SSP_50438-Part_1-Rev_F-ITAR.docx
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This notice announces a forthcoming Request for Proposal for the Human Space Flight Technical Integration Contract. The solicitation will be released on or about November 1, 2019, with proposals due on or about December 11, 2019. The contract is a total small business set-aside under NAICS code 541715 with a size standard of 1,250 employees. The contract will support NASA's Johnson Space Center. Interested parties should monitor the listed websites for release of the RFP and any amendments. All technical questions must be submitted in writing. The RFP solicits proposals to provide technical integration services for human space flight programs.
SSP 50438-Part 1-Rev F-ITAR
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SSP 50438 Part 1 Revision F (Draft – February 2019) International Space Station to H-II Transfer Vehicle Interface Control Document Part 1
International Space Station Program
Revision F
February 2019
This document contains information which falls under the purview of the U.S. Munitions List (USML), as defined in the International Traffic in Arms Regulations (ITAR), 22 CFR 120-130, and is export controlled. It shall not be transferred to foreign nationals in the U.S. or abroad, without specific approval of a knowledgeable NASA export control official, and/or unless an export license/license exemption is obtained/available from the United States Department of State. Violations of these regulations are punishable by fine, imprisonment, or both.
National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract No.: NNJ12GA46C
SSP 50438, Part 1 Revision F
REVISION AND HISTORY
| REV. |
| DESCRIPTION |
| PUB. DATE |
| D |
| Revision D per (SSCD 013685 EFF, 06/28/13) |
| 09-25-13 |
| SSCNs incorporated by this change include 006354, 009086, 009111, 009606, 009719, 010119, 010546, 010915, 011151, 011279, 011388, 011867, 012691, and 013685. | ||
| PIRN | IRN | SSCN |
| 50438-ND-0008 | N/A | 013685 |
| 50438-NA-0017C | N/A | 013685 |
| 50438-NA-0018 | N/A | 013685 |
| 50438-NA-0020 | N/A | 013685 |
| 50438-NA-0021B | N/A | 013685 |
| 50438-NA-0022 | 0011 | 009086 |
| 50438-NA-0022 | 0015 | 009606 |
| 50438-NA-0022 | 0016 | 006354 |
| 50438-NA-0022 | 0017 | 009719 |
| 50438-NA-0022 | 0018 | 009111 |
| 50438-NA-0022 | 0019 | 009993 |
| 50438-NA-0022 | 0020 | 010546 |
| 50438-NA-0022 | 0021 | 010119 |
| 50438-NA-0022 | 0022 | 010915 |
| 50438-NA-0022 | 0025 | 011151 |
| 50438-NA-0022 | 0026 | 011388 |
| 50438-NA-0022 | 0027 | 011279 |
| 50438-NA-0022 | 0029 | 010905 |
| 50438-NA-0022 | 0030 | 011867 |
| 50438-NA-0022 | 0031 | 012691 |
| 50438-ND-2002 | N/A | 013685 |
| 50438-NA-0023 | N/A | 013685 |
| 50438-NA-0028 | N/A | 013685 |
Revision D also closes the following SSCNs which were determined to be overcome by events or to be of no impact: 008655-OBE, 009029-OBE, 010726OBE, 011047-NI, 011582 IRN 0028-NI.
| E |
| Revision E (Reference per SSCD 14514R1, EFF. 11-23-15) |
| 12-10-15 |
| PIRN | IRN | SSCN | |
| 50438-ND-0009 | N/A | N/A |
| F |
| Revision F (Reference per SSCD 15941, EFF. 05-15-19) |
| 07-23-19 |
SSCNs incorporated by this change include 012906, 013393,013565
PIRN
50438-NA-0029
REVISION AND HISTORY
| REV. |
| DESCRIPTION |
| PUB. DATE |
50438-NA-0030
50438-NA-0031
50438-NA-0032
SSCN 12902 was not incorporated as the applicable document to be updated was removed during the Revision E Release. Proposed changes to SSP 50438 Part 1 via SSCN 12902 are now OBE.
PREFACE
International Space Station to H-II Transfer Vehicle Interface Control Document Part 1 The SSP 50438, International Space Station to H-II Transfer Vehicle Interface Control Document Part 1, defines the physical and functional interface requirements between the International Space Station (ISS) and the H-II Transfer Vehicle (HTV). This Interface Control Document (ICD) provides all interface requirements necessary to develop ICD Part 2, and the associated verification requirements in a verification matrix form, to verify Joint (ISS and HTV) interface. The contents of this document equally apply to the National Aeronautics and Space Administration (NASA) and to its contractors and to the Japanese Aerospace Exploration Agency (JAXA) and its contractors. This document shall be implemented on all new Program contractual and internal activity. This document shall be included in any existing contracts through contract changes. This document is under the control of the Space Station Control Board (SSCB) with the concurrence of the respective International Agency, and any changes or revisions will be approved by the SSCB and the respective International Agency.
The Space Station Control Board delegates control and approval authority for future updates or revisions to the Transportation Integration Control Board (TICB).
See Directive Approval
See Directive Approval
Ven Feng Manager Transportation Integration Office hIROHIKO uEMATSU HTV Technology Center DIRECTOR
Date
Date
INTERNATIONAL SPACE STATION PROGRAM
Interface Control Document Part 1
CONCURRENCE
February 2019
INTERNATIONAL SPACE STATION PROGRAM
Interface Control Document Part 1
CONCURRENCE
february 2019
TABLE OF CONTENTS
| PARAGRAPH | PAGE | |
| 1.0 | INTRODUCTIOn | 1-1 |
| 1.1 | Purpose and scope | 1-1 |
| 1.2 | precedence | 1-1 |
| 1.3 | responsibility and change authority | 1-1 |
| 2.0 | Documents | 2-1 |
| 2.1 | applicable documents | 2-1 |
| 2.2 | reference documents | 2-5 |
| 3.0 | Interfaces | 3-1 |
| 3.1 | GENERAL | 3-1 |
| 3.1.1 | INTERFACE DESCRIPTION | 3-1 |
| 3.1.1.1 | iss DESCRIPTION | 3-4 |
| 3.1.1.2 | HTV system DESCRIPTION | 3-4 |
| 3.1.1.2.1 | htv | 3-5 |
| 3.1.1.2.2 | HTV Proximity communication system | 3-5 |
| 3.1.1.2.3 | laser radar reflector | 3-5 |
| 3.1.1.2.4 | htv operations systems | 3-5 |
