI and CCCD.

a. Vehicle Configuration TABLE 1

Item Comments 1. Orbiter OV-104* Flight Number: 27 2. External Tank ET-121* 3. Solid Rocket Boosters BI-125* 4. Redesigned Solid Rocket

Motors RSRM-92*


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5. SSME TBD* TBD* TBD*

Position 1 Position 2 Position 3

6. Software OI-30 * 7. Cryo Tank Sets 5* ** No-offload 8. Gaseous Nitrogen Tanks

(GN2) 6* ** No-offload

System 1, tanks 2,3,4 ** System 2, tanks 1,2,4 **

b. Mission Support Equipment/ Configuration The integration documentation for manifested cargo (reference paragraph 3.2) and the

FTSOD, NSTS 16725 for manifested DTO’s, DSO’s and HTD’s (reference paragraph 5.0) specify payload-, SSP-, ISSP- and sponsor-provided hardware required for the flight. Only those requirements that involve an orbiter configuration (e.g., an aft flight deck panel) or necessitate a flight-integrated requirement (e.g., Payload and General Support Computers (PGSC’s)) will be duplicated in this document. Location Column

F = Forward (Forward of Xo 576) M = Midbody (Between Xo 576 and Xo 1307) A = Aft (Aft of Xo 1307) I = Integrated components (various locations)

Applicability Column R = Required for mission objectives I = Not required for mission objectives but planned to be left installed NI = Not installed TBD = To be determined

TABLE 2

Nomenclature Loc App Specific Requirements 1. 400 mm Lens F R 2. Airlock Booster Fan M R** 3. Assembly Power Converter

Uints (APCUs) M R** Quantity: 2**

Config. K 4. Avionics Bay 3A Fan F R** Low Power Ballast 5. Aft Fuselage A R Boxes required.** TBD lbs 6. Bay 13 M NI Cameras CTVC=Color Television Camera;

ITVC=Intensified Television Camera (black and white)

7. A (port forward) M R CTVC 180 White Illuminator 8. B (port aft) M R ITVC 180 White Illuminator


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9. C (starboard aft) M R CTVC 180 White Illuminator 10. D (starboard forward) M R CTVC 180 White Illuminator 11. Payload Ops camera M I 12. SRMS elbow camera M R CTVC 180 White Illuminator 13. SRMS wrist camera M R CTVC 40 White Illuminator 14. ODS truss camera M NI 15. Centerline Airlock

Camera (stowed) F R CTVC (quantity 2: 1 prime, 1 backup)

16. Lefthand Umbilical Camera (forward)

A R 16 mm Motion/10 mm Lens

17. Lefthand Umbilical Camera (aft)

A R 16 mm Motion/5 mm Lens

18. Righthand Umbilical Camera

A R Digital Still/35 mm Lens

19. Computer Interface Panel (CIP) F NI** 20. Core Crew Compartment

Equipment plus consumables/equipment to support the full flight duration and crew complement

F R Ref: CCCD Core SGD32100594

21. Core Crew Compartment Equipment - Removals

F NI

22. Deployment Pointing Panel (DPP)

F NI**

23. Digital Television (DTV) F R** Configuration 1, Ref.: ICD-A-21429 24. Docking Lights M R** 2 on ODS truss, 1 on ODS Vestibule ** 25. Extended Duration Orbiter

(EDO) Pallet M NI**

26. External Airlock M R** 27. Extravehicular Mobility Unit

(EMU) F R Quantity: 2

28. EVA Safety Tethers M R** 1 to port, 1 to starboard ** 29. Global Positioning System

(GPS) Miniature Airborne GPS Receiver (MAGR), Single String

F R No PGSC

Hatches 30. 576 Bulkhead M R** B hatch 31. External Airlock - Top M R** D hatch 32. External Airlock - Aft M R** B hatch 33. Tunnel Adapter

Assembly (TAA) - Top M NI

34. TAA - Aft M NI 35. Internal Airlock -

Forward F NI


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36. Heads Up Display (HUD) - Spare

F NI

37. High Intensity Spot Light (HISL)

M NI

38. Internal Airlock F NI 39. Iodine Removal F R GIRA 40. Ku-Band Antenna M R** 41. Lightweight Crew Compartment F R Lockers, trays, pallets and LiOH soft bags 42. Lithium hydroxide (LiOH)

canisters F R 48 total (to support 4 crewmembers for 3

days and 11 crewmembers for 8 days (6+2+3 duration), N/A payload animals, or N/A payload CO2 limit) Stowage locations: 48 stowed/installed in middeck.

