(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Mars CubeSat Workshop 21 November 2014 Peter Kahn Jet Propulsion Laboratory, California Institute of Technology. SmallSats /CubeSats Interface Standard for Payloads and Hosting Spacecraft JPL Innovation Foundry

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. CubeSats as Mission Multiplier, Secondary Payloads Requirement to limit impact on the mothership sets the bar high  Grant navigation control and telecom responsibility on deployer

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Purpose and Objectives of the PDCS Objectives: Develop and demonstrate a modular: 1) Deep Space Secondary Payload Data Handling and Relay Communications System Avionics 2) Mechanical Deployment & Containment System Purpose: Becomes the “standard” mechanical, data, and telecommunications interface for secondary, deployable payloads A system that enables unique science enhancements via secondary spacecraft for larger planetary missions Simplifies the integration of CubeSats or SmallSats with any hosting planetary spacecraft

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. OR Deep Space Qualified Standard Deployer Fits standard 1-6U “CubeSats” Provides mechanical containment & isolation, limited radiation shielding, and thermal control Launch Rail or Custom Separation Interface Light Weight (more payload mass) Increased volume envelope More flexible payload configuration Mounting Bracket & Connector Provides mechanical i/f to mothership, incl. vibration isolation Provides electrical & data i/f to PDCS for in-flight battery charging, heaters, health checks & software updates Optional deployment camera Payload Data & Communication System (PDCS) Commands payloads and provides relay telecom Manages payloads during cruise (electrical power, heaters, data monitoring & updates) Stores & forwards deployed payload data (on- demand or continuous read-out modes) Located on deployer or within mothership <2kg, <2L internal volume est. Relay Antennas Distributed on mothership for omnidirectional coverage Deep Space Deployable Payloads Architecture Mothership Deployable Payloads PDCS Avionics PDCS Deployer 6U 3U 1U June 25, Custom Deployer

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Accommodation & Mission and Requirements Mass Allocation Estimate – ~5 kg Deployer (PDCS) + up to 10 kg payload (Cubesat) Power Allocation Estimate – ~15 W peak for transmit, ~2-5W standby/receive Mechanical Interface to Host S/C – Clear, unobstructed FOV to deploy secondary payload S/C Downlink allocation for packetized data – Store & forward or bent pipe capability Demonstration on Mars Missions Can be deployed at the end of primary science mission or earlier if preferred 2pi steradian antenna coverage possible (no demand on s/c attitude) Optional deployment camera 300 mm 260 mm 6U Cubesat (payload) Deep Space Deployer System (DS 2 ) Payload Data and Communications System (PDCS)

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Simplifies the complex interface requirements of “mother-ship” integration Two-way telecomm and navigation Data handling and storage Maintains health of secondary payload during cruise (e.g. thermal, battery charging, radiation shielding) Supports in-flight Calibration Simplifies analysis of electromagnetic and mechanical interference via standardized form factor and interface (reduces risk) Can host 6U or 2x 3U, CubeSats as secondary payloads

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. PDCS Overview Deep Space Qualified Commercial CubeSat Dispenser (e.g. CSD derivative, 3U or 6U) Optional Additional Relay Antenna for Omni Coverage Relay Antenna (UHF or S Band) PDCS Avionics Power Board Relay Board (UHF or S-Band) + MSP430 Optional Deployment Camera Host Spacecraft Payload Connector Survival Heater LEON3 FT CDH Board Power RF Data

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. 8 DS 2 Deployed Configuration Details Standoff for thermal isolation from mothership + clearance for release door Nonexplosive door release mechanism ( Door hard stops Release door (deployed) Patch heaters Deployer designed for standard Cubesat interface Deployment spring can be sized for payload mass, ΔV requirements

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. 9 Mission Structural Accommodation Stowed Payload release

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Not All Interplanetary CubeSats are actually “cubes”: PDCS need not be form-factor limited 10 November 11th, 2014 Aerocapture delivery concept of payloads to Mars orbit Notional Venus Aerocapture delivery concept

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Current Dispenser Options 6U or 3U Planetary Systems Corp “Canisterized Satellite Dispenser” (CSD) – Includes proven separation connector – Options for MLI and vibration isolators as needed – TRL 9 – To be augmented with strip heater to provide survival heat to payload in “off” state 6U or 3U design by CalPoly SLO – Based on the existing P-POD design – Customized and light weight options may be available, e.g. If light-weighted, it offers no EMI/EMC shielding 3U CSD 6U Cal Poly PDSD

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Contributing Team Members Archer Eric D (337F) Telecommunications Banazadeh Payam (312D) Systems Barltrop Kevin J (349A) Avionics/C&DH Becker Raymond A (353J) Thermal Boland Justin S (382E) Instrument/Electronics Castillo-Rogez Julie C (3227) Science Duncan Courtney B (337G) Telecommunications/Radio Lead Dhack Muthulingam (3466) Electrical power System Frick Andreas (312E) Systems Lead ** Hansen David M (337H) Telecommunications Link Margins Jones, Stephanie (312D) Systems and RTB Lead for Cal Poly Project Klesh Andrew T (312A) Systems Komarek Tomas A (6100) Mars Applications Schone Harald (5100) Mission Assurance Thompson Mark K (5128) Mechanisms Tinto Massimo (3330) Telecommunications Wang K. Charles (352B) Configuration Ziemer John K (1510) Formulation Projects Coatta Daniel M (352B) Configuration Lead Henrikson, John (385G) CAD Design