| 3.1.1.3 | iNTERFACE PLANES DESCRIPTION | 3-5 |
| 3.1.1.4 | COORDINATE SYSTEM | 3-10 |
| 3.1.1.5 | ISS INTERFACE FUNCTIONS | 3-19 |
| 3.1.1.6 | HTV INTERFACE FUNCTIONS | 3-19 |
| 3.1.1.7 | reserved | 3-20 |
| 3.1.2 | INTERFACE RESPONSIBILITIES | 3-20 |
| 3.1.2.1 | RESPONSIBILITY FOR ISS | 3-20 |
| 3.1.2.2 | RESPONSIBILITY FOR HTV | 3-20 |
| 3.1.2.3 | RESPONSIBILITY FOR UTILITY CONNECTORS | 3-20 |
| 3.1.3 | ENGINEERING UNITS | 3-21 |
| 3.1.4 | tolerances | 3-21 |
| 3.2 | INTERFACE REQUIREMENTS TO ISS (Nodes 1 and 2) AND HTV | 3-21 |
| 3.2.1 | ISS (node 2 and node 1) INTERFACE REQUIREMENTS | 3-21 |
| 3.2.1.1 | ENVELOPE REQUIREMENTS | 3-22 |
| 3.2.1.1.1 | ACCESS ENVELOPE | 3-22 |
| 3.2.1.2 | STRUCTURAL/MECHANICAL INTERFACE | 3-22 |
| 3.2.1.2.1 | RESERVED | 3-22 |
| 3.2.1.2.2 | BERTHING/ATTACHMENT MECHANISM(S) | 3-22 |
| 3.2.1.2.3 | structural | 3-22 |
| 3.2.1.2.4 | fracture control | 3-22 |
| 3.2.1.2.5 | UTILITY MECHANICAL INTERFACES | 3-22 |
| 3.2.1.2.5.1 | Accessibility | 3-22 |
| 3.2.1.2.5.2 | Redundancy | 3-22 |
| 3.2.1.2.5.3 | ELECTRICAL CONNECTORS | 3-22 |
| 3.2.1.2.5.4 | FLUID FITTINGS | 3-22 |
| 3.2.1.2.5.4.1 | fittings mating | 3-22 |
| 3.2.1.2.5.4.2 | flexible lines and bellows | 3-22 |
| 3.2.1.2.5.5 | utility cable specifications | 3-22 |
| 3.2.1.2.5.5.1 | data bus cable specifications | 3-22 |
| 3.2.1.2.5.5.2 | Power cable specifications | 3-23 |
| 3.2.1.2.6 | ACCESS/PASSAGE WAYS | 3-23 |
| 3.2.1.2.6.1 | Vestibule clearances | 3-23 |
| 3.2.1.2.6.2 | Ingress/Egress passageways | 3-23 |
| 3.2.1.2.7 | RESERVED | 3-23 |
| 3.2.1.2.8 | Grounding | 3-23 |
| 3.2.1.2.9 | SHIELDING | 3-23 |
| 3.2.1.3 | FLUID INTERFACES | 3-23 |
| 3.2.1.3.1 | Reserved | 3-23 |
| 3.2.1.3.2 | reserved | 3-23 |
| 3.2.1.3.3 | SUPPLY INTERMODULE ATMOSPHERE. | 3-23 |
| 3.2.1.3.3.1 | intermodule Atmosphere SUPPLY characteristics | 3-23 |
| 3.2.1.3.3.1.1 | intermodule atmosphere supply temperature | 3-23 |
| 3.2.1.3.3.1.2 | intermodule atmosphere supply pressure | 3-23 |
| 3.2.1.3.3.1.3 | intermodule atmosphere supply rate | 3-23 |
| 3.2.1.3.3.1.4 | intermodule atmosphere SUPPLY humidity | 3-23 |
| 3.2.1.3.3.1.5 | maximum oxygen concentration | 3-23 |
| 3.2.1.3.3.2 | RESERVED | 3-24 |
| 3.2.1.3.3.3 | CONTROL INTERMODULE ATMOSPHERE SUPPLY | 3-24 |
| 3.2.1.3.4 | RECEIVE RETURN INTERMODULE ATMOSPHERE | 3-24 |
| 3.2.1.3.4.1 | INTERMODULE ATMOSPHERE CHARACTERISTICS | 3-24 |
| 3.2.1.3.4.1.1 | INTERMODULE ATMOSPHERE RECEIVE RETURN PRESSURE | 3-24 |
| 3.2.1.3.4.1.2 | INTERMODULE ATMOSPHERE RECEIVE RETURN RATE | 3-24 |
| 3.2.1.3.4.1.3 | intermodule atmosphere receive return heat load | 3-24 |
| 3.2.1.3.4.2 | INTERMODULE ATMOSPHERE receive return availability | 3-24 |
| 3.2.1.3.4.3 | control RETURN INTERMODULE ATMOSPHERE | 3-24 |
| 3.2.1.3.5 | RECEIVE ATMOSPHERE SAMPLE AIR | 3-24 |
| 3.2.1.3.5.1 | atmosphere sample air receive flow rate | 3-24 |
| 3.2.1.3.5.2 | atmosphere sample air receive pressure drop | 3-24 |
| 3.2.1.3.6 | Reserved | 3-24 |
| 3.2.1.4 | ELECTRICAL POWER INTERFACES | 3-24 |
| 3.2.1.4.1 | PMMN1N POWER OUTPUT CIRCUIT | 3-24 |
| 3.2.1.4.1.1 | PMMN1N POWER SOURCE CHARACTERISTICS | 3-25 |
| 3.2.1.4.1.2 | PMMN1N IN FAULT PROTECTION | 3-25 |
| 3.2.1.4.1.3 | PMMN1N/HTV−1 POWER CONTROL | 3-25 |
| 3.2.1.4.1.3.1 | PMMN1N/HTV−1 POWER ON/OFF CONTROL | 3-25 |
| 3.2.1.4.1.3.2 | RESERVED | 3-25 |
| 3.2.1.4.1.4 | PMMN1N SOURCE IMPEDANCE | 3-25 |
| 3.2.1.4.1.5 | PMMN1N/HTV−1 SOURCE TURN_ON CHARACTERISTICS | 3-25 |
| 3.2.1.4.2 | PMMN2N/HTV_1 POWER OUTPUT CIRCUIT | 3-25 |
| 3.2.1.4.2.1 | PMMN2N/HTV_1 POWER SOURCE CHARACTERISTICS | 3-25 |
| 3.2.1.4.2.2 | PMMN2N/HTV_1 FAULT PROTECTION | 3-25 |
| 3.2.1.4.2.3 | PMMN2N/HTV_1 POWER CONTROL | 3-25 |
| 3.2.1.4.2.3.1 | PMMN2N/HTV_1 POWER ON/OFF CONTROL | 3-25 |
| 3.2.1.4.2.4 | PMMN2N/HTV_1 SOURCE IMPEDance | 3-25 |
| 3.2.1.4.2.5 | PMMN2N/HTV_1 USOS SOURCE TURN_ON CHARACTERISTICS | 3-25 |
| 3.2.1.4.3 | RESERVED | 3-25 |
| 3.2.1.4.4 | HTV-2 POWER output circuit | 3-25 |
| 3.2.1.4.4.1 | HTV-2 power SOURCE CHARACTERISTICS | 3-26 |
| 3.2.1.4.4.2 | HTV-2 fault protection | 3-26 |
| 3.2.1.4.4.3 | HTV-2 power control | 3-26 |
| 3.2.1.4.4.3.1 | HTV-2 power on/off control | 3-26 |
| 3.2.1.4.4.4 | HTV-2 source impedance | 3-26 |
| 3.2.1.4.4.5 | HTV-2 SOURCE TURN-ON CHARACTERISTICS | 3-26 |
| 3.2.1.5 | Command and data handling (c&DH) interface (ISS (NODE 2 and NODE 1) to HTV element) | 3-26 |
| 3.2.1.5.1 | mil-std-1553B interfaces | 3-26 |
| 3.2.1.5.1.1 | DATA BUS STANDARDS | 3-26 |
| 3.2.1.5.1.2 | reserved | 3-26 |
| 3.2.1.5.1.3 | reserved | 3-26 |
| 3.2.1.5.1.4 | reserved | 3-26 |
| 3.2.1.5.1.5 | space station Local Bus | 3-26 |
| 3.2.1.5.1.5.1 | Terminal operations | 3-26 |
| 3.2.1.5.1.5.2 | SOFTWARE FUNCTIONAL INTERFACES | 3-26 |
| 3.2.1.5.1.5.3 | provide output amplitude | 3-26 |
| 3.2.1.5.1.5.4 | TERMINATIONS/jumpers | 3-27 |
| 3.2.1.5.2 | RESERVED | 3-27 |
| 3.2.1.6 | induced environments | 3-27 |
| 3.2.1.6.1 | electromagnetic EFFECTS | 3-27 |
| 3.2.1.6.1.1 | electromagnetic compatibility | 3-27 |
| 3.2.1.6.1.2 | BONDING | 3-27 |
| 3.2.1.6.2 | thermal | 3-27 |
| 3.2.1.6.2.1 | reserved | 3-27 |
| 3.2.1.6.2.2 | thermal interface for htv | 3-27 |
| 3.2.1.6.2.2.1 | PASSIVE INTERFACE TEMPERATURE | 3-27 |
| 3.2.1.6.2.2.2 | CONDUCTIVE HEAT TRANSFER | 3-27 |
| 3.2.1.6.2.2.3 | RADIATIVE HEAT TRANSFER | 3-27 |
| 3.2.1.6.2.3 | Deleted | 3-27 |
| 3.2.1.6.3 | Deleted | 3-27 |
| 3.2.1.6.4 | STRUCTURAL LOADS | 3-27 |
| 3.2.1.6.4.1 | ON-orbit induced loads | 3-27 |
| 3.2.1.6.4.2 | reserved | 3-27 |
| 3.2.1.6.4.3 | on-orbit thermally induced loads | 3-27 |
| 3.2.1.6.4.3.1 | on-orbit thermally induced structural loads | 3-27 |
| 3.2.1.6.4.3.2 | on-orbit thermally induced structural loads spectra | 3-27 |
| 3.2.2 | HTV INTERFACE REQUIREMENTS | 3-28 |
| 3.2.2.1 | ENVELOPE REQUIREMENTS | 3-28 |
