2016-A-3

Bartolomeo –
Commercial External Payload Hosting
Facility On ISS
Dr. Per Christian Steimle, Airbus DS GmbH, Space Systems, Bremen, Germany
Ron Dunklee, Airbus DS Space Systems Inc., Houston, Texas
Bill Corley, Teledyne Brown Engineering, Huntsville, Alabama
ISS R&D Conference, Presentation No. 2016-A-3, 12 July 2016

Bartolomeo Features
Payload mass FRAM standard
Payload volume FRAM standard
View Nadir / Zenith / Limb,
pointing, stabilization
Power up to 800 W
Data up to 100 Mbps
Cooling up to 1.5 kW, active
Mission duration End of ISS
Payload mission
lead time
12 – 18 months
Bartolomeo
Concept Features
Your view to
Earth
Various payload
sizes available
Commercial External Payload Hosting Facility on ISS
2
Remote Sensing
Astrophysics
Heliophysics
Atmospheric
Research
Space Weather
Material Science Robotics Testing
In-orbit
Technology
Testing
In-space
Manufacturing
Payload
resources
provided by
ISS
Your view to
the stars
Payload
cooling
available

Bartolomeo Mechanical Platform Design
Integrated Pallet Assembly
Mechanical Attachment to Columbus
3

Bartolomeo On-orbit Configuration (1/4)
4
JCAP-1
JCAP-2
JCAP-3
JCAP-4
JCAP-5
JCAP-6
Y-bar
FRAM-1
FRAM-2
FRAM-5
COL AIS
antenna
(relocated)
COL
Starboard
Trunnion
COL Port
Trunnion
Zenith
Ram
Platform designed to host
• 6 JCAP-based payloads
(STANDARD sites in business case)
• 6 FRAM-based payloads
(LARGE sites in business case)
Mechanical attachment to COL
Starboard, Port and Keel trunnions
using EUTAS and own interfaces
Flight configuration compatible with
SpaceX Dragon Trunk and
intermediate positioning at the
Payload/Orbital Replacement Unit
Accommodations (POA)
Bartolomeo platform optimized for
giving best viewing conditions
FRAM-6

5
FRAM-3
FRAM-4
FRAM-6
Nadir
Ram
Keel bar
COL Keel
trunnion
Active cooling system for payloads
Own power and data management
unit
Payloads accommodated using
standard mechanical / electrical /
robotic interfaces
Full compatibility with ISS robotic
systems
No EVA required for payload
installation / de-installation during
service phase

6
COL ADS-B and
AIS antenna
(relocated)
JCAP-based payloads
compliant with JEM-A/L
envelope
FRAM-based payloads
FRAM Extension Kit
Teledyne Brown MUSES
Active Cooling
System
Zenith

7
FRAM Extension Kit
Teledyne Brown MUSES
Zenith
COL ADS-B and
AIS antenna
(relocated)

Representative Payload Fields of View
8
Bartolomeo platform optimized for giving best viewing conditions to
its payloads (Nadir, Zenith, Ram direction)
Slots Nadir Zenith Ram Wake
STANDARD
JCAP-1
JCAP-2
JCAP-3
JCAP-4
JCAP-5
JCAP-6
LARGE
FRAM-1
FRAM-2
FRAM-3
FRAM-4
FRAM-5
FRAM-6
Payload Fields of View
in Zenith, Nadir, Ram and Wake direction
Zenith Nadir Ram Port Starboard Wake
Minimum 22.4% 1.1% 0% 57.6% 45.1% 44.6%
Maximum 34.4% 8.7% 5.3% 58.6% 48.1% 47.0%
Payload Field of View obscuration
Payload viewing quality assessment

Payload Compatibility with JEM-A/L
9
Bartolomeo will be the only external payload hosting facility
suitable for unpressurized and pressurized payload launch
Versatility gives frequent and repeating launch opportunities
Random vibration loads during launch significantly reduced
due to payload transportation in foam
Pressurized launch Japanese airlock utilization
Extra-vehicular Robotics Installation on Bartolomeo
Payload packed
in foam
Payload hard-
mounted

