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Small Payload Rideshare Conference, June 2015, Applied Physics Laboratory, Laurel, MD Right-Sized Nanosatellites: Finding the Sweet Spot between 3U/6U and ESPA June 9, 2015 Clint Apland (240) 228-0388 clint.apland@jhuapl.edu

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2 SPRC, June 2015, JHU/APL Need and Motivation Express-class Space Vehicle Features and Benefits Payload Provisions and Suitability to Payloads with Significant Mission Utility Benefits of Rectangular Adaptor Systems First Generation Adapter System Second Generation Adapter System Future Work Topics to Discuss

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3 SPRC, June 2015, JHU/APL Motivation for Express Class An intermediary mission class standard is needed between ESPA (181 kg) and 3/6U CubeSat (~4-12 kg), to: More optimally utilize excess LV secondary payload rideshare accommodation capability. Enable lower cost missions when ESPA-class not needed. Provide for more flexible and capable space vehicles than possible w/ 3U-6U CubeSat (physical) constraints: E.g., larger payloads, greater power generation, propulsion Permit more ready-use of COTS components and technologies. Poly- Picosat Orbital Deployer (P-POD) NASA Ames (3/6U) NLAS Dispenser Atlas V ESPA Configuration Express Initial top-down/bottom-up study performed by APL in 2010-11

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4 SPRC, June 2015, JHU/APL Launching high performance, reliable nanosatellites featuring inexpensive and reliable separation systems is possible over a wide selection of launch vehicles Optional shroud alleviates concerns of primary Payload (PL) damage Protects/conceals contents from: Visual inspection Physical access and tampering Aero-heating, thruster plume thermal Acoustics and contamination EMI/EMC Provides a standard, flexible spacecraft interface compatible with multiple LVs: For secondary manifest: oSpace-X Falcon 1e/9/9H oOSC Minotaur I/IV/V, Antares,Taurus XL oULA Atlas V, Delta IV oLM/ATK Athena IIc For primary manifest: oORS Super-Strypi oSMDC Nano-Launcher* oDARPA ALASA* Bridges gap between 3U/6U and ESPA *To be investigated as data becomes available Express Class: 25-75 kg Standardized Nanosatellite 47.0 cm (18.5 in) 26.4 cm (10.4 in) 55.8 cm (22 in) W/ Propulsion W/O Propulsion

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5 SPRC, June 2015, JHU/APL FEATUREBENEFITS Configurations with or without propulsion. > 225 m/s V chemical propulsion allows rideshare flexibility; enables formation flying and constellations. Non-propulsion is lower cost and accommodates larger payloads within standard volume. Multiple PL data interfaces. Allows >two independent payloads. Large payload volume.Propulsion: 6,500 cm 3 (400 in 3 ) Propulsion Extended: 35,000 cm 3 (2100 in 3 ) Non-propulsion: 20,000 cm 3 (1200 in 3 ) Size, shape and mass less constraining than CubeSats. Allows more use of COTS components, can still benefit from use of CubeSat components, appendages can protrude if necessary. Simplified Adaptor & Separation System Simple, proven, low cost, allows axial or radial deployment, easily adapted to any LV. Flyaway half of separation system can double as bottom deck of SV. Available shroud.Provides protected environment, prevents visual inspection, tamper-resistance prevents access. Express Features and Benefits

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6 SPRC, June 2015, JHU/APL Nominal PL Mass: 21 kg w/o propulsion; 8 kg w/ propulsion Data processing capability may be supported by S/C C&DH Flexible S/C software architecture with encryption capability Time: 1 pulse per second, GPS referenced Solid State Recorder (Mass Memory) is scalable Nominal PL Power: Orbit Average (typical orbit): >10 W Peak: 100 W Available Voltages: Unregulated Bus: 28 V (24 to 33 V) Regulated: 3.3 V and 5.0 V @ >4 A; Adjustable Attitude Determination & Control: Full 3-axis (zero momentum) Control