| 3.2.2.1.1 | Access envelope FOR UTILITY JUMPERS | 3-28 |
| 3.2.2.1.2 | ACCESS ENVELOPE FOR EXTERNAL MAINTENANCE | 3-28 |
| 3.2.2.1.3 | HTV berthing STAY-OUT zone envelope | 3-28 |
| 3.2.2.1.4 | htv maximum structural envelope | 3-32 |
| 3.2.2.1.5 | HTV MAXIMUM LENGTH | 3-32 |
| 3.2.2.2 | STRUCTURAL/MECHANICAL INTERFACE | 3-34 |
| 3.2.2.2.1 | RESERVED | 3-34 |
| 3.2.2.2.2 | BERTHING/ATTACHMENT MECHANISM(S) | 3-34 |
| 3.2.2.2.3 | reserved | 3-35 |
| 3.2.2.2.4 | reserved | 3-35 |
| 3.2.2.2.5 | interconnecting utility hardware | 3-35 |
| 3.2.2.2.5.1 | Accessibility | 3-35 |
| 3.2.2.2.5.2 | Redundancy | 3-35 |
| 3.2.2.2.5.3 | ELECTRICAL CONNECTORS | 3-35 |
| 3.2.2.2.5.4 | FLUID FITTINGS | 3-35 |
| 3.2.2.2.5.4.1 | fitting mating | 3-36 |
| 3.2.2.2.5.5 | utility cable specifications | 3-36 |
| 3.2.2.2.5.5.1 | data bus cable specifications | 3-36 |
| 3.2.2.2.5.5.2 | Power cable specifications | 3-36 |
| 3.2.2.2.6 | ACCESS/PASSAGE WAYS | 3-36 |
| 3.2.2.2.6.1 | Vestibule clearances | 3-36 |
| 3.2.2.2.6.2 | Ingress/Egress passageways | 3-36 |
| 3.2.2.2.7 | reserved | 3-36 |
| 3.2.2.2.8 | GROUNDING | 3-36 |
| 3.2.2.2.9 | SHIELDING | 3-36 |
| 3.2.2.3 | FLUID INTERFACES | 3-37 |
| 3.2.2.3.1 | reserved | 3-37 |
| 3.2.2.3.2 | reserved | 3-37 |
| 3.2.2.3.3 | receive INTERMODULE ATMOSPHERE | 3-37 |
| 3.2.2.3.3.1 | INTERMODULE ATMOSPHERE RECEIVE CHARACTERISTICS | 3-37 |
| 3.2.2.3.3.1.1 | Intermodule atmosphere receive temperature | 3-37 |
| 3.2.2.3.3.1.2 | Intermodule atmosphere receive pressure | 3-37 |
| 3.2.2.3.3.1.3 | intermodule atmosphere receive rate | 3-37 |
| 3.2.2.3.3.1.4 | intermodule atmosphere receive humidity | 3-37 |
| 3.2.2.3.3.1.5 | maximum oxygen concentration | 3-37 |
| 3.2.2.3.3.2 | reserved | 3-37 |
| 3.2.2.3.3.3 | reserved | 3-37 |
| 3.2.2.3.4 | RETURN INTERMODULE ATMOSPHERE | 3-37 |
| 3.2.2.3.4.1 | INTERMODULE ATMOSPHERE CHARACTERISTICS | 3-37 |
| 3.2.2.3.4.1.1 | reserved | 3-37 |
| 3.2.2.3.4.1.2 | INTERMODULE ATMOSPHERE RETURN RATE | 3-37 |
| 3.2.2.3.4.1.3 | Intermodule atmosphere return heat load | 3-38 |
| 3.2.2.3.4.2 | INTERMODULE ATMOSPHERE return availability | 3-38 |
| 3.2.2.3.4.3 | RESERVED | 3-38 |
| 3.2.2.3.5 | ATMOSPHERE sampling | 3-38 |
| 3.2.2.3.5.1 | atmosphere sample air supply FLOW RATE | 3-38 |
| 3.2.2.3.5.2 | ATMOSPHERE SAMPLE AIR SUPPLY PRESSURE DROP | 3-38 |
| 3.2.2.3.6 | supply potable water | 3-38 |
| 3.2.2.3.6.1 | DELETED | 3-38 |
| 3.2.2.3.6.1.1 | DELETED | 3-38 |
| 3.2.2.3.6.1.2 | DELETED | 3-38 |
| 3.2.2.3.6.1.3 | DELETED | 3-38 |
| 3.2.2.3.6.1.4 | DELETED | 3-38 |
| 3.2.2.3.6.1.5 | DELETED | 3-38 |
| 3.2.2.3.6.1.6 | DELETED | 3-38 |
| 3.2.2.4 | Electrical Power interfaces | 3-38 |
| 3.2.2.4.1 | nominal power input circuit | 3-39 |
| 3.2.2.4.1.1 | POWER QUALITY | 3-39 |
| 3.2.2.4.1.2 | fault protection | 3-40 |
| 3.2.2.4.1.3 | INITIALIZATION SURGE CURRENT | 3-40 |
| 3.2.2.4.1.4 | small signal stability | 3-40 |
| 3.2.2.4.2 | RESERVED | 3-41 |
| 3.2.2.5 | c&DH interface (HTV element) | 3-41 |
| 3.2.2.5.1 | mil-std-1553B interface | 3-41 |
| 3.2.2.5.1.1 | DATA BUS STANDARDS | 3-41 |
| 3.2.2.5.1.2 | deleteD | 3-42 |
| 3.2.2.5.1.3 | HTV Bus Topology | 3-42 |
| 3.2.2.5.1.4 | reserved | 3-42 |
| 3.2.2.5.1.5 | space station Local Bus | 3-42 |
| 3.2.2.5.1.5.1 | Terminal operations | 3-42 |
| 3.2.2.5.1.5.2 | SOFTWARE FUNCTIONal INTERFACES | 3-42 |
| 3.2.2.5.1.5.3 | provide output amplitude | 3-42 |
| 3.2.2.5.1.5.4 | deleted | 3-42 |
| 3.2.2.5.2 | RESERVED | 3-42 |
| 3.2.2.6 | induced environments | 3-42 |
| 3.2.2.6.1 | electromagnetic effects | 3-42 |
| 3.2.2.6.1.1 | electromagnetic compatibility | 3-42 |
| 3.2.2.6.1.2 | BONDING | 3-42 |
| 3.2.2.6.2 | thermal | 3-44 |
| 3.2.2.6.2.1 | reserved | 3-44 |
| 3.2.2.6.2.2 | thermal interface | 3-44 |
| 3.2.2.6.2.2.1 | passive interface temperature | 3-44 |
| 3.2.2.6.2.2.2 | conductive heat transfer | 3-45 |
| 3.2.2.6.2.2.3 | radiative heat transfer | 3-45 |
| 3.2.2.6.2.3 | deleted | 3-45 |
| 3.2.2.6.3 | deleteD | 3-45 |
| 3.2.2.6.4 | STRUCTURAL LOADS | 3-45 |
| 3.2.2.6.4.1 | ON-ORBIT INDUCED LOADS | 3-45 |
| 3.2.2.6.4.2 | ON-Orbit pressure loads and load spectra | 3-47 |
| 3.2.2.6.4.3 | on-orbit thermally induced structural loads and LOADs SPECTRA | 3-49 |
| 3.2.2.6.4.3.1 | on-orbit thermally induced structural loads | 3-49 |
| 3.2.2.6.4.3.2 | ON-ORBIT THERMALLY INDUCED structural LOAD SPECTRA | 3-51 |
| 3.3 | Mobile servicing system to HTV INTERFACE | 3-53 |
| 3.3.1 | MSS Interface Requirements | 3-53 |
| 3.3.1.1 | reserved | 3-53 |
| 3.3.1.2 | reserved | 3-53 |
| 3.3.2 | HTV Interface requirements | 3-53 |
| 3.3.2.1 | mechanical condition of frgf separation | 3-53 |
| 3.3.2.2 | deleted | 3-53 |
| 3.3.2.3 | electrical power supply from mss | 3-53 |
| 3.3.2.4 | SPDM OTCM to exposed pallet hefu interface | 3-53 |
| 3.4 | ISs to prox interface | 3-55 |
| 3.4.1 | ISS interface requirements | 3-55 |
| 3.4.1.1 | c&DH interfaces (Iss to prox) | 3-55 |
| 3.4.1.1.1 | mil-std-1553b interface | 3-55 |
| 3.4.1.1.1.1 | data bus standards | 3-55 |
| 3.4.1.1.1.2 | reserved | 3-55 |
| 3.4.1.1.1.3 | space station control buses | 3-55 |
| 3.4.1.1.1.4 | terminal operations | 3-55 |
| 3.4.1.1.1.5 | provide output amplitude | 3-55 |
| 3.4.1.1.1.6 | terminations | 3-55 |
| 3.4.1.1.1.7 | software functional interfaces | 3-55 |
| 3.4.2 | PROX Interface requirements | 3-55 |
| 3.4.2.1 | c&DH interfaces (PROX) | 3-55 |
| 3.4.2.1.1 | mil-std-1553B Interface | 3-55 |
| 3.4.2.1.1.1 | data bus standards | 3-55 |
| 3.4.2.1.1.2 | DeleteD | 3-56 |
| 3.4.2.1.1.3 | space station control buses | 3-56 |
| 3.4.2.1.1.4 | terminal operations | 3-56 |
| 3.4.2.1.1.5 | provide output amplitude | 3-56 |
| 3.4.2.1.1.6 | Bus cabling | 3-56 |
| 3.4.2.1.1.7 | software functional interfaces | 3-56 |
| 3.5 | other interfaces | 3-56 |
| 3.5.1 | iss interface requirements | 3-56 |
| 3.5.1.1 | rendezvous sensor field of view | 3-56 |