Bartolomeo Compared to Existing Sites
10
Other external payload hosting sites:
• Express Logistics Carriers (ELCs) with FRAM payload slots
• Japanese Experiment Module Exposed Facility (JEM-EF)
• Columbus External Payload Facility (COL-EPF)
• NanoRacks External Platform (NREP) for very small size payloads
0
200
400
600
800
1000
1200
1400
1600
0 500 1000 1500 2000 2500 3000
PayloadVolume[U]
Payload Mass [kg]
Bartolomeo
FRAM-based
Bartolomeo
JCAP-based
JEM-EF
(standard) JEM-EF
(large)COL-EPF
ELCs
NREP
Sites FOV Size [mm] Mass [kg] Power Data Cooling Payload Upload
ELCs Obstructed 864 x 1168 x 1245 up to 599
750 W @ 120 Vdc
500 W @ 28 Vdc
10 Mbps Ethernet
3 Mbps Wireless
No Unpressurized
COL-EPF Good 864 x 1168 x 1245 370 TBD
100 Mbps Ethernet
3 Mbps Wireless
No Unpressurized
JEM-EF Obstructed 800 x 1000 x 1850 500 – 2500
3000 – 6000 W @ 120 Vdc
1.2 kW @ 120 Vdc survival
100 Mbps Ethernet
TBD Mbps Wireless
900 W per
payload
Unpressurized
BTL
JCAP-based
Very good 640 x 830 x 1000 up to 100 up to 100 W @ 28 Vdc
100 Mbps Wireless
No
Pressurized /
UnpressurizedBTL
FRAM-based
Very good 864 x 1168 x 1245 300 – 599
800 W @ 120 Vdc
120 W @ 120 Vdc survival
1.5 kW for
2 payloads
NREP Obstructed 100 x 100 x 400 4 30 W @ 28 Vdc TBD Mbps Wireless No Unpressurized

Bartolomeo Launch
Configuration (1/2)
Platform designed to be launched with
one SpaceX Dragon flight
Possibility to upload up to 2 FRAM-based
payloads together with Bartolomeo
Pallet interfaces with Trunk beam
structure with 3 SpaceX-provided
brackets operated by Dragon
Bartolomeo requires one combined EVA /
EVR to be installed at COL
During unloading Space Station Remote
Manipulator System (SSRMS) interfaces
with the FRGF interface installed on
vertical pallet section
Guiding rails attached to two of the Trunk
side beams support removal operation
and allow narrowing the tolerance to
Dragon Trunk envelope
11
Guiding rails
y-bar
FRAM
Extension
Kit
Trunk
envelope
Additional
payload

Bartolomeo Launch
Configuration (2/2)
12
y-bar
FRAM
Extension Kit
Additional
payload

Bartolomeo Avionics System Design
Power Conversion and Distribution Concept
Payload Communication Concept
13

Power Conversion &
Distribution Concept
14
4 PFRAMs on Bartolomeo base
platform support all FRAM-based
standards
• Columbus EPF standard power
supply
• NASA ExPA payloads
• ORU FSE payloads
FRAM-based payloads receive
120 Vdc either from Columbus or
USOS, max. 750 W
JCAP-based payloads receive
28 Vdc from Columbus,
50 – 150 W
Survival power available for all
payload slots

Payload Communications Concept (1/2)
15
Bartolomeo nominal payload communication
paths:
• All payloads through the Bartolomeo WiFi access
point
• NASA payloads through USOS WiFi access point
• FRAM-based payloads through Ethernet lines with
the COL DMS using standard command and data
protocols
• FRAM-based payloads through USOS-provided
wired communication (MIL-Bus, Ethernet) TBD
Communication via BTL WAP uses MPCC which
allows direct TCP/IP based data transmission
between payload and user home base

Payload Communications Concept (2/2)
ISS link provides data throughput up to 1200 Gbit per day with 80 – 90 minutes TDRS contact per orbit
Bartolomeo avionics system compatible with Col-Ka Terminal
However, provision of own communication system to Bartolomeo on-board infrastructure under consideration
Laser communication can be a good option, LCT has < 50W power consumption, downlink data rate > 1 Gbit/s (target 10
Gbit/s)
• Transfer of 480 Gbit per 8 minutes ground station contact (signal acquisition at 5° elevation, ISS orbit altitude)
• Mean daily data down link could be extended to 4500 Gbit from ISS with currently
existing OGS network currently
• Optical Ground Station (OGS) network of 10 stations currently
developed by BridgeSat Inc. until end of 2017
Direct data transmission to ground supported by Bartolomeo avionics system
• Bartolomeo WAP supports up to 450 Mbit/s data transmission
• Intermediate storage of data for data transmission to ground, depending on availability and number of ground stations
16

Bartolomeo Active Cooling Capability
Active Cooling System
Payload Fluid Interface
17

Active Cooling Concept
18
• 2 FRAM-based payload slots with active cooling capability
• 6 pumps in parallel for redundancy
• Cooling fluid propanol or silicon oil
• Radiator size approximately 2 m2 radiating both in Nadir
and Zenith direction
• Total cooling capability up to 1.5 kW
P: Pump
VC: Volume
compensation tanks
V: Valves
QD: Quick
Disconnect
F: Filter
T: Temperature
sensor
Pr: Pressure sensor
Fl: Mass flow sensor
Vl: Volume sensor

