NanoRacks Airlock OverviewNovember 2016

1The technical information contained within this presentation is considered EAR99 for export classification purposes.

NanoRacks Airlock - Your Commercial Doorway to Space

Develop, deploy and operate NanoRack’s next generation of ISS payload accommodation system –NanoRacks Airlock

• Builds upon NanoRack’s successful NanoLab Modules, NanoRacks CubeSat Deployers, NanoRacks External Platform, and Kaber systems

• Utilizes NanoRack’s access to world wide commercial payload customer base

• An enabling system to provide additional capability for future utilization of ISS

• Provides additional airlock capacity for deploying commercial satellites off of ISS

• Provides additional capacity for housing commercial payloads on ISS

• Currently envisioned for installation on Node 3, Port

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Node 3

Building a Bigger Door to Space

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• Current bottleneck at the JEM Airlock

• Limited size (~25 ft3, (0.70 m3))• ~10 openings per year with

restrictions on who uses those openings

• NanoRacks Airlock will expand those capabilities

• Over five times the volume (~141 ft3, (3.99 m3))

• Number of openings driven by commercial market and ISS availability

NR A/L Envelope

JEM A/L Envelope

Airlock Overview

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PVGF

Launch Vehicle FSE

MMOD Shielding

PVGF

Interior of NanoRacks Airlock is scarred with generic structural and electrical

interfaces to support sortie equipment

PCBM Bell Jar designNo hatch

Airlock Configuration

• Basic Info:• Weight: ~2,330 lbs (1,059 kg) total• CBM interface to ISS• Dragon trunk FSE similar to BEAM• Two PVGFs for ISS robotic handling

• Airlock Systems:• Structures• Command and Data Handling

System (CDHS)• Electrical Power System (EPS)• Thermal System• Video System

• ISS Supporting Systems:• Air Save Pump/Vestibule Depress

System• CBM Controller Panel Assembly

(CPA) fold down mechanisms

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Diameter ~83 in (2.1 m)

Length ~70 in (1.8 m)

ISS Node 3, Port Location

• Node 3, Port • Initial EVR access assessments complete

• Dragon extraction and installation with SSRMS based at LAB Nadir

• Deployments with SSRMS based at LAB Nadir• Contingency POA installation feasible too

• Some of the ISS resources already available (e.g. ventilation, power)

• Power: J22 (two feeds, one connector)• IMV Supply and Return• Add Ethernet interfaces for Joint Station

LAN (JSL) – J21 (Was allocated to 1553 but now will be used for Ethernet)

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Node 3 Port

Airlock Interfaces - Berthed

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• CDHS - Command & Data Handling System• EPS – Electrical Power System• EWC- External Wireless Communication• IMV – Intermodular Ventilation• WAP – Wireless Access Point

• Smoke detection via Node 3 IMV detectors

• Node 3 hatch may be open or closed• However, probably closed during

quiescent periods (little to no payload ops)

Power

Ethernet Data

Air Ventilation

Air Supply (IMV)

Air Return (IMV)

ISS Node 3 Port

Ethernet 10/100 (JSL)

120 VDC, 25A (Dual Feed)

CDHS

EPS

Depl

oyer

/Pay

load

Sy

stem

Coax to EWC WAP

External Wireless Coax

External Payloads (qty: 6)

J22

J21

J23

Airlock Interfaces – Deployed

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• CDHS - Command & Data Handling System• EPS – Electrical Power System• WAP – Wireless Access Point

• Power Video Grapple Fixture (PVGF) interfaces:

• Power (120 VDC, dual feed) • Data (MIL 1553)• Video (3 channels)• Second PVGF will provide identical

interfaces

• MIL 1553 commanding through PVGF for deployer commands – Safety critical data and commanding

• Wireless Ethernet utilized during deployed operations for nominal payload data and commanding

Power

Ethernet DataMIL 1553

CDHS

EPS

Depl

oyer

/Pay

load

Sy

stem

WAP

Video

External Payloads (qty: 6)