| 3.5.1.2 | prox link during berthing | 3-56 |
| 3.5.1.3 | RESERVED | 3-58 |
| 3.5.1.4 | RESERVED | 3-58 |
| 3.5.1.5 | RESERVED | 3-58 |
| 3.5.1.6 | BERTHING AND RELEASE INTERFACE | 3-58 |
| 3.5.1.6.1 | RESERVED | 3-58 |
| 3.5.1.6.2 | RELEASE POINT AND ATTITUDE | 3-58 |
| 3.5.1.6.3 | RELEASE CONDITIONS | 3-59 |
| 3.5.1.7 | PORTABLE EQUIPMENT AND ORBITAL INSTALLATION UNIT (TBC) | 3-59 |
| 3.5.2 | htv interface requirements | 3-61 |
| 3.5.2.1 | rESERVED | 3-61 |
| 3.5.2.2 | rESERVED | 3-61 |
| 3.5.2.3 | VISIBILITY FROM THE ISS | 3-61 |
| 3.5.2.4 | approach and departure corridor | 3-61 |
| 3.5.2.4.1 | approach corridor | 3-61 |
| 3.5.2.4.2 | departure corridor | 3-61 |
| 3.5.2.5 | Optical interference | 3-66 |
| 3.5.2.5.1 | HTV REFLECTORS interference | 3-66 |
| 3.5.2.5.2 | iss and shuttle/esa/rsa interference | 3-66 |
| 3.5.2.6 | berthing and release interface | 3-66 |
| 3.5.2.6.1 | MINIMUM CLEARANCE | 3-66 |
| 3.5.2.6.2 | RESERVED | 3-67 |
| 3.5.2.6.3 | RELEASE CONDITIONS | 3-67 |
| 3.5.2.7 | PORTABLE EQUIPMENT AND ORBITAL INSTALLATION UNIT | 3-67 |
| 3.5.2.8 | Centerline Berthing Camera System target | 3-67 |
| 4.0 | interface quality assurance provisions | 4-1 |
| 4.1 | verification methods | 4-1 |
| 4.2 | interface verification process | 4-1 |
| 4.2.1 | verification responsibility | 4-1 |
APPENDIX
| a | Acronyms and abbreviations | a-1 |
| b | tbd/tbc listing with assigned actionee | b-1 |
| c | RESERVED | c-1 |
TABLE
| 3.1.2.3-1 | ISS/HTV INTERFACE HARDWARE RESPONSIBILITIES | 3-21 |
| 3.1.4-1 | LINEAR TOLERANCES | 3-21 |
| 3.2.2.2.5.4-1 | FLUID FITTINGS | 3-35 |
| 3.2.2.3.6.1.5-1 | DELETED | 3-38 |
| 3.2.2.3.6.1.6-1 | DELETED | 3-38 |
| 3.2.2.4.1.1−1 | POWER QUALITY REQUIREMENTS | 3-39 |
| 3.2.2.6.4.1-1 | ON-ORBIT TRANSIENT LOADS | 3-46 |
| 3.2.2.6.4.1-2 | ON-ORBIT TRANSIENT LOAD SPECTRA | 3-46 |
| 3.2.2.6.4.2-1 | PRESSURE LOAD CASES(1) | 3-48 |
| 3.2.2.6.4.2-2 | ON-ORBIT PRESSURE SPECTRA | 3-49 |
| 3.2.2.6.4.3.1-1 | ON-ORBIT THERMALLY INDUCED structural LOADS (2 Pages) | 3-49 |
| 3.2.2.6.4.3.1-2 | ACBM/PCBM INTERFACE BOLT LOCATIONS | 3-50 |
| 3.2.2.6.4.3.2-1 | ON-ORBIT TRANSIENT THERMAL LOADS | 3-51 |
| 3.2.2.6.4.3.2-2 | ON-ORBIT THERMALLY INDUCED structural LOAD SPECTRA | 3-52 |
| 3.2.2.6.4.3.2-3 | ON-ORBIT THERMALLY INDUCED MEAN BERTHING LOADS | 3-53 |
| 3.3.2.1-1 | MECHANICAL CONDITION OF FRGF SEPARATION | 3-53 |
| 3.3.2.2-1 | DELETED | 3-53 |
| 3.3.2.4-1 | SPDM TO HEFU INTERFACE CONDITIONS | 3-54 |
| 3.5.1.6.2-1 | HTV FRGF LOCATION FOR HTV RELEASE | 3-58 |
| 3.5.1.6.2-2 | HTV RELEASE ATTITUDES | 3-59 |
| 3.5.1.6.3-1 | HTV RELEASE CONDITIONS | 3-59 |
| 4.0-1 | VERIFICATION MATRIX | 4-2 |
FIGURE
| FIGURE 3.1.1-1 | ON-ORBIT CONFIGURATION OF THE HTV AT NODE 2 | 3-2 |
| FIGURE 3.1.1−2 | ON−ORBIT CONFIGURATION OF THE HTV AT NODE 1 NADIR | 3-3 |
| FIGURE 3.1.1-3 | FUNCTIONAL INTERFACE DIAGRAM | 3-4 |
| FIGURE 3.1.1.3-1 | NOMINAL UTILITY INTERFACE at NODE 2 | 3-6 |
| FIGURE 3.1.1.3-2 | NOMINAL STRUCTURAL AND MECHANICAL INTERFACE at NODE 2 | 3-7 |
| FIGURE 3.1.1.3−3 | NOMINAL UTILITY INTERFACE AT NODE 1 NADIR | 3-8 |
| FIGURE 3.1.1.3−4 | NOMINAL STRUCTURAL AND MECHANICAL INTERFACE AT NODE 1 NADIR | 3-9 |
| FIGURE 3.1.1.4-1 | DELETED | 3-10 |
| FIGURE 3.1.1.4-2 | DELETED | 3-10 |
| FIGURE 3.1.1.4-3 | THE COORDINATE SYSTEM OF THE PRESSURIZED SECTION OF | |
| THE LOGISTICS CARRIER | 3-11 | |
| FIGURE 3.1.1.4-4 | GRAPPLE FIXTURE COORDINATE SYSTEM | 3-13 |
| FIGURE 3.1.1.4-5 | HTV BERTHING BOX COORDINATE SYSTEM | 3-14 |
| FIGURE 3.1.1.4-6 | HTV LASER RADAR REFLECTOR COORDINATE SYSTEM | 3-15 |
| FIGURE 3.1.1.4-7 | HTV PASSIVE CBM COORDINATE SYSTEM | 3-16 |
| FIGURE 3.1.1.4-8 | HTV EXPOSED PALLET COORDINATE SYSTEM | 3-17 |
| FIGURE 3.1.1.4-9 | htv berthing camera system (HBCS) frame of reference (FOR) | 3-18 |
| FIGURE 3.2.2.1.3-1 | BERTHING STAY-OUT ZONE (Page 1 OF 3) | 3-29 |
| FIGURE 3.2.2.1.3-2 | BERTHING STAY-OUT ZONE (PAGE 2 OF 3) | 3-30 |
| FIGURE 3.2.2.1.3-3 | BERTHING STAY-OUT ZONE (Page 3 OF 3) | 3-31 |
| FIGURE 3.2.2.1.4-1 | HTV MAXIMUM STRUCTURAL ENVELOPE | 3-33 |
| FIGURE 3.2.2.1.5-1 | HTV MAXIMUM LENGTH | 3-34 |
| Figure 3.2.2.4.1.1-1 | htv interface b transient voltage envelope | 3-40 |
| FIGURE 3.2.2.4.1.2-1 | HTV FAULT PROTECTION CHARACTERISTICS | 3-41 |
| FIGURE 3.2.2.5.1.3-1 | HTV Internal MIL-STD-1553 Bus Topology | 3-43 |
| Figure 3.2.2.6.2.2.1-1 | allowable cbm temperature range | 3-45 |
| FIGURE 3.2.2.6.4.1-1 | LOAD APPLICATION DIAGRAM | 3-47 |
| FIGURE 3.2.2.6.4.2-1 | PRESSURE LOAD CASES DIAGRAM | 3-48 |
| FIGURE 3.2.2.6.4.3.1-1 ACBM/PCBM INTERFACE ATTACHMENT LOCATIONS | 3-51 | |
| FIGURE 3.3.2.2-1 | DELETED | 3-53 |
| FIGURE 3.4.2.1.1.6-1 | PROX BUS CABLING SPECIFICATION | 3-57 |
| FIGURE 3.5.1.6.3-1 | Impulse applied to Grapple Fixture during release | 3-60 |
| FIGURE 3.5.2.4.1-1 | HTV APPROACH CORRIDORS (PAGE 1 OF 2) | 3-62 |
| FIGURE 3.5.2.4.1-1 | HTV Approach Corridors (PAGE 2 OF 2) | 3-63 |
| FIGURE 3.5.2.4.2-1 | HTV DEPARTURE CORRIDORS (PAGE 1 OF 2) | 3-64 |
| FIGURE 3.5.2.4.2-1 | HTV DEPARTURE Corridors (PAGE 2 OF 2) | 3-65 |
| FIGURE 3.5.2.8-1 | DELETED | 3-67 |
SSP 50438 Part 1 Revision F xii
INTRODUCTIOn Purpose and scope The purpose of this document is to provide definition of the structural/mechanical, electrical, thermal, fluid, and data interface functional requirements between the ISS and the HTV and the HTV system component residing in the ISS. The scope of this document is limited to the interfaces between the ISS and the HTV.
precedence In the event of conflict between SSP 41000, System Specification for Space Station and the contents of this ICD, the requirements of SSP 41000 shall take precedence.
responsibility and change authority This document is prepared and maintained in accordance with SSP 30459, International Space Station Interface Control Plan.