Payload Mechanical / Electrical / Fluid Interface
Modification to the FRAM interface proposed
Fluid FRAM used to provide mechanical, power, data and fluid
interfaces for payloads with active cooling requirement
Interface to payloads is achieved via two Quick Disconnects
(QDs) accommodated in the third usually unused connector/cable
cover of the passive FRAM assemblies
QD mating between the Bartolomeo cooling loop and FRAM-
based payloads is achieved via a robotically operated mechanism
on the active FRAM
As back-up Bartolomeo will provide to two pairs of QDs to be
operated by EVA for those payloads which cannot accommodate
the robotically activated solution.
Integration of fluid interfaces into Active FRAM is expected from
NASA
As backup solution a manual connection of simple QD interfaces
in an Extra-Vehicular Activity (EVA) can be foreseen
Fluid interface design pending requirements and negotiation with
NASA
19
Connector
bracket for fluid
I/F provided
through QDs
Connector
bracket for
electrical power
and data
Fluid pipes
Flight Releasable Attachment Mechanism with Fluid Interface
Modification (Fluid FRAM)

Bartolomeo Operational Concept
Platform Servicing during Utilization
Integrated Service Concept
20

Platform Servicing During Utilization (1/2)
Bartolomeo to be operated as single payload on COL with varying configurations over time, user may operate payloads from ground with the
power / data budgets allocated over the increments
No requirement for EVA due to the robotic compatibility of the mechanical, electrical and fluid interfaces
Payloads may be launched / disposed unpressurized or pressurized, after launch in pressurized supply vehicle, each airlock-compatible
payload requires IVA with airlock cycle to transfer it to the outside and EVR to install
it onto the Bartolomeo platform
Platform servicing traffic predicted around 3 payloads
per year to be launched / disposed, not more than 2
airlock cycles per year
21
Payload
JEM-A/L
envelope
JCAP
interface
used in
JEM A/L
Unpressurized upload
(FRAM- and oversize JCAP-based payloads)
Pressurized upload
(JCAP-based payloads with JEM-A/L compatible dimensions)
(Source: NanoRacks / MDA)

Platform Servicing During Utilization (2/2)
Platform is fully compatible with ISS robotic manipulation systems, no EVA required during utilization phase
Use of standard robotic interfaces for installation / de-installation of payloads
Micro fixture interface to the SPDM used to handle the payloads
22
Robotic access corridor for payload installation on pallet
JCAP-based payloads FRAM-based payloads on Zenith side FRAM-based payloads on Nadir side

ISS R&D Conference, Presentation No. 2016-A-3, 12 July 2016 23
Payload transfer
to outside
Payload robotic
installation
Payload mission
Payload launch
Mission Duration 1 – 7 yearsMission Lead Time 1 – 1.5 years
Payload data
processing
and delivery
Bartolomeo
All-in-one Service Concept

Summary of Payload Standard Interfaces and Resources
24
Item JCAP-based Payloads FRAM Standard Payloads
Quantity of sites 6 6
Field of view • All Nadir and Zenith view
• 4 slots Ram view
• 2 slots Zenith and Ram view
• 2 slots Nadir, Ram, Wake
• 1 slot Zenith, Ram, Starboard
• 1 slot Nadir, Ram, Starboard
Geometric envelopes 640 x 830 x 1000 mm1 864 x 1168 x 1245 mm 864 x 1168 x 1245 mm
Mass per payload up to 100 kg nominal2 up to 599 kg nominal2,3 up to 300 kg nominal2,3
Power per payload • 2 x 28 Vdc operational power up to
50 W per each slot
• 1 x 28 Vdc 100 W additional power
selectable for one slot at a time
• 120 Vdc operational power up to
800 W, CEPA compatible4
• 120 Vdc operational power, ExPA
compatible5
• 120 Vdc operational power,
ExPA compatible5
Data rate to COL per
payload
up to 100 Mbit/s via Bartolomeo
wireless system
wireless system
wireless system
Cooling capability - • 1 Nadir, 1 Zenith site
• Up to 1.5 kW total cooling capability
-
Robotic interface SPDM micro fixture SPDM micro fixture SPDM micro fixture
Return capability Yes, if JEM-A/L compatible No No
Payload to platform
interface
JCAP bracket and electrical connector P-FRAM standard, P-FRAM modified
with fluid I/F
P-FRAM standard
1 Geometric envelope constrained by JEM-A/L dimensions,
envelope can be extended if payload is launched unpressurized.
2 Overall payload mass budget of the platform is 2800 kg.
3 FRAM capability depends on P/L CoG per SIDD for FRAM System Type 2, D684-10822-01 Rev. A, 2002/09/10
4 Power routed from COL PAPOS interface.
5 Power routed from USOS.

25
Contact
Dr. Christian Steimle
Project Manager Bartolomeo
ISS Evolutions and Commercial Applications
Airbus Defence and Space, Bremen, Germany
Email: per-christian.steimle@airbus.com
Mobile: +49 151 277 677 74
https://de.linkedin.com/in/dr-per-christian-steimle-46217b8a
Ron Dunklee
President and CEO
Airbus DS Space Systems Inc., Houston, Texas, United States
Email: rdunklee@airbusdshouston.com
Mobile: +1 281 414 3617
https://www.linkedin.com/in/rondunklee

2016-A-3

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