Maximizing ISS Utilization for Small Satellite Deployments and External Hardware/Sensor Testing Photo credit: NASA

Sampling of Our ISS Customers

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

Satellite Deployment Track Record 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

2. Launched by ISS visiting vehicle 3. Deployers installed by ISS Crew 6. Deployers positioned by arm 1. Deployers transported in CTBs 4. JEM Air Lock depress 5. Grappled by robotic arm

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)

NanoRacks CubeSat Deployer (NRCSD) Each NRCSD can deploy up to 6U of CubeSats 8 NRCSD’s per airlock cycle, for a total of 48U deployment capability ~2 Air Lock cycles per mission Photo credit: NASA

Introduction to Kaber for Microsats 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 Photo credit: NASA

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 98.00 cm Width 66.00 cm Height 41.00 cm Length 78.00 cm Width 81.00 cm Height 56.00 cm

Microsat (Kaber) Developer Timeline Keep for CM

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) 20 0.057 (g2/Hz) 20-153 0 (dB/oct) 153 153-190 +7.67 (dB/oct) 190 0.099 (g2/Hz) 190-250 250 250-750 -1.61 (dB/oct) 750 0.055 (g2/Hz) 750-2000 -3.43 (dB/oct) 2000 0.018 (g2/Hz) OA (grms) 9.47 Table 1 Random Vibration Test Profile [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

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

External Payload Platform on JEM-EF 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 17 February 2015

External Platform Payload Configurations 58 cm 57 cm 60 cm 1 2 3 4 5 6 7 8 9 10 cm 40 cm EPP-P standard 4U size payload package Unique payload configuration 17 February 2015

External Platform System Design WiFi interface Standard payload provisions Voltage 28 Vdc ± 2 V or 120 Vdc as option Total power 30 W at 28 Vdc Maximum current 2 A USB 2.0 bus 5 Vdc / 500 mA, non-switchable Total payload data rate up to 8 Mbit/s Avionics Grapple fixture for robotic arm operations 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 Experiment packages baseplate External Platform – Flight Unit

ISS Manifest Status* Orb-5 3/30/16 SpX-11 6/2/16 Orb-6 6/30/16 HTV-6 NET 11/1/16 SpX-13 2/7/17 * Subject to change