43. Manipulator Controller Interface Unit (MCIU) - spare

F R

44. MCIU/RMS Situational Awareness Display (RSAD)

F R**

45. Operational Sleep Station F NI 4 - tier 46. Orbiter Space Vision System

(OSVS) I NI 10 Targets will remain installed: 5 on

starboard and 5 on port wire tray covers located in bay 13.

47. Orbiter Docking System (ODS) M R** Configuration 1 48. Orbiter Interface Unit (OIU) F R** 2 in panel L11 ** 49. Oxone Hose Section F R Quantity: 8 50. Payload and General Support

Computer (PGSC) and related cables and equipment

F R 6 Total including Core, TRAD and unique 2-PGSC (760XD) with expansion unit, PCMMU board 1-PGSC (760XD) with expansion unit, OCA board 1-PGSC (760XD) with expansion unit, Proshare board 2-PGSC (760XD)

51. Payload Bay Liner/Bolt Hole Covers

M NI** Not required, but may remain partially installed

52. Payload Data Interface Panel (PDIP)

F R** 1 in panel L11, 1 in panel L12 **

53. Payload Data Interleaver (PDI) -spare

F R

54. Payload Interrogator (PI) F NI 55. Payload Recorder F NI** MMU installed to support payload

recording 56. Portable Foot Restraint (PFR) M NI Orbiter Fwd Bulkhead PFR Bracket

(approximately 2 lbs) remains installed 57. Portable Inflight Landing

Operations Trainer (PILOT) F NI


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hand controller and support hardware (stowed)

58. Provision Stowage Assembly (PSA)

M NI**

59. Regenerable Carbon Dioxide Removal System (RCRS) and LiOH canisters for minimum duration flight (MDF)

F NI

60. Sequential Still Video (SSV) I R** Configuration 3 61. Shuttle Remote Manipulator

System (SRMS) M R**

62. SRMS display and control equipment

M R**

63. SRMS Manipulator Positioning Mechanisms (MPM)

M R**

64. Simplified Aid for EVA Rescue (SAFER)

F NI

65. Slidewire(s) M R Short, Port Side Only 66. Small Payload Accommodations

Switch Panel (SPASP) F R** SPASP and OSVS Patch Panel (OPP)

required in support of OBSS. 67. Standalone Acceleration

Measurement Device (SAAMD)I NI May remain installed from STS-121 flow.

68. Standard Switch Panel (SSP) F R** 2 in panel L12 ** Stowage accommodations: 69. Item Removed 70. Item Removed 71. Middeck (MDK) stowage

bags - small (5-MLE) F R Quantity: 4

72. MDK stowage bags - large (10-MLE)

F NI

73. Ext A/L Floor bag (5-MLE)

F R

74. Aft Flight Deck (AFD) Generic Stowage Containers

F R 1 in panel L10

75. Middeck Accommodations Rack (MAR)

F R Lightweight

76. Seat bags F NI 77. Volume B F R 78. Volume D F R Depends on vehicle (Not available on OV-

103) 79. Volume F F R Stowage not authorized 80. TACAN cooling F NI TBD 81. Tools for Rendezvous and

Docking (TRAD) I R** Configuration F

(F=1 Trajectory Control Sensor (TCS)**, 2 HHL's, and 1 PGSC)


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82. Tool Stowage Assembly (TSA) M R** Port lightweight**, Starboard lightweight TBD

83. Tunnel Adapter Assembly (TAA)

M NI

84. TV Controller Unit F R** 85. Video Processing Unit (VPU) F R** 1 in panel R12** with Orbiter to ISS Video

Jumper 86. Winches M R** 87. Wireless Video System (WVS) I R** Antennas: (7) S-Band - port and starboard at