1-1
Documents applicable documents The following applicable documents of the exact issue shown form a part of this specification to the extent specified herein. Inclusion of applicable documents herein does not in any way supersede the order of precedence identified in Section 1.2. The references show where each applicable document is cited in this document.
ASTM E380
Revision A January 1, 1993 Standard Practice for Use of the International System of Units (SI) (the Modernized Metric System)
| References |
| 3.1.3, 3.1.4 |
JSC 66617
Initial Release September 2013 ISS Passive Thermal Control Systems (PTCS) Analysis Guide
| References |
| 3.2.2.6.2.2.3 |
MIL-STD-1553B
Revision B, Notice 2 September 8, 1986 Digital Time Division Command / Response Multiplex Databus
| References |
| 3.2.1.5.1, 3.2.2.2.5.2, 3.2.2.2.5.5.1, 3.2.2.5.1, 3.2.2.5.1.1, 3.2.2.5.1.5.1, 3.2.2.5.1.5.3, 3.4.1.1.1, 3.4.1.1.1.3, 3.4.1.1.1.4, 3.4.2.1.1, 3.4.2.1.1.1, 3.4.2.1.1.4, Table 3.2.1.2.3-1, Table 4.0-1 |
SSP 30219
Revision J May 1, 2008 Space Station Reference Coordinate Systems
| References |
| 3.1.1.4, 3.5.1.6.2, Figures 3.1.1.4-5, 3.1.1.4-6, 3.1.1.4-9 |
SSP 30240
Revision H January 15, 2010 Space Station Grounding Requirements
| References |
| 3.2.2.2.8 |
SSP 30242
Revision K January 20, 2010 Space Station Cable/Wire Design and Control Requirements for Electromagnetic Compatibility
| References |
| 3.2.2.2.9 |
SSP 30243
Revision N January 21, 2010 Space Station Requirements for Electromagnetic Compatibility
| References |
| 3.2.2.6.1.1 |
SSP 30245
Revision P January 27, 2010 Space Station Electrical Bonding Requirements
| References |
| 3.2.2.6.1.2 |
SSP 30459
Revision H April 6, 2006 International Space Station Interface Control Plan
| References |
| 1.3 |
SSP 30482
Revision C July 7, 1997 Electrical Power Specifications and Standards Volume 1: EPS Electrical Performance Specifications
| References |
| 3.2.2.4.1.1 |
SSP 41004
Revision H October 25, 2005
References Common Berthing Mechanism to Pressurized Elements Interface Control Document, Part 1
3.2.2.1.1
SSP 41004
Revision J October 25, 2005 Common Berthing Mechanism to Pressurized Elements Interface Control Document, Part 2
| References |
| 3.2.2.1.3 |
SSP 41015
Revision G September 23, 2005 Common Hatch and Mechanisms to Pressurized Elements Interface Control Document, Part 1
| References |
| 3.5.2.8 |
SSP 41147
Revision C September 30, 2001 Space Station Program Node Element 2 to Centrifuge Accommodation Module Interface Control Document, Part 1
| References |
| 3.2 |
SSP 41148
Revision D October 9, 1998 Active Common Berthing Mechanism to Passive Common Berthing Mechanism Interface Control Document, Part 1
| References |
| 3.1.1.3, 3.2.2.2.2 |
SSP 41151
Revision H August 2016 Interface Requirements Document United States On-orbit Segment to Japanese Experiment Module
| References |
| 3.4.1.1.1.1, 3.4.1.1.1.4 |
SSP 41167
Revision H June 14, 2010 Mobile Servicing System Segment Specification for the International Space Station Program
| References |
| Table 3.5.1.6.3-1 |
SSP 41175-35
Revision B June 2009 Software Interface Control Document Station Management and Control to International Space Station, Book 35, Proximity Communications System Interface
| References |
| 3.4.1.1.1.7, 3.4.2.1.1.7 |
SSP 42000
Revision U March 2016 United States On-orbit Segment to Japanese Experiment Module Interface Control Document
| References |
| 3.4.1.1.1.3, 3.4.1.1.1.5, 3.4.2.1.1.3, Figure 3.4.2.1.1.6-1 |
SSP 42004, Part 1 Revision K Current Issue Mobile Servicing System (MSS) to User (Generic), Interface Control Document, Part 1
| References |
| 3.3, 3.3.2.3, 3.3.2.4 |
SSP 42007
Revision J November 30, 2010 U. S. On-orbit Segment to Italian Mini Pressurized Logistics Module Interface Control Document, Part 1
| References |
| 3.2, 3.2.1.1.1, 3.2.1.2, 3.2.1.2.2, 3.2.1.2.3, 3.2.1.2.4, 3.2.1.2.5, 3.2.1.2.5.1, 3.2.1.2.5.2, 3.2.1.2.5.3, 3.2.1.2.5.4, 3.2.1.2.5.4.1, 3.2.1.2.5.4.2, 3.2.1.2.5.5.1, 3.2.1.2.5.5.2, 3.2.1.2.6.1, 3.2.1.2.6.2, 3.2.1.2.8, 3.2.1.2.9, 3.2.1.3.3, 3.2.1.3.3.1.1, 3.2.1.3.3.1.2, 3.2.1.3.3.1.3, 3.2.1.3.3.1.4, 3.2.1.3.3.1.5, 3.2.1.3.3.3, 3.2.1.3.4, 3.2.1.3.4.1.1, 3.2.1.3.4.1.2, 3.2.1.3.4.1.3, 3.2.1.3.4.2, 3.2.1.3.4.3, 3.2.1.3.5, 3.2.1.3.5.1, 3.2.1.3.5.2, 3.2.1.3.6, 3.2.1.3.6.1.1, 3.2.1.3.6.1.2, 3.2.1.3.6.1.3, 3.2.1.4, 3.2.1.4.1, 3.2.1.4.1.1, 3.2.1.4.1.2, 3.2.1.4.1.3.1, 3.2.1.4.1.4, 3.2.1.4.1.5, 3.2.1.4.2, 3.2.1.4.2.1, 3.2.1.4.2.2, 3.2.1.4.2.3.1, 3.2.1.4.2.4, 3.2.1.4.2.5, 3.2.1.4.4, 3.2.1.4.4.1, 3.2.1.4.4.2, 3.2.1.4.4.3.1, 3.2.1.4.4.4, 3.2.1.4.4.5, 3.2.1.5.1.1, 3.2.1.5.1.5, 3.2.1.5.1.5.1, 3.2.1.5.1.5.2, 3.2.1.5.1.5.3, 3.2.1.5.1.5.4, 3.2.1.6.1.1, 3.2.1.6.1.2, 3.2.1.6.2.2.1, 3.2.1.6.2.2.2, 3.2.1.6.2.2.3, 3.2.1.6.4.1, 3.2.1.6.4.3.1, 3.2.1.6.4.3.2, 3.2.2.2.6.1, 3.2.2.2.6.2, 3.2.2.3.3, 3.2.2.3.3.1.2, 3.2.2.3.3.1.4, 3.2.2.4, 3.2.2.5.1.5 |
SSP 50005
Revision F January 15, 2015 International Space Station Flight Crew Integration Standard
| References |
| 3.2.2.1.2, 3.2.2.2.5.1 |
SSP 50023
Rev Basic April 15, 1994 Thermal Control Plan
| References |
| 3.2.2.6.2.2.3 |
SSP 50273
Revision H March 2015 Segment Specification for the H-II Transfer Vehicle
| References |
| 3.1.1.2.1, 3.1.1.2.2, 3.1.1.2.3, 3.1.1.2.4, Figure 3.1.1.4-6 |
SSP 50420
Revision B January 2010 NASA/JAXA Bilateral Integration Verification Plan for HTV
| References |
| 4.0, 4.2 |
SSP 50917
Revision B February 2015 Contingency Water Container - Iodine to H-II Transfer Vehicle Interface Requirements Document
| References |
| 3.2.2.3.6 |
SSP 52051
Revision B
TBD
User Electrical Power Specifications and Standards
| References |
| 3.2.2.4.1.3, 3.2.2.4.1.4 |
SSQ 21635
Revision N October 22, 2012 General Specification for Connectors and Accessories, Electrical, Circular, Miniature, IVA/EVA Compatible, Space Quality
| References |
| 3.2.2.2.5.3 |
SSQ 21655
Revision H October 30, 2014 General Specification for Cable, Electrical, MIL-STD-1553 Databus Space Quality
| References |
| 3.2.2.2.5.5.1 |
SSQ 22720
Revision A January 15, 2000 Wire, Electrical, Super Flex, Tefzel Insulated, Nickel Coated, Space Quality, General Specification
| References |
| 3.2.2.2.5.5.2 |
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.
