Autonomous Large Distributed CubeSat Space Telescope (ALDCST)

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Autonomous Large Distributed CubeSat Space Telescope (ALDCST) ASTE 527: Space Exploration Architectures Concepts Synthesis Studio Midterm Presentation October 16, 2012 Professor: Madhu Thangavelu Concept Presentation: Jesus Isarraras

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Autonomous Large Distributed CubeSat Space Telescope (ALDCST). ASTE 527: Space Exploration Architectures Concepts Synthesis Studio Midterm Presentation October 16, 2012 Professor: Madhu Thangavelu Concept Presentation: Jesus Isarraras. BACKGROUND / HISTORY. NASA - PowerPoint PPT Presentation

Transcript of Autonomous Large Distributed CubeSat Space Telescope (ALDCST)

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Autonomous Large Distributed CubeSat Space Telescope

(ALDCST)ASTE 527: Space Exploration Architectures Concepts Synthesis StudioMidterm Presentation October 16, 2012Professor: Madhu Thangavelu

Concept Presentation: Jesus Isarraras

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BACKGROUND / HISTORYBACKGROUND / HISTORY• NASA

– Hubble Space Telescope; ~570km LEO orbit; 2.4m mirror aperture– James Webb Space Telescope scheduled for launch in 2018; 1.5M km (Earth-

Sun Lagrangian L2) orbit; 6.5m mirror aperture– Studying next generation UVOIR space observatory through the Advanced

Technology Large-Aperture Space Telescope (ATLAST)

• California Polytechnic State University & Stanford– Developed CubeSat Standard

• Cal Tech & University of Surrey– Autonomous Assembly of a Reconfigurable Space Telescope (AAReST)

Technology Development– Surrey Training Research and Nanosatellite Demonstrator (STRaND) payload

development for AAReST

• Naval Post Graduate School– Pseudospectral Estimation for optimal controls problems

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RATIONALERATIONALE

• Develop key technologies and architectures for large space apertures to improve the capability of future imaging and sensing using CubeSat innovations

http://www.jwst.nasa.gov/comparison.html 3

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ATLAST-8mATLAST-9.2mATLAST-16m

TIMELINE OF TECHONOLOGIES FOR TIMELINE OF TECHONOLOGIES FOR ADVANCED TELESCOPESADVANCED TELESCOPES

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2012 2013 2014 2015 2016 2017 20182020’s

1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q

STRaND-1

S-Android Logo

STRaND-2

S-Android Logo

ARReST

JWTSDirect Tech Insert

Direct Tech Insert

Payload contains Google

Nexus Smartphone;

Nexus will fully control nanosat

Kinect Tech for 3D modeling spacial awareness

Kinect

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ASSUMPTIONS / GROUNDRULESASSUMPTIONS / GROUNDRULES

• Time frame: 10 years• Successful STRaND – 1 mission in 2012• Successful STRaND – 2 mission in 2014• Successful ARReST mission in 2015• Successful JWTS launch and mission in 2018• Adaptive Optics• Gap size between sub-mirrors is < 0.01D; aberration is

minimized

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CONCEPT - PROPOSALCONCEPT - PROPOSAL• Provide an alternative architecture

for large primary mirror (D>20m) for space telescopes– Alternative for next generation UVOIR

telescopes (e.g ATLAST)– CubeSat cluster with segmented mirrors– Autonomous formation and control

• Potential Benefits– Potential lower cost and mass– Mirror segment replacement– Removes human activity for fielding– Faster production/manufacturing

http://www.jwst.nasa.gov/comparison.html

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CONCEPT - LOCATIONCONCEPT - LOCATION

• Direct extrasolar planetary observations become possible with large (D>20m) apertures– Earth-Sun Lagrangian point L2– Opportunity to study early

universe phenomena, monitor extremely faint and distant galaxies, dark matter and dark energy http://www.jwst.nasa.gov/comparison.html

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CHALLENGESCHALLENGES

Deployable mirror segment alignmentAchieving high surface accuracy of a large

segmented mirror (optical figuring)Surface and structure control stabilization

• Vibration isolation and potential jitter control• Control of adaptable/flexible mirrors

Wavefront sensing and correction (sensors)Thermal management/distortion mitigationPower management of segmented architecture

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COMPLEX SUBSYSTEMSCOMPLEX SUBSYSTEMSArchitecture - StructureArchitecture - Structure

• Launcher to hold multiple layers

• Layers deployed in sequence

• Each layer contains 6 segments

• Each segment contains N mirrors

NN

th L

ayer

11st

Inne

r Lay

er (c

ente

r)