Xo=588, Xo=759, Xo=1126, and (1) at Xo=1307; UHF Antenna 1 at location Xo=684** (ODS truss) WIB: Spread Spectrum Transceiver (Panel R12)

88. Modular Auxiliary Data System (MADS)

F R Reference Section 5.4

89. Space to Space Orbiter Radio (SSOR)

M R 1 UHF antenna at Xo=684 on ODS truss

c. Non-Standard Items:

TABLE 3 Nomenclature Loc App Specific Requirements 1. Orbiter Boom Sensor System

(OBSS) M R Config. 2

2. MPS Flowliner Wide-band

Micro-Triaxial Accelerometer Unit (TAU)

A R 9 Measurement locations (9 Triaxial Accelerometer Blocks and 12 WB Micro- TAU Sensor Units), Ref.: ICD-3-0049-17

3. Station Power Distribution Unit (SPDU)

M R Provide APCU power for OBSS System

4. RMS Sideview Camera (RSC)

M R Videospection Camera Config. 3, Ref.: IP NSTS 21418

5. Aft Thrust Structure Micro-Strain Gauge Unit (SGU)

A R 12 Sensor Locations; Ref.: ICD-3-0049-17

Item deleted 6. Wing Leading Edge (WLE)

Instrumentation - Left Wing I R 66 Accelerometers, 22 Temp RTDs, 22

Sensor Units, 2 Relay Units; Ref.: ICD-3-0049-19

7. Wing Leading Edge (WLE) Instrumentation - Right Wing

I R 66 Accelerometers, 22 Temp RTDs, 22 Sensor Units, 2 Relay Units; Ref.: ICD-3-0049-19

3.4 Integrated Activity/Functional Requirements

a. Payload Deployment Requirements: None identified


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b. Rendezvous/Retrieval Requirements: None identified c. Crew Compartment/Attached Payloads Requirements: None identified d. Payload Prelaunch Simulation: Not required

3.5 Flight Design Requirements

a. Groundrules and Constraints:

The flight-unique groundrules and constraints are defined in the Level A Groundrules and Constraints, and published under separate cover by the contractor. The STS Operational Flight Design Standard Groundrules and Constraints, NSTS 21075, defines the standard Level B Groundrules and Constraints which are applicable, except for those additions or changes defined in the Level A’s.

b. Space Shuttle Operational Data:

1. The official SSP data to be used for design of this flight are contained in the Trajectory Design Data Package as specified in Level A Groundrules and Constraints. 2. Crew Compartment ascent weight for mass properties assessment is 7,600 lbs. but goes to status weight after delivery of the Uplink TDDP unless the flight specific IPT directs otherwise. The Crew Compartment entry

weight for mass properties assessment is 9,400 lbs. 3. Supply water tanks: 180 lb offload. 4. Protect propellant for FD3 to FD4 Rendezvous. 5. Forward RCS: full

c. Ascent Flight Design Requirement:

The following parameters will be used for the ascent trajectory design requirements:

1. Q Design Season/Design Month: Summer/May 2. Q Target: PE Low Q 3. Alpha: PE Max Alpha

4. Performance Enhancement Items: 52 nm MECO Del Psi 5. OI-30 Abort Performance Enhancements: Off

4.0 PLACARDS/CONSTRAINTS/LIMITATIONS 4.1 Integrated Orbiter/Crew/Payload Constraints/Limitations The following constraints are required to assure that the operations of one flight element (orbiter, crew, or payload) will not result in adverse effects on another flight element or adverse effects on itself because of the presence of other flight elements.