SSP 50438 Part 2 Revision Basic January 13, 2006 International Space Station to H-II Transfer Vehicle Interface Control Document, Part 2
| References |
| 3.5.1.6.2, 3.5.2.5.1 |
2-5
Interfaces
GENERAL
INTERFACE DESCRIPTION
The HTV on-orbit configuration for N2 Nadir and Zenith interfaces is shown in Figure 3.1.1-1, On-orbit Configuration of the HTV at NODE 2. The HTV on-orbit configuration for Node 1 Nadir is shown in Figure 3.1.1.-2, On-Orbit Configuration of the HTV at Node 1 Nadir. This ICD depicts the nominal clocking of HTV on each of the Node interfaces, any off-nominal clocking will be addressed via operations procedures.
The ISS to the HTV functional interface diagram is shown in Figure 3.1.1-3, Functional Interface Diagram.
The HTV approaches to the ISS Node 2 Nadir port and berths to Node 2 Nadir or Node 1 Nadir port. The Node 2 Zenith port no longer supports berthing. In this section and other sections of this document, where there is a choice between berthing at Node 1 Nadir or Node 2 Zenith, the Node 1 Nadir port will be used.
FIGURE 3.1.1-1 ON-ORBIT CONFIGURATION OF THE HTV AT NODE 2
FIGURE 3.1.1−2 ON−ORBIT CONFIGURATION OF THE HTV AT NODE 1 NADIR
FIGURE 3.1.1-3 FUNCTIONAL INTERFACE DIAGRAM
iss DESCRIPTION The ISS is an earth orbiting facility which houses experiment payloads, distributes resource utilities, and supports permanent human habitation for conducting research and science experiments in a microgravity environment. The ISS will supply the following services and capabilities: electrical power generation, storage, distribution and control; communications and data links to ground support facilities; environmental control and life support; thermal control data processing, stowage and transportation; housekeeping; personal hygiene; food preparation and storage; extravehicular activity, (EVA) access; payload utilities; and robotic systems control.
HTV system DESCRIPTION The HTV system is composed of the HTV, the HTV Proximity Communication System (HTV PROX or PROX), the Laser Radar Reflectors (LRRs), and the HTV Operations System.
The HTV is a space vehicle which carries the cargo to supply the equipment and the logistics for the ISS and to dispose of the wastes by reentry into the earth atmosphere to destruct.
htv Description of the HTV is included in SSP 50273, Segment Specification for the H-II Transfer Vehicle, paragraph 3.1.1.1.
HTV Proximity communication system The HTV PROX system is installed in the Japanese Experiment Module (JEM). Description of the HTV PROX is included in SSP 50273, paragraph 3.1.1.4.
laser radar reflector Description of the LRRs mounted on the JEM is included in SSP 50273, paragraph 3.1.1.5.
htv operations systems Description of the HTV Operations System is included in SSP 50273, paragraph 3.1.1.3.
iNTERFACE PLANES DESCRIPTION The Node 2 to the HTV utility interface is shown in Figure 3.1.1.3-1, Nominal Utility Interface. The avionics and fluid interfaces are at the external feedthrough connectors of the HTV bulkhead. The structural and mechanical interface is at the interface between the Common Berthing Mechanisms (CBM) connecting the Node 2 and the HTV as shown in Figure 3.1.1.3-2, Nominal Structural and Mechanical Interface. Dimensions and material characteristics at the CBM interface are in accordance with SSP 41148, Active Common Berthing Mechanism to Passive Common Berthing Mechanism Interface Control Document, Part 1.
The Node 1 to the HTV utility interface is shown in Figure 3.1.1.3−3, Nominal Utility Interface. The avionics and fluid interfaces are at the external feedthrough connectors of the HTV bulkhead. The structural and mechanical interface is at the interface between the Common Berthing Mechanisms (CBM) connecting the Node 1 and the HTV as shown in Figure 3.1.1.3−4, Nominal Structural and Mechanical Interface.
The HTV is nominally berthed to the Node 2 nadir port. It can alternately be berthed to the Node 2 zenith port or the Node 1 nadir port.
FIGURE 3.1.1.3-1 NOMINAL UTILITY INTERFACE at NODE 2
FIGURE 3.1.1.3-2 NOMINAL STRUCTURAL AND MECHANICAL INTERFACE at NODE 2
FIGURE 3.1.1.3−3 NOMINAL UTILITY INTERFACE AT NODE 1 NADIR
FIGURE 3.1.1.3−4 NOMINAL STRUCTURAL AND MECHANICAL INTERFACE AT NODE 1 NADIR
COORDINATE SYSTEM
A. ISS Reference Coordinate Systems The ISS reference coordinate systems, which are defined in SSP 30219, Space Station Reference Coordinate Systems, shall be used for interface definitions between the HTV and the ISS.
| B. | HTV Reference Coordinate Systems |
| 1. | HTV Coordinate System, Mechanical Design Reference |
The HTV coordinate system for mechanical design reference is defined in SSP 30219.
2. HTV Coordinate System, Attitude Reference The HTV Coordinate System for attitude reference is defined in SSP 30219.
3. Coordinate System of the Pressurized Section of the Logistics Carrier
FIGURE 3.1.1.4-1 DELETED
FIGURE 3.1.1.4-2 DELETED
The Coordinate System of the Pressurized Section of the Logistics Carrier is defined as follows and is shown in Figure 3.1.1.4-3:
FIGURE 3.1.1.4-3 THE COORDINATE SYSTEM OF THE PRESSURIZED SECTION OF THE LOGISTICS CARRIER
| NAME: |
| The Coordinate System of the Pressurized Section of the Logistics Carrier. |
| ORIGIN: |
| The origin is located at the geometric center of the interface plane between the structure of the Pressurized Section and the CBM. |
| ORIENTATION: |
| The XHTVPLC axis is coincident with the longitudinal axis of the Pressurized Section. The positive X-axis is toward the Pressurized Section |
The YHTVPLC axis completes a right-handed system.
The ZHTVPLC axis is parallel to the centerline of the field of view of the Rendezvous Sensor. The negative Z-axis is toward the Rendezvous Sensor head.
| CHARACTERISTICS: |
| Rotating right-handed Cartesian coordinate system, body-fixed. |
4. HTV Flight Releasable Grapple Fixture (FRGF) Coordinate System The HTV FRGF Coordinate System, is defined as follows and is shown in Figure 3.1.1.4-4:
| NAME: |
| The Grapple Fixture Axis System |
| ORIGIN: |
| The origin is located at the intersection of the grapple shaft centerline with the plane of the abutment face of the grapple plate. |
| ORIENTATION: |
| The positive XGFAS axis is out the grapple shaft. The YGFAS axis completes a right-handed system. |
The positive ZGFAS axis is up through the grapple target.