Concept of Operations

• Launch• SpaceX Dragon• Airlock in Dragon Trunk• No plans for hardware in soft stowage

• Installation• SSRMS ops from Dragon trunk to Node 3 Port Port - Ground• Berthing and CBM ops – Ground

• First installation utilizes CBCS system• Pressurization and Leak checks (via Node 3 ports) – ISS Crew

• Utilizes ISS resources for pressurization through equalization valve on hatch (first pressurization only)

• Hatch opening – ISS Crew• Centerline Berthing Camera Target removal – ISS Crew• Avionics cable hook up – ISS Crew• Ventilation system hook up – ISS Crew

• Activation and Commissioning• CDHS & EPS activation, Systems commissioning• Performed by NanoRacks Operations personnel• NR interface to ISS Ops via MCC-H• NR will monitor Airlock Systems after commissioning

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Airlock in SpaceX Dragon Trunk

CBCS Target

• Initial berthing to be performed using the CBCS Target System

• After hatch opening, target to be removed by the crew and stowed onboard in case of need for future use

• CBCS target and support structure can be broken down into a smaller more stowable configuration

• Future berthings will be performed using SSRMS digital data

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CBCS Target

EVR Operations

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EVR Operations (cont’d)

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Future Payload Operations

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• Future Payload Operations• Will be handled under separate agreements between NanoRacks and ISS Program• Operations to be coordinated between NR and MCC-H and POIC

• Typical Airlock Sortie:1. Payload satellite and deployer loaded into Airlock – Crew2. SSRMS grapple of Airlock – Ground3. Transfer of Airlock power from Node 3 to SSRMS - Ground4. Airlock power and data cables, IMV, and EWC coax cable disconnect – Crew5. Install CBM Controller Panel Assemblies6. Hatch closure and Air Save Pump hookup to hatch Equalization Valve – Crew7. Air Save Pump depress – Ground8. Vestibule residual air depress – Ground9. CBM bolt disengage – Ground10. SSRMS maneuver to deploy position – Ground11. Satellite deployment – Ground12. SSRMS maneuver back to Node 3 Port and berth Airlock (without CBCS) – Ground13. Air Save Pump repress and leak check – Ground14. Open Hatch – Crew15. Relocate CBM Controller Panel Assemblies16. Reconnect power and data cables, IMV, and EWC coax cable to Airlock – Crew17. Transfer of Airlock power from Node 3 to SSRMS - Ground18. SSRMS ungrapple - Ground19. Remove payload deployer hardware left behind and stow - Crew

Deploy Position

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Payload Capabilities

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Representative Smallsat/Microsat shown Lightband deployment mechanism

KABE

R Cl

ass

Depl

oyerNanoRacks Airlock: Shown with a smallsat for deployment

Airlock External Payload Sites

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NADIR

Six (6) External Payload Sites

Conceptual payload volumes shown for visual purposes only

Note: Payload volume definition in work

AFT

Airlock External Payload Sites (cont’d)

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• Utilize Oceaneering Space Systems (OSS) system

• General purpose Oceaneering Latching Device (GOLD)

• In development for MISSE-FF and will have flown prior to Airlock launch (CY 2017)

• Passive half mounted to Airlock pressure shell

• Active half mounted to payload• Redundant Power and Data

Interfaces• 120 VDC• Ethernet

• Payload mass: 1,000 lbs (453 kg)• Robotic mating/demating via SPDM • Payload deployment concept via NR

Airlock, JEM Airlock, or launched external to ISS cargo vehicle

Conceptual payload volume for visual

purposes only

Active Half

Passive Half

Airlock mounting bracket

Redundant electrical connectors

Micro Square Fixture (Micro Conical Fixture shown)

Note: Payload volume, data rate and power draw definition in work

Project Execution and Schedule

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• Engineering Design• Traditional design approach with SRR, PDR,

CDR• Fabrication start after CDR (Except long lead

items such as PCBM and pressure shell)• Hardware verified via inspection and testing• Verification of all requirements and ICD

compliance prior to flight• Traditional safety review process

• Phase 0, 1, 2, and 3 safety reviews• Verification of all safety requirements prior to

flight• Assembly and integration at NR Houston

• Final assembly and installation• Final integrated tests (e.g. FE1410 tests,

vehicle checks, continuity checks, etc)• Airlock sent to SpaceX for installation in