15

a. Cargo Radio Frequency (RF) Constraints: 1. Ku-band Constraints: Reference NSTS 21497 Section 4.2.4 and Reference 21458, SIA. 2. S-band Constraints: Reference NSTS 21497, Section 4.2.4 and Reference 21458, SIA. b. Payload Bay Light Constraints: None c. Fuel Cell Performance Requirements: None. 4.2 Space Shuttle Placards/Constraints/Limitations The following are constraints on this flight that are more restrictive than the baseline design. This does not necessarily reflect all constraints, limitations, or placards on the Space Shuttle at this time, but are those of primary concern to this flight. Reference should also be made to the Shuttle Operational Data Book, JSC 08934, for standard placards and constraints. a. None Identified. 5.0 SUPPLEMENTAL REQUIREMENTS 5.1 Development Test Objectives (DTO's) The following DTO's are assigned to this flight: None Identified A “D” suffix to a DTO number identifies it as a data only test. The details of the DTO's assigned to this flight for implementation are contained in the FTSOD, NSTS 16725. 5.2 Detailed Supplementary Objectives (DSO's) The following DSO’s are assigned to this flight: None Identified The details of the DSO's assigned to this flight for implementation are contained in the FTSOD, NSTS 16725. 5.3 Human Exploration and Development of Space (HEDS) Technology Demonstrations (HTD’s) The following HTD’s are assigned to this flight: None Identified


16

The details of the HTD’s assigned to this flight for implementation are contained in FTSOD, NSTS 16725. 5.4 Data Collection The Modular Auxiliary Data System (MADS) Pulse Code Modulation (PCM) and MADS wideband will be recording during ascent and entry. 6.0 PRIORITIES These priorities are established to provide guidance for premission planning and real-time rescheduling in the event of anomalies or operational considerations that preclude the accomplishment of all planned requirements. 6.1 Generalized Priorities

(1) Reference ISS LON Crew Rescue MIP, NSTS 21519, for details of the integrated mission priorities.

FIGURE 1 - CARGO ARRANGEMENT

NSTS 17462-300 Appendix B

POWER, VIDEO AND DATA PLUG-IN-PLAN

1.0 INTRODUCTION 1.1 Purpose The purpose of this appendix is to document payload and government furnished equipment (GFE) hardware requirements with respect to power, video and data cable interfaces with the orbiter in the crew compartment for the flight. The requirements are documented in the form of plug-in plans, a Video Table, and a pointer to the POC PGSC Usage document. The Video Table will be baselined (normally) just after Cargo Integration Review (CIR), with the remainder of the Plug-In-Plan requirements baselined after Crew Compartment Configuration Review (CCCR). 1.2 Scope This appendix documents payload and GFE hardware power cable interface requirements for the available designated utility outlets defined in the NSTS 21000-IDD-MDK. Power levels shown in this document are used to aid location/installation definition/evaluation and do not constitute a budgetary allocation. Power level requirements are defined and controlled in the item-specific Payload Integration Plans (PIP), the Flight Test and Supplementary Objectives Document (FTSOD), NSTS 16725, or the Flight Crew Equipment Electrical Specification, JSC 27085. In addition, stowage/installation locations shown in this document are provided for completeness but are controlled in the flight-specific Crew Compartment Configuration Drawing (CCCD). 1.3 Change Procedure All changes to this appendix will be processed in accordance with the procedures defined in the Configuration Management Requirements, NSTS 07700, Vol. IV. 1.4 Power Panel Reference Figure 1 shows the Crew Compartment Power Panel Reference to the Plug-in-Plan. 2.0 PRE ROUTED Figure 2 shows the power/data/video cable interfaces in the Orbiter crew compartment for the pre-routed configuration. 3.0 ASCENT AND ENTRY Figure 3-1 shows the power cable interfaces with the orbiter in the crew compartment for the ascent phase. Figure 3-2 shows the power cable interfaces with the orbiter in the crew compartment for the entry phase. 4.0 ON-ORBIT Figure 4-1 shows the power cable interfaces with the orbiter in the crew compartment for the on-orbit phase. Table 1 Photo TV Configuration shows the Cargo Engineering video cable requirements. The applicable data cable interfaces with the Orbiter are reflected in the POC PGSC Usage document.

