Cube Sat Proximity Operations Demonstration CPOD Overview InSpace

Cube. Sat Proximity Operations Demonstration (CPOD) Overview In-Space Inspection Workshop 2014 Houston, TX 07/16/2014 Austin Williams CPOD Vehicle Bus Lead Tyvak Nano-Satellite Systems Inc.

Operational View - Cube. Sat Proximity Operations Demonstration (CPOD) Tyvak Nano-Satellite Systems Inc. RSO Chaser UHF Ground Stations S-Band Ground Network Mission Operations Center (MOC) 2

System View - Cube. Sat Proximity Operations Demonstration (CPOD) Tyvak Nano-Satellite Systems Inc. SPACE SEGMENT CPOD Spacecraft A GPS Signal CMD / TLM RPO Sensors CPOD Spacecraft B RPO Sensors and Image Software Rendezvous, Proximity Operations (RPO) Payload Cube. Sat Bus GROUND SEGMENT UHF S-Band Inter-Satellite Link w/ Ranging USER SEGMENT LAUNCH / ORBIT INSERTION SEGMENT NASA-Tyvak 6 U Dispenser S-Band Tracking Stations VPN Mission Operations Center Hosted UHF Remote Station User / Customer Launch Platform / Orbit Insertion 3

CONOPS - Designed to Maximize Mission Success Probability Tyvak Nano-Satellite Systems Inc. Cube. Sat A performs RPO relative to Cube. Sat B Orbit Maneuvering to Initial Proximity Distance (Walking Safety Ellipse) Separate and Continue Checkout 4 b-c Decreased Range RPO & Docking Scenarios 6 7 A 5 Non-passively Safe Maneuvers Initial SOH 4 a Checkout CMD / TLM A CMD / TLM B Residual Ops CMD /TLM 3 10 CMD / TLM Disposal TLM 2 9 8 B Release together from 6 U dispenser Increased Range RPO Scenarios 11 CMD Launch Ground Network Main RPO Experiment Phases Mission-Planning / Pre-Launch 1 Mission Operations Center 4

Deployment Configurations and Vehicle Checkout Tyvak Nano-Satellite Systems Inc. 3 Connected “ 6 U” Configuration 4 a First Panel Deploy UHF Antenna Initial SOH Checkout 4 b-c Vehicle Separation Second Panel Deploy Complete Checkout 5

CONOPS Overview Tyvak Nano-Satellite Systems Inc. RENDEZVOUS ∆GPS via ISL Ranging NFOV Bearings Rbar Inject into 5. 1 Initiate Safety Ellipse 5. 2 NFOV Ranging Walking Safety Ellipse 100 s m B Vbar A DOCKING Stabilize into 5. 3 Safety Ellipse about Cube. Sat. B 4 Drift km’s during checkout Rbar NFOV Bearings & Ranging ISL Ranging Docking Bearings Docking Ranging IR 1 B & R IR 2 B & R Approach to WP 1 to WP 2 Approach & Dock Vbar Reduce Size Safety Ellipses & NFOV checkout 6 7. 6 B 7. 5 7. 4 Transfer to V-bar 7. 3 7. 1 Transfer to In. Plane NMC Reduced Size 7. 2 NMC Reduce Size Safety Ellipse & Docking Sensor checkout 6. 3 A 6

Space Vehicle Architecture Tyvak Nano-Satellite Systems Inc. SYSTEM PROCESSOR EPS Health & State Sensors Heater Power Sequencing ADCS State Estimation & Control Processor S-BAND (downlink) 3 -axis Sun Sensor Set UHF 3 -axis Magnetometer Set GPS Inter-Satellite link (Comm / Ranging) RPO Infrared Imager Docking Sensor Star Trackers w/ dedicated processing 3 -axis Reaction Wheel Set COMM Wide Field Visible Imager 3 -axis IMU Relative Position Estimation Processor (Imaging Processor) 3 -axis Mag. Torquer Set Maneuver Planning Processor (GN&C) Docking Mechanism Optical Target Aid 8 -thruster Cold Gas CONTRIBUTIONS Tyvak Nano-Satellite Systems Applied Defense Solutions 406 Aerospace VACCO 7

Vehicle Configuration - External Arrangement, Isometric Views Tyvak Nano-Satellite Systems Inc. Thermal Radiators GPS Patch Solar Panel Arrays with MPPTs Docking Mechanism S-Band Patch Thermal Radiator Separation Devices Star Trackers UHF Antennas 8

Remote Proximity Operations and Docking Module (RPOD) Tyvak Nano-Satellite Systems Inc. RPOD Module LED 35 mm IR Camera ISL Patch Antenna LED 50 mm IR Camera 70 mm Visible Camera LED 9

Vehicle Configuration - Internal Arrangement and Packaging Tyvak Nano-Satellite Systems Inc. GPS Receiver Battery Module Cold Gas Thrusters (8) S-Band Transmitter UHF Radio RPOD Module Inertial Reference Module (IRM) Propulsion Module Battery Module Endeavour Bus 10

1 U Endeavr Avionics Tyvak Nano-Satellite Systems Inc. UHF Radio and Antenna S-Band Radio Battery Module Torque Coils (3 x) Reaction Wheels (3 x) IMU C&DH and ADCS Star Trackers (2 x) Endeavour C&DH Control Processor 11

Algorithm Simulations Tyvak Nano-Satellite Systems Inc. Actual Range 20. 53 m Calculated Range 1 20. 52 m Range 1 Error 0. 05% Calculated Range 2 19. 38 m Range 2 Error 5. 93% Two Solutions 12

CPOD Performance Summary Tyvak Nano-Satellite Systems Inc. Capability Specification Comments Average ~17 W to 30 W Power Polar Sun-Sync OAP Generated Average Load ~15 W Fully Active Star Trackers Pointing <0. 15 degrees available under all Accuracy mission scenarios Mission Data Downlink Delta-V Total Mass ~60 MB / day UHF and S-Band ~20 m/s Cold Gas 5. 990 kg Wet Mass (13% Margin) 13

CPOD Integrated Flat-Satellite Tyvak Nano-Satellite Systems Inc. • Accomplishments to date – EDU avionics bring-up complete with 100% of subsystems functionally verified using software driver implementations – Complex low-level bus protocols functionally verified with flight data rates and electrical connectivity – Initial EMI compatibility testing complete – Vibration and Thermal Vacuum survivability tests – Reaction Wheel life testing complete – Star Tracker outdoor testing complete 14

Summary and Status Tyvak Nano-Satellite Systems Inc. • State of the art Proximity, Rendezvous and Docking system – Scalable architecture • Leverage on Tyvak’s Endeavour bus architecture • Sensor suite and algorithms created to interact with Tyvak’s vehicle • Great flexibility of operations • Design phase complete – Leveraging on multiple quick iterations with hardware evaluation • Main interface risks retired through early adoption of Flat. Sat and dedicated risk reduction environmental tests • Final iteration of Engineering Development hardware is on order – Qualification unit completed by November • Extensive mission assurance campaign through testing and ground demonstration 15

Tyvak Nano-Satellite Systems Inc. Questions? For additional inquiries, please contact: Dr. Marco Villa CPOD Program Manager Marco. Villa@tyvak. com 310 -956 -5973 16