SAT- 1 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. Mechanical Development of a Mesh Ka-­band Parabolic Deployable Antenna (KaPDA) for Interplanetary CubeSat Communications Jonathan Sauder 11/21/14

SAT- 2 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. The KaPDA Team Role:Name:Group: PI Mark Thomson 355 Co-I Tim Barrett USC/ISI Co-I Richard Hodges 337 Co-I Pezhman Zarifian 312 CogEJonathan Sauder355 RF AnalysisYahya Rahmat-SamiiUCLA RF Analysis Nacer Chahat337

SAT- 3 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. KaPDA Overview Challenge – Data rates are a limiting factor on CubeSat missions beyond LEO Objective – High-rate CubeSat communications with DSN –Over 100x increase over state-of-the art data rate requires a Ka-band deployable high-gain antenna (HGA) –Would provide over a 10,000x increase over a X-band patch antenna Solution – A low-cost deployable HGA stowing in ~1.5U –42 dBi goal at 34 GHz for downlink to DSN Ka-band High Gain Antenna at Mars Range (AU) Data Rate (bps) L1.01AU Moon.0026A U X-band, 1w, patch antenna Ka-band, 1w, deployable dish S-band, 1w, deployable dish Data Rate Comparison Artist’s Concept

SAT- 4 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. Existing CubeSat Antennas Existing parabolic and parabolic like antennas –Goer-wrap composite reflector –Reflector transformed from the CubeSat body –Inflatable cone/cylinder shaped reflector –Reflectarray –Mesh Antennas All are designed for S-band operation –Except for reflectarray Ka-band provides data rate advantages –But requires greater surface accuracy Mesh design was the most practical to upgrade –Specifically ANEAS parabolic deployable antenna –USC/ISI launched ANEAS in Sept –Architecture fits CubeSat form factor –Required complete redesign for Ka-band operation Existing Antenna Concepts

SAT- 5 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. General Architecture Key KaPDA Components KaPDA Stowed KaPDA Deployed Antenna configuration drove architecture –Cassegrainian design was improved for gain Similar folding rib geometry to ANEAS –Required additional sub-reflector, horn, and waveguide

SAT- 6 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. Deployment Design and Sequence

SAT- 7 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. KaPDA Parameters and Progress Parameters: –0.5 meter dish stowing within 1.5U –RF analysis shows ~43 dB of gain before manufacturing tolerances –Operations frequencies of 34.2 GHz to 34.7 GHz and 31.8 GHz to 32.3 GHz –Alternative configuration operates at 37.5 GHz for radar applications Progress: –Conceptual design has been completed –RF and structural analysis completed –Next Steps Deployment breadboard & static RF model Engineering Model RF verification of engineering model Expected Completion end of 2015 for 0.5 meter –Deliverable: flight-validated engineering model Table of Design Parameters Design Stretch Goal Diameter (m) Freqeuncy (GHz) Gain (dBi) Efficiency (%) 50 Size (U) Mass (Kg) Artist’s Concept

SAT- 8 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Mars CubeSat/NanoSat Workshop 2014 Nov , Pasadena, CA © 2014 California Institute of Technology. Government sponsorship acknowledged. Summary KaPDA stands to enable opportunities for a host of new Cubesat missions by allowing high data rate communication which would allow venturing further into deep space, including Mars missions. Artist’s Concept