Dragon trunk

Item Milestone Date

1 Space Act Agreement Signed May 17, 2016

2 ISS CR Directive Signed July 28, 2016

3 SRR August 30, 2016

4 Phase 0 Safety TIM September 7, 2016

5 PDR February 2017

6 Phase 1 Safety Review March 2017

7 CDR August 2017

8 Phase 2 Safety Review September 2017

9 Start of integrated assembly May 2018

10 Phase 3 Safety Review September 2018

11 Integrated testing complete September 2018

12 Ship to Launch Site October 2018

13 Ready for Launch December 2018 *

* Manifesting process in work

Backup Slides

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Payload Envelope

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Payload envelope

Envelope trimmed to missPCBM guides and latches

PCBM

Payload Envelope65” (1,651 mm) Dia

Payload Envelope (cont’d)

• For installation of payloads into Airlock, they must pass through the CBM hatch

• The CBM Controller Panel Assemblies (CPAs) will be mounted on a fold down mechanism which restricts the opening to 41” square

• Note: CBM CPAs without the fold down mechanism furthers restricts clearance to 30” square

• Note: Full hatch opening: 50” square

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CBM CPA – No fold down mech

CBM CPA – With fold down mech

Payload Capabilities (cont’d)

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NanoRacks “HayBale” Deployable Cubesat Dispenser (144U capability in configuration shown)

“HayBale” is deployed from NanoRacks Airlock in similar fashion to ESPA/Kaber type satellites, using NRSS or

Lightband. NanoRacks Airlock is then re-berthed to ISS. Once adequately separated from ISS, the orbiting

“HayBale” deploys pairs of cubesats over time until deployments are complete. Empty “HayBale” orbit

degrades and “HayBale” is destroyed upon re-entry.

HAYB

ALE

Other Capabilities

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ORU

FSE

Battery FSE Battery ORU installed on FSE

NanoRacks Airlock: Shown outfitted with FSE so that an ORU can be can be brought into ISS for repair/replacement (Battery ORU shown)

Other Capabilities (cont’d)

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FRAM

FRAM Small Adapter Plate Assembly with ORU and MLI

Note: FRAM mounting structure not shown

NanoRacks Airlock: Shown with a FRAM-size ORU (which can be brought into ISS for repair)

Other Capabilities (cont’d)

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Tras

h Di

spos

al

Trash ContainerDeployment mechanism similar

to Kaber/NRSS deployment system

Guide rails 8x (ISS internal handrail

oval cross-section)

Trash Container Internal Volume 71 cubic feet (38 CTB) <TBD>;Diameter 54.5in, Length 58in

Trash Container access port with cover plate (25in dia

opening)

Velcro straps restrain Trash Container to Guide Rails during

filling ops (removed prior to deployment)

External Payload Capabilities

• Payload exposure for short duration (< 5 days) or long duration (>5 days)

• Power via SSRMS or Payload ORU Adapter (POA)

• 120 or 28 VDC from Airlock EPS• Data via ISS external wireless

• Ethernet through Airlock CDHS• Data storage available on Airlock CDHS also

• Examples:• Earth viewing cameras• Materials exposure• Space construction• Space sensors – Technology

development/verification

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Internal Payload Capabilities

• “Typical Rack/Locker” type internal payloads

• Interfaces similar to ISS Racks• Power via ISS Node 3

• 120 or 28 VDC from Airlock EPS• Data via wired Ethernet to ISS Node 3

• Ethernet through Airlock CDHS• Data storage available on Airlock CDHS

too• Examples:

• Locker payloads• Glove Box payloads• Frame payloads

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Airlock in SpaceX Dragon Trunk

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Airlock in SpaceX Dragon Trunk

Deploy Position (cont’d)

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POA Temp Stow

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POA Temp Stow (cont’d)

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