NanoRacks Airlock Overview November 2016
The technical information contained within this presentation is considered EAR99 for export classification purposes. 1 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 Node 3 • 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
2 Building a Bigger Door to Space
• Current bottleneck at the JEM NR A/L Envelope Airlock • Limited size (~25 ft3, (0.70 m3)) • ~10 openings per year with JEM A/L Envelope 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
3 Airlock Overview
Launch PVGF Vehicle FSE
PCBM Bell Jar design No hatch
MMOD Shielding
PVGF Interior of NanoRacks Airlock is scarred with generic structural and electrical interfaces to support sortie equipment 4 Airlock Configuration
• Basic Info:
• Weight: ~2,330 lbs (1,059 kg) total Length ~70 in (1.8 m) • 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 Diameter ~83 in (2.1 m) • CBM Controller Panel Assembly (CPA) fold down mechanisms
5 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 Node 3 Port • 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)
6 Airlock Interfaces - Berthed
Power Ethernet Data • CDHS - Command & Data Handling System External Payloads Air Ventilation (qty: 6) • EPS – Electrical Power System External Wireless Coax • EWC- External Wireless Communication J22 • IMV – Intermodular Ventilation EPS 120 VDC, 25A (Dual Feed) • WAP – Wireless Access Point
Air Supply (IMV) • Smoke detection via Node 3 IMV detectors
• Node 3 hatch may be open or closed System
• However, probably closed during Air Return (IMV) quiescent periods (little to no payload Deployer/Payload ops) J21 CDHS Ethernet 10/100 (JSL) J23 Coax to EWC WAP
ISS Node 3 Port
7 Airlock Interfaces – Deployed
• CDHS - Command & Data Handling System External Payloads • EPS – Electrical Power System (qty: 6) • WAP – Wireless Access Point WAP • Power Video Grapple Fixture (PVGF) EPS interfaces: • Power (120 VDC, dual feed) • Data (MIL 1553) • Video (3 channels) Power • Second PVGF will provide identical interfaces System Ethernet Data MIL 1553 Deployer/Payload Video • MIL 1553 commanding through PVGF for CDHS deployer commands – Safety critical data and commanding • Wireless Ethernet utilized during deployed operations for nominal payload data and commanding
8 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
Airlock in SpaceX Dragon Trunk
9 CBCS Target
• Initial berthing to be performed using the CBCS Target System CBCS Target • 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
10 EVR Operations
11 EVR Operations (cont’d)
12 Future Payload Operations
• 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 – Crew 2. SSRMS grapple of Airlock – Ground 3. Transfer of Airlock power from Node 3 to SSRMS - Ground 4. Airlock power and data cables, IMV, and EWC coax cable disconnect – Crew 5. Install CBM Controller Panel Assemblies 6. Hatch closure and Air Save Pump hookup to hatch Equalization Valve – Crew 7. Air Save Pump depress – Ground 8. Vestibule residual air depress – Ground 9. CBM bolt disengage – Ground 10. SSRMS maneuver to deploy position – Ground 11. Satellite deployment – Ground 12. SSRMS maneuver back to Node 3 Port and berth Airlock (without CBCS) – Ground 13. Air Save Pump repress and leak check – Ground 14. Open Hatch – Crew 15. Relocate CBM Controller Panel Assemblies 16. Reconnect power and data cables, IMV, and EWC coax cable to Airlock – Crew 17. Transfer of Airlock power from Node 3 to SSRMS - Ground 18. SSRMS ungrapple - Ground 19. Remove payload deployer hardware left behind and stow - Crew
13 Deploy Position
14 Payload Capabilities
NanoRacks Airlock: Shown with a smallsat for deployment Deployer KABER Class KABER
Representative Smallsat/Microsat shown Lightband deployment mechanism 15 Airlock External Payload Sites
Six (6) External Payload Sites
AFT
Conceptual payload volumes shown for visual purposes only NADIR Note: Payload volume definition in work
16 Airlock External Payload Sites (cont’d)
• Utilize Oceaneering Space Systems (OSS) system Micro Square Fixture (Micro Conical • General purpose Oceaneering Fixture shown) Latching Device (GOLD) • In development for MISSE-FF and will have flown prior to Airlock launch (CY 2017) Active Half
• Passive half mounted to Airlock Redundant pressure shell electrical • Active half mounted to payload connectors
• Redundant Power and Data Conceptual payload Passive Half Interfaces volume for visual • 120 VDC purposes only • Ethernet • Payload mass: 1,000 lbs (453 kg) • Robotic mating/demating via SPDM Airlock • Payload deployment concept via NR mounting Airlock, JEM Airlock, or launched bracket external to ISS cargo vehicle Note: Payload volume, data rate and power draw definition in work 17 Project Execution and Schedule
• Engineering Design • Traditional design approach with SRR, PDR, CDR
• Fabrication start after CDR (Except long lead Item Milestone Date items such as PCBM and pressure shell) 1 Space Act Agreement Signed May 17, 2016 • Hardware verified via inspection and testing 2 ISS CR Directive Signed July 28, 2016 • Verification of all requirements and ICD 3 SRR August 30, 2016 compliance prior to flight 4 Phase 0 Safety TIM September 7, 2016 5 PDR February 2017 • Traditional safety review process 6 Phase 1 Safety Review March 2017 • Phase 0, 1, 2, and 3 safety reviews 7 CDR August 2017 • Verification of all safety requirements prior to 8 Phase 2 Safety Review September 2017 flight 9 Start of integrated assembly May 2018 10 Phase 3 Safety Review September 2018 • Assembly and integration at NR Houston 11 Integrated testing complete September 2018 • Final assembly and installation 12 Ship to Launch Site October 2018 • Final integrated tests (e.g. FE1410 tests, 13 Ready for Launch December 2018 * vehicle checks, continuity checks, etc) * Manifesting process in work • Airlock sent to SpaceX for installation in Dragon trunk
18 Backup Slides
19 Payload Envelope
Payload Envelope Payload envelope 65” (1,651 mm) Dia
PCBM Envelope trimmed to miss PCBM guides and latches
20 Payload Envelope (cont’d)
CBM CPA – With • For installation of payloads into fold down mech 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
CBM CPA – No fold down mech
21 Payload Capabilities (cont’d)
“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 HAYBALE degrades and “HayBale” is destroyed upon re-entry.
NanoRacks “HayBale” Deployable Cubesat Dispenser (144U capability in configuration shown)
22 Other Capabilities
NanoRacks Airlock: Shown outfitted with FSE so that an ORU can be can be brought into ISS for repair/replacement (Battery ORU shown) ORU FSE ORU
Battery FSE Battery ORU installed on FSE
23 Other Capabilities (cont’d)
NanoRacks Airlock: Shown with a FRAM-size ORU (which can be brought into ISS for repair) FRAM
FRAM Small Adapter Plate Assembly with ORU and MLI Note: FRAM mounting structure not shown 24 Other Capabilities (cont’d)
Trash Container Internal Volume Guide rails 8x (ISS 71 cubic feet (38 CTB)
Trash Container Velcro straps restrain Trash Deployment mechanism similar Trash Disposal Trash Container to Guide Rails during Trash Container access port to Kaber/NRSS deployment filling ops (removed prior to with cover plate (25in dia system deployment) opening)
25 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
26 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
27 Airlock in SpaceX Dragon Trunk
28 Airlock in SpaceX Dragon Trunk
29 Deploy Position (cont’d)
30 POA Temp Stow
31 POA Temp Stow (cont’d)
32