Maximizing ISS Utilization for Small Satellite Deployments and
External Hardware/Sensor Testing Photo credit: NASA
Slide 2
Sampling of Our ISS Customers 2
Slide 3
NanoRacks Satellite Deployments Size: 1 U (nanosat) to ~75 kg
(microsat) Low-cost 51.6 degree inclination, 385-420 KM Orbit
lifetime: 6-12 months (no propulsion) Frequent Launch: Multiple
times per year Rapid Launch: Typically 9-14 months from contract to
launch Deployment: Typically 1-3 months after berthing to ISS Soft
stowage internal ride Easy Contracting Photo credit: NASA
Slide 4
To date, NanoRacks has successfully launched 86 spacecraft to
ISS 64 satellites deployed from ISS 16 satellites at ISS awaiting
deployment 6 satellites returned to Earth In Pipeline (on
contract): 99 Nanosats 3 Microsats (40-50 kg) to be deployed via
KABER Photo credit: NASA Satellite Deployment Track Record
Slide 5
1. Deployers transported in CTBs 2. Launched by ISS visiting
vehicle 3. Deployers installed by ISS Crew 4. JEM Air Lock depress
5. Grappled by robotic arm 6. Deployers positioned by arm
Slide 6
7. Deploy 8. Robotic arm returns deployer to JEM airlock,
retracts and pressurizes 9. ISS Crew un-install first deployer;
repeat install/deploy for second set (if necessary)
Slide 7
NanoRacks CubeSat Deployer (NRCSD) Each NRCSD can deploy up to
6U of CubeSats 8 NRCSDs per airlock cycle, for a total of 48U
deployment capability ~2 Air Lock cycles per mission Photo credit:
NASA
Slide 8
NanoRacks Microsatellite Deployer System Up to ~75 kg
microsatellites Within specific volume constraints Kaber uses JEM
airlock and ISS robotic infrastructure as deployment platform SPDM
for microsatellite-class payloads Kaber Status Hardware delivered
for payload integration on April 14, 2015 Successfully passed 2 of
3 safety reviews Initial Flight: Microsatellite manifested on
SpaceX-8 (Sep. 2015) 2 Microsatellites on contract for future
flights Introduction to Kaber for Microsats
Slide 9
Kaber Payload Mass & Volume Constraints Max VOLUME: Shown
Below Envelope shown is JEM Airlock static envelope.
Mission-specific envelope reductions to accommodate tolerance
accumulations and micro-G disturbances are TBD. Additional envelope
available for other form factors (e.g., a reduction in width allows
an increase in length.) Mass: 75 kg Payloads may go over 75
kilograms in some cases. However, center of mass of s/c must be
within margin, and ballistic co-efficient of s/c must be less than
91.24 kg/m2 assuming Cd = 2. Length 78.00 cm Width 81.00 cm Height
56.00 cm Length 98.00 cm Width 66.00 cm Height 41.00 cm
Slide 10
Microsat (Kaber) Developer Timeline
Slide 11
Random Vibration Comparison & Flight Acceptance Launch
environment to ISS has significant advantages compared to rides on
alternative LVs Being wrapped in bubble wrap and soft cargo bags
significantly attenuates vibration experienced by s/c About 2 Grms
(actual) Testing Required for ISS Flight Safety Certification
Flight acceptance testing requires the Satellite be subjected to
random vibration along each axis using the profile shown. The test
period for each axis shall be 60 seconds. [1] Can take test wrapped
in bubble wrap Frequency (Hz)Maximum Flight Envelope (g2/Hz)
200.057 (g 2 /Hz) 20-1530 (dB/oct) 1530.057 (g 2 /Hz) 153-190+7.67
(dB/oct) 1900.099 (g 2 /Hz) 190-2500 (dB/oct) 2500.099 (g 2 /Hz)
250-750-1.61 (dB/oct) 7500.055 (g 2 /Hz) 750-2000-3.43 (dB/oct)
20000.018 (g 2 /Hz) OA (grms)9.47 Table 1 Random Vibration Test
Profile [1] [1] NASA SSP 50835, Rev C, TABLE 4.3.1.1.2.1.2.3.1-1
SUMMARY OF THE TEST CONDITIONS FOR FOAM PACKED ITEMS FOR
QUALIFICATION, PROTOFLIGHT, AND ACCEPTANCE TESTING
Slide 12
Other Satellite Program Requirements Battery flight acceptance
test Electrical: 3 inhibits minimum Customer responsible for
spectrum & remote sensing licensing Fault-tolerance for
deployables Non/low toxicity materials Secondary locking
features
Slide 13
External Platform Up to 9 4U cubesat size payloads outside the
ISS Standard mission duration 15 weeks Excellent viewing conditions
for Earth observation Full end-to-end mission service External
Payload Platform on JEM- EF 17 February 201513
Slide 14
External Platform Payload Configurations 17 February 201514
EPP-P standard 4U size payload package 1 2 3 4 5 6 7 8 9 Unique
payload configuration 10 cm 40 cm 10 cm 58 cm 57 cm 60 cm
Slide 15
External Platform System Design 15 Standard payload provisions
Voltage 28 Vdc 2 V or 120 Vdc as option Total power30 W at 28 Vdc
Maximum current2 A USB 2.0 bus 5 Vdc / 500 mA, non-switchable Total
payload data rate up to 8 Mbit/s WiFi interface Grapple fixture for
robotic arm operations Experiment packages baseplate Avionics
External Platform Flight Unit EP provides all functions of the
conventional spacecraft bus Ideal platform for small size hosted
payloads No further subsystems necessary Improved anomaly
resolution by human in the loop
Slide 16
ISS Manifest Status* Orb-5 3/30/16 SpX-116/2/16 Orb-6 6/30/16
SpX-128/24/16 Orb-710/4/16 HTV-6NET 11/1/16 SpX-132/7/17 * Subject
to change