| CHARACTERISTICS: |
| Rotating right-handed Cartesian coordinate system, body-fixed. |
FIGURE 3.1.1.4-4 GRAPPLE FIXTURE COORDINATE SYSTEM
5. HTV Berthing Box Coordinate System The HTV Berthing Box Coordinate System, is defined as follows and is shown in Figure 3.1.1.4-5:
| NAME: |
| HTV Berthing Box Coordinate System |
| ORIGIN: |
| The origin is located at the center of the HTV berthing box. |
| ORIENTATION: |
| The XHTVBB, YHTVBB, and ZHTVBB axis are parallel to the XLO axis, YLO axis, and ZLO axis of the Local Vertical/Local Horizontal (LVLH) coordinate system defined in SSP 30219. |
| CHARACTERISTICS: |
| Rotating right-handed Cartesian coordinate system. |
FIGURE 3.1.1.4-5 HTV BERTHING BOX COORDINATE SYSTEM
6. HTV Laser Radar Reflector Coordinate System The HTV Laser Radar Reflector Coordinate System, is defined as follows and is shown in Figure 3.1.1.4-6:
| NAME: |
| HTV Laser Radar Reflector Coordinate System |
| ORIGIN: |
| The origin is located on the geometric center of the Laser Radar Reflectors. The location of the LRRs is defined in SSP 50273. |
| ORIENTATION: |
| The XLRRS, YLRRS, and ZLRRS axis are parallel to the XLO axis, YLO axis, and ZLO axis of the LVLH coordinate system defined in SSP 30219. |
| CHARACTERISTICS: |
| Rotating right-handed Cartesian coordinate system |
NODE 3
US-LAB
JEM
X
LRRS
Z
LRRS
HTV
Rendezvous Sensor Head Laser Radar Reflector
FIGURE 3.1.1.4-6 HTV LASER RADAR REFLECTOR COORDINATE SYSTEM
7. HTV Passive CBM Coordinate System The HTV Passive Common Berthing Mechanism (PCBM) Coordinate System, is defined as follows and is shown in Figure 3.1.1.4-7:
| NAME: |
| HTV Passive CBM Coordinate System |
| ORIGIN: |
| The origin is located at the geometric center of the interface plane between the CBM and the HTV Pressurized Section. |
| ORIENTATION: |
| The XCBM axis crosses the CBM/HTV Pressurized Section interface plane at right angles. The negative X-axis is toward the HTV Pressurized Section. The YCBM axis points at the Intermodule Ventilation (IMV) Duct Hole of the Bulk Head from the Origin, along the CBM/HTV Pressurized Section interface plane. The ZCBM axis completes a right-handed system. |
| CHARACTERISTICS: |
| Rotating right-handed Cartesian coordinate system, CBM fixed. |
Note: The CBM direction during attached phase.
+ZCBM, +YHTVS and -YISS are the same direction.
FIGURE 3.1.1.4-7 HTV PASSIVE CBM COORDINATE SYSTEM
8. HTV Exposed Pallet (EP) Coordinate System The HTV Exposed Pallet Coordinate System, is defined as follows and is shown in Figure 3.1.1.4-8:
| NAME: |
| HTV Exposed Pallet Coordinate System |
| TYPE: |
| Right-Handed Cartesian, Body-Fixed to EP |
| ORIGIN: |
| The origin is located on the lower starboard forward location of the EP structure. |
ORIENTATION:
The YEP axis is parallel to the longitudinal axis of the EP. The positive Y-axis is in the EP AFT direction. The XEP axis is perpendicular to YEP and parallel to the lateral axis of the EP. Positive X-axis is in the EP PORT direction. The ZEP axis completes the right-handed orthogonal system.
| SUBSCRIPT: |
| EP |
| NOTE: |
| Origin and Orientation are applicable for all the types of EP (Type Ia, Ib, IIIa, IIIb, IIIc, etc.) |
FIGURE 3.1.1.4-8 HTV EXPOSED PALLET COORDINATE SYSTEM
9. HTV Berthing Camera System (HBCS) Frame of Reference (FOR) The HBCS Frame of Reference is defined as follows and is shown in Figure 3.1.1.4-9:
| NAME: |
| HBCS Frame of Reference |
| TYPE: |
| Right-Handed Cartesian, Body-Fixed to EP |
| ORIGIN: |
| The origin is located between the two HBCS camera lenses on the leading edge of the EP during insertion. The HBCS Frame of Reference is located as XEP = 850 mm (33.5 in), YEP = 3706 mm (145.9 in), ZEP = 333 mm (13.1 in) with respect to the EP Coordinate System described in SSP 30219, Figure 7.0-4. |
| ORIENTATION: |
| The XHBCS FOR axis runs along the long axis of the EP and is positive in the direction from EP GF#1 to the HBCS cameras. The YHBCS FOR axis is parallel to and in the same direction as the HTV Exposed Pallet Coordinate System’s X axis (See SSP 30219, Figure 7.0-4). The positive Z-axis completes the right handed coordinate system. |
| SUBSCRIPT: |
| HBCS FOR |
| NOTE: |
| When the HTV is attached to Node 2 Nadir and the EP is installed in the ULC, the HBCS FOR principle axes are parallel with the ISS Analysis Coordinate System (See SSP 30219, Figure 4.0-1). The X axes point ISS forward, the Y axes point ISS starboard and the Z axes point ISS nadir. |
FIGURE 3.1.1.4-9 htv berthing camera system (HBCS) frame of reference (FOR)
ISS INTERFACE FUNCTIONS
The ISS will support the following functions at the interface to the HTV:
| A. | Support Structural/Mechanical Attachment |
| B. | Support Utility Distribution |
| C. | Support Passageway/Access |
| D. | Support Berthing/Mating Aids |
| E. | N/A |
| F. | N/A |
| G. | N/A |
| H. | Supply Power |
| I. | Control Power |
| J. | Supply Atmosphere |
| K. | Receive Atmosphere |
| L. | Control Atmosphere |
| M. | Receive Atmosphere Sample Air |
| N. | Supply Data (HTV Consultative Committee Standards for Data System (CCSDS) Data Processor (CDP) and PROX) |
| O. | Receive Data (HTV CDP and PROX) |
| P. | N/A |
| Q. | N/A |
| R. | N/A |
| S. | N/A |
| T. | Robotics (HTV and Exposed Pallet) |
HTV INTERFACE FUNCTIONS
The HTV will support the following functions at the interface to the ISS:
| A. | Support Structural/Mechanical Attachment |
| B. | Support Utility Distribution |
| C. | Support Passageway/Access |
| D. | Support Berthing/Mating Aids |
| E. | N/A |
| F. | N/A |
| G. | N/A |
| H. | Receive Power |
| I. | N/A |
| J. | Receive Atmosphere |
| K. | Return Atmosphere |
| L. | N/A |
| M. | Supply Atmosphere Sample Air |
| N. | Receive Commands/Data (HTV CDP and PROX) |
| O. | Supply Data (HTV CDP and PROX) |
| P. | N/A |
| Q. | N/A |
| R. | N/A |
| S. | N/A |
| T. | Robotics (HTV and Exposed Pallet) |
reserved
INTERFACE RESPONSIBILITIES
RESPONSIBILITY FOR ISS
NASA is responsible for the ISS side of the ISS to the HTV interface.
RESPONSIBILITY FOR HTV
JAXA is responsible for the HTV side of the ISS to the HTV interface.
RESPONSIBILITY FOR UTILITY CONNECTORS
The deliverable interfacing utility jumper connector responsibilities for each agency are listed in Table 3.1.2.3-1, ISS/HTV Interface Hardware Responsibilities.
TABLE 3.1.2.3-1 ISS/HTV INTERFACE HARDWARE RESPONSIBILITIES
| ISS/HTV Interface ITEM |
| HTV Supplied |
| ISS Supplied |
AVIONIC UTILITY JUMPER
| POWER |
| * |
| X |
| MIL-STD-1553B |
| * |
| X |
LIFE SUPPORT UTILITY JUMPERS
| INTERMODULE AIR RETURN |
| * |
| X |
| INTERMODULE AIR SUPPLY |
| * |
| X |
| ATMOSPHERE MONITOR |
| * |
| X |
MAIN SYSTEMS
INTERELEMENT CLOSEOUT
PANEL SET
X
*(feedthrough connectors only)
ENGINEERING UNITS
Unless otherwise noted herein, all primary dimensions are in the English (inch, pound, second) system of units. Conversion will be in accordance with American Society for Testing and Materials (ASTM) E380, Standard Practice for Use of the International System of Units (SI) (the Modernized Metric System).
tolerances Linear tolerances on English dimensions are as indicated in Table 3.1.4-1, Linear Tolerances. Linear tolerances on metric dimensions are derived from the English measurements and tolerances as defined in ASTM E380. Angular tolerances are +/- 0.1 degrees on all angles unless otherwise stated.
TABLE 3.1.4-1 LINEAR TOLERANCES
| English Dimension |
| Implied Tolerance |
| X.XX |
| +/-0.030 |
| X.XXX |
| +/-0.010 |
INTERFACE REQUIREMENTS TO ISS (Nodes 1 and 2) AND HTV The HTV will nominally berth to the Node 2 nadir port, and alternately be berthed to the Node 2 zenith port or Node 1 nadir port. Interface requirements for the Node 2 nadir/zenith and Node 1 nadir ports are provided in SSP 42007, U.S. On-orbit Segment to Italian Mini Pressurized Logistics Module, (MPLM) Interface Control Document, Part 1, as specified in the following paragraphs. Corresponding requirements for the Node 2 zenith port are specified in SSP 41147, Space Station Program Node Element 2 to Centrifuge Accommodation Module Interface Control Document, Part 1.
ISS (node 2 and node 1) INTERFACE REQUIREMENTS
ENVELOPE REQUIREMENTS
ACCESS ENVELOPE
This interface requirement is in accordance with SSP 42007, U.S. On-orbit Segment to Italian Mini Pressurized Logistics Module ICD, Part 1, paragraph 3.2.1.1.1.
STRUCTURAL/MECHANICAL INTERFACE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.2.