B-1


FIGURES (N/A)


PHOTO TV CONFIGURATION TABLE (ISS Flights)

Payload Support Equipment

Mission Phase

Mission Activity PL TV 1

PL TV 2

PL TV 3

PNL-019

PNL MO58F

TV MON 2

VSU Orb Video Output

VSU Video B Output

VSU Video Spare

I/F Definition

Minicam (Standard)

Ascent Record video during ascent

Video only Cable Pre-routed Record on V10

Payload 1 (Unique)

On-Orbit Downlink Video X Video and Synch PDIP JTBD Cable TBD

KEEL 1 (Unique)

On-Orbit To support Mission Objective (i.e Prox Ops)

X Video and Synch KEEL 1 to VPU via pre-routed cables. Green jumper on “KEEL 1” VPU patch panel.

KEEL 2 (Unique)

On-Orbit To support Mission Objective (i.e Prox Ops)

X Video and Synch KEEL 2 To PNL 019 via VPU J203. Cable TBD

Mission Camera

On-Orbit To support Mission Objective

X Video and Synch Signals wired to VPU via pre-routed cables. Green jumper on “MISS CAM” VPU patch panel .

SSV (Standard)

On-Orbit Downlink Still Video

X Video only PDIP J107 via cable SED16103246-301

WVS (Standard)

On-Orbit

Record video via V10 and access orbiter video System

X Video Only Via WIB XCVR 1 & 2 port

DTV (Standard)

On-Orbit Digitally downlink video via KU CH 3 (PL Max) and/or record video.

X video, vertical interval data and audio

ISS Hardwired Orbiter to ISS Video (2) (Standard)

On-Orbit (Mated)

Video to ISS RWS X X Video Only I/F Hardwired from VPU to APAS X3

EXAMPLE

B-7


PHOTO TV CONFIGURATION TABLE

(ISS Flights)

Payload Support Equipment

Mission Phase

Mission Activity

PL TV 1

PL TV 2

PL TV 3

PNL-019

PNL MO58F

TV MON 2

VSU Orb Video Output

VSU Video B Output

VSU Video Spare

I/F Definition

ISS Pri C/L Cam (Standard ISS) *

On-Orbit Rndz/Sep

Nominal docking Config

X Video and Synch. Docking (interface via ODS TV 1 to VPU). Signals Pre-routed via VPU J201 jumper V845-73441-001. Green Jumper on “Pri CL “ VPU Patch Panel .

ISS Sec C/L Cam (Standard ISS) *

On-Orbit Rndz/Sep

OFF- Nominal docking Config

X Video and Synch Docking (interface via ODS TV 2 to VPU ). Signals Pre-routed via VPU J202 jumper V845-73441-001. Green Jumper on “SEC CL “ VPU Patch Panel .

ISS Hardwired ISS to Orb Video (1) (Standard)

On-Orbit (Mated)

Video to Orb (i.e. CBCS video)

X Video only. I/F Hardwired from APAS X3 to VPU . Green jumper on “ISS” VPU Patch Panel Jumper.

ISS Primary Camcorder (Standard)

On-Orbit (Mated)

ISS viewing X Video and Audio Lines. Camcorder connected at primary ODS TV port 1 in airlock . Signals wired to VPU J201. Green Jumper on “Pri CL “ VPU Patch Panel Audio lines wired to PLT CCU Via cable V838-713763-001

ISS Secondary Camcorder (Standard)

On- Orbit (Mated)

ISS viewing (Off Nominal Config)

X Video and Audio Lines. Camcorder connected at Secondary ODS TV port 2 in airlock (Primary wiring failure). Signals wired to VPU J202. Green jumper on “Sec CL “ VPU Patch Panel . Audio lines wired to PLT CCU Via cable V838-713763-001

Minicam (Standard)

Descent Record and Downlink video via S-band

Video Only Downlink cable pre-routed to AVIU in L-10 container Record on V10

* If Pri C/L fails, Secondary camera will be used on ODS TV 1. If ODS TV port 1 fails, Sec CL Camera will be used via secondary port in airlock (via pre-routed VPU jumper). If VSU fails TVCU will be connected to VPU J201 via cable SED33105876-301. EXAMPLE

B-8

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