(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Mars CubeSat

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only.

Mars CubeSat Workshop

21 November 2014Peter Kahn

Jet Propulsion Laboratory, California Institute of Technology.

SmallSats /CubeSats Interface Standard for Payloads and Hosting

Spacecraft

JPL Innovation Foundry


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


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


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 Deployer6U

3U

1U

June 25, 2014 4

Custom Deployer


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 (DS2)

Payload Data and Communications System (PDCS)


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


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

PowerRFData


8

DS2 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


9

Mission Structural Accommodation

Stowed

Payload release


Not All Interplanetary CubeSats are actually “cubes”: PDCS need not be form-factor limited

10November 11th, 2014

Aerocapture delivery concept of payloads to Mars orbit

Notional Venus Aerocapture delivery concept


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


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

Documents

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Mars CubeSat