RESERVED
BERTHING/ATTACHMENT MECHANISM(S)
This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.2.
structural This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.3.
fracture control This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.4.
UTILITY MECHANICAL INTERFACES
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.2.5.
Accessibility This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.1.
Redundancy This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.2.
ELECTRICAL CONNECTORS
This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.3.
FLUID FITTINGS
This interface requirement is in accordance with SSP 42007, Paragraph 3.2.1.2.5.4.
fittings mating This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.4.1.
flexible lines and bellows This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.4.2.
utility cable specifications data bus cable specifications This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.5.1.
Power cable specifications This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.5.5.2.
ACCESS/PASSAGE WAYS
Vestibule clearances The interface requirement is in accordance with SSP 42007, paragraph 3.2.1.2.6.1.
Ingress/Egress passageways This interface requirement is in accordance with SSP 42007 paragraph 3.2.1.2.6.2.
RESERVED
Grounding This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.2.8.
SHIELDING
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.2.9.
FLUID INTERFACES
Reserved reserved
SUPPLY INTERMODULE ATMOSPHERE.
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.
intermodule Atmosphere SUPPLY characteristics intermodule atmosphere supply temperature This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.1.1.
intermodule atmosphere supply pressure This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.1.2.
intermodule atmosphere supply rate This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.1.3.
intermodule atmosphere SUPPLY humidity This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.1.4.
maximum oxygen concentration This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.1.5.
RESERVED
CONTROL INTERMODULE ATMOSPHERE SUPPLY
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.3.3.
RECEIVE RETURN INTERMODULE ATMOSPHERE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.
INTERMODULE ATMOSPHERE CHARACTERISTICS
INTERMODULE ATMOSPHERE RECEIVE RETURN PRESSURE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.1.1.
INTERMODULE ATMOSPHERE RECEIVE RETURN RATE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.1.2.
intermodule atmosphere receive return heat load This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.1.3.
INTERMODULE ATMOSPHERE receive return availability This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.2.
control RETURN INTERMODULE ATMOSPHERE This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.4.3.
RECEIVE ATMOSPHERE SAMPLE AIR
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.5.
atmosphere sample air receive flow rate This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.5.1.
atmosphere sample air receive pressure drop This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.3.5.2.
Reserved
ELECTRICAL POWER INTERFACES
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.
Note: The Node 2 Auxiliary Power (PMMN2A) does not apply to the HTV.
PMMN1N POWER OUTPUT CIRCUIT
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.
PMMN1N POWER SOURCE CHARACTERISTICS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.1.
PMMN1N IN FAULT PROTECTION
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.2.
PMMN1N/HTV−1 POWER CONTROL
PMMN1N/HTV−1 POWER ON/OFF CONTROL
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.3.1.
RESERVED
PMMN1N SOURCE IMPEDANCE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.4.
PMMN1N/HTV−1 SOURCE TURN_ON CHARACTERISTICS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.1.5.
PMMN2N/HTV_1 POWER OUTPUT CIRCUIT
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.
PMMN2N/HTV_1 POWER SOURCE CHARACTERISTICS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.1.
PMMN2N/HTV_1 FAULT PROTECTION
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.2.
PMMN2N/HTV_1 POWER CONTROL
PMMN2N/HTV_1 POWER ON/OFF CONTROL
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.3.1.
PMMN2N/HTV_1 SOURCE IMPEDance This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.4.
PMMN2N/HTV_1 USOS SOURCE TURN_ON CHARACTERISTICS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.2.5.
RESERVED
HTV-2 POWER output circuit This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.
HTV-2 power SOURCE CHARACTERISTICS This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.1.
HTV-2 fault protection This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.2.
HTV-2 power control HTV-2 power on/off control This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.3.1.
HTV-2 source impedance This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.4.
HTV-2 SOURCE TURN-ON CHARACTERISTICS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.4.4.5.
Command and data handling (c&DH) interface (ISS (NODE 2 and NODE 1) to HTV element) mil-std-1553B interfaces
DATA BUS STANDARDS
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.5.1.1.
reserved reserved reserved space station Local Bus This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.5.1.5 for applicable N1 and N2 interfaces.
Terminal operations This interface requirement is in accordance with SSP 42007, section 3.2.1.5.1.5.1 for applicable N1 Nadir, N2 Zenith, and N2 Nadir interfaces.
SOFTWARE FUNCTIONAL INTERFACES
This interface requirement is in accordance with SSP 42007, section 3.2.1.5.1.5.2 for applicable N1 Nadir, N2 Zenith, and N2 Nadir interfaces.
provide output amplitude This interface requirement is in accordance with SSP 42007, section 3.2.1.5.1.5.3 for applicable N1 Nadir, N2 Zenith, and N2 Nadir interfaces.
TERMINATIONS/jumpers This interface requirement is in accordance with SSP 42007, section 3.2.1.5.1.5.4 for applicable N1 Nadir, N2 Zenith, and N2 Nadir interfaces.
RESERVED
induced environments electromagnetic EFFECTS electromagnetic compatibility This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.1.1.
BONDING
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.1.2.
thermal reserved thermal interface for htv
PASSIVE INTERFACE TEMPERATURE
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.2.2.1.
CONDUCTIVE HEAT TRANSFER
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.2.2.2.
RADIATIVE HEAT TRANSFER
This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.2.2.3.
Deleted Deleted
STRUCTURAL LOADS
ON-orbit induced loads This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.4.1.
reserved on-orbit thermally induced loads on-orbit thermally induced structural loads This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.4.3.1.
on-orbit thermally induced structural loads spectra This interface requirement is in accordance with SSP 42007, paragraph 3.2.1.6.4.3.2.
HTV INTERFACE REQUIREMENTS
ENVELOPE REQUIREMENTS
Access envelope FOR UTILITY JUMPERS Envelopes reserved for utility jumpers shall be in accordance with SSP 41004, Common Berthing Mechanism to Pressurized Elements Interface Control Document, Part 1.
ACCESS ENVELOPE FOR EXTERNAL MAINTENANCE
The HTV external area requiring maintenance shall have reserved access envelopes in accordance with SSP 50005, International Space Station Flight Crew Integration Standard.
HTV berthing STAY-OUT zone envelope The HTV shall not interfere with the berthing stay-out zone shown in Figures 3.2.2.1.3-1, Berthing Stay-out Zone (page 1 of 3), 3.2.2.1.3-2 Berthing Stay-out Zone (2 of 3), and 3.2.2.1.3- Berthing Stay-out Zone (3 of 3). The definition of the berthing stay-out zone encompasses the envelope required for the CBM Meteoroid/Debris Covers.
The HTV shall be in accordance with the berthing stay-out zone envelope requirements defined in SSP 41004, Common Berthing Mechanism to Pressurized Elements Interface Control Document, Part 2.
FIGURE 3.2.2.1.3-1 BERTHING STAY-OUT ZONE (Page 1 OF 3)
FIGURE 3.2.2.1.3-2 BERTHING STAY-OUT ZONE (PAGE 2 OF 3)
FIGURE 3.2.2.1.3-3 BERTHING STAY-OUT ZONE (Page 3 OF 3) htv maximum structural envelope The HTV radius (from its center line) to the following components as shown in Figure 3.2.2.1.4-1, HTV Maximum Structural Envelope shall not exceed the following dimensions:
2,300 mm (90.55 in) to the surface of the solar arrays, and other components excluding the following items.
2,420 mm (95.28 in) to the tip of the Proximity Link System Zenith Antenna 2,530 mm (99.61 in) to the tip of the Reaction Control System thrusters 2,590 mm (101.97 in) to the tip of the FRGF
HTV MAXIMUM LENGTH
The HTV Length shall not exceed 10,020 mm (394.49 in) measuring from the tip of the Active Common Berthing Mechanism (ACBM)/PCBM interface plane to the tip of the Main Thrusters as shown in Figure 3.2.2.1.5-1, HTV Maximum Length.
FIGURE 3.2.2.1.4-1 HTV MAXIMUM STRUCTURAL ENVELOPE
FIGURE 3.2.2.1.5-1 HTV MAXIMUM LENGTH
STRUCTURAL/MECHANICAL INTERFACE
The HTV shall attach to the ISS via a CBM interface.
RESERVED
BERTHING/ATTACHMENT MECHANISM(S)
Interfaces between the CBM and the HTV shall be in accordance with SSP 41004.
The PCBM of the HTV shall support the capability to attach to and form a pressurized seal with the attached ACBM of the Node 1 and Node 2 Elements in accordance with SSP 41148.
reserved reserved interconnecting utility hardware The HTV interface shall incorporate provisions for the mechanical connection of data, power, atmosphere and atmosphere sample between the HTV and the ISS during on-orbit assembly.
Accessibility All internal vestibule utility interface connections shall be mateable after opening the Node 1 or Node 2 module hatch in the berthed configuration.
Vestib…
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