22n

d In

ner L

ayer

Launcher 9

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COMPLEX SUBSYSTEMSCOMPLEX SUBSYSTEMSArchitecture - StructureArchitecture - Structure

Nth CubeSat Layer of Mirror

Top view of Nth Layer

Expands to create Hexagon Shape

Hex-Frame: provides stability and links Pod’s together

Flexible joints connecting sat’s

Top view of Nth Layer

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COMPLEX SUBSYSTEMSCOMPLEX SUBSYSTEMSArchitecture - StructureArchitecture - Structure

Autonomous formation• Control

− ADC− Advanced algorithms (e.g PS)

• Sensing− Lasers, optical, IR

• Actuation− Cold Gas, PPT, Hall

• Comm− Short range wireless− LOS Wireless− Laser

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COMPLEX SUBSYSTEMSCOMPLEX SUBSYSTEMSArchitecture – Structure LayersArchitecture – Structure Layers

Layer# of Mirrors per Layer

Diameter

1 6 0.32 12 0.53 18 0.74 24 0.95 30 1.120 120 4.150 300 10.175 450 15.1100 600 20.1

100 mirrors

99 mirrors

100 mirrors99 mirrors

Total Mirrors: 30,300Total CubeSats: 30,300Total Layers: 5,050Total Segments: 600

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CONCEPT - COMPLEX SUBSYSTEMSCONCEPT - COMPLEX SUBSYSTEMSArchitecture – Deformable MirrorArchitecture – Deformable Mirror

• Thin deformable mirrors with integrated actuators– >200 independent

actuators– Wavefront correction for

each mirror (algorithms)– Improved light gathering

power– Improved resolution– Thermal management

through shape/curvature correction

370μm

http://www.kiss.caltech.edu/study/largestructure/technology.html

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Primary material: Polyvinylidene flouride (PVDF)

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CONCEPT - COMPLEX SUBSYSTEMSCONCEPT - COMPLEX SUBSYSTEMSArchitecture – Advanced GN&CArchitecture – Advanced GN&C

• Pseudo-spectral estimation – GN&C stability of complete cluster structure – Optimal motion planning for autonomous vehicles in

obstacle rich environments– Constraint Non-Linear Problems

The Zero Propellant Maneuver demonstrated on the ISS. November 5, 2006 rotated 90 deg and March 3, 2007 rotated 180 degrees

Autonomous Reentry and Decent of Reusable Launch Vehicles 14

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CONCEPT - EVOLUTIONCONCEPT - EVOLUTION

• Mirror packaging• Mirror wavefront sensors• Flight formation sensors• Adaptive optics systems• Mirror actuators• CubeSat P-POD and dimension growth • Instrumentation (cameras, sensors, etc)

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CONCLUSIONSCONCLUSIONS

• Large apertures can be created through CubeSat Cluster design

• Segmented and adaptable mirrors future of telescope design

• Complex CubeSat architectures affordable options of the future

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FUTURE QUANTITATIVE FUTURE QUANTITATIVE STUDYSTUDY• Secondary Mirror Deployment • Aberration and Mirror stabilization• Orbit definition• Thermal management of cubesat’s and system

architecture (e.g Passive – radiate heat to space vs active – refrigerator system)

• Sun shield technology• Radiation hardening requirements• Power Management• Communication architecture

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REFERENCESREFERENCES1. Patterson, K., Yamamoto, N., Pellegrino, S. (2012). Thin deformable mirrors for a reconfigurable space telescope.

Retrieved from http://pellegrino.caltech.edu/PUBLICATIONS/AIAA_SDM2012_1220023%20(2).pdf

2. Postman, M. (2009). Advanced Technology Large Aperture Space Telescope Study NASA. Retrieved from http://www.stsci.edu/institute/atlast/documents/ATLAST_NASA_ASMCS_Public_Report.pdf

3. Keck Institute for Space Studies. (2012)http://www.kiss.caltech.edu/lectures/index.html

4. Steeves, J., Patterson, K., Yamamoto, N., Kobilarov, M., Johnson, G., Pellegrino, S. (2012). AAReST Technology Development. Retrieved from http://kiss.caltech.edu/workshops/smallsat2012/presentations/steeves.pdf

5. Patterson, K., Pellegrino, S., Breckinridge, J. (TBD) Shape correction of thin mirrors in a reconfigurable modular space telescope. Retrieved from: http://www.kiss.caltech.edu/study/largestructure/papers/patterson-pellegrino-breckinridge.pdf

6. McClellan, J. (TBD). Aurora Flight Sciences CubeSat Cluster. Retrieved from: http://icubesat.files.wordpress.com/2012/06/icubesat-org-2012-c-3-3-_presentation_mccellan_201205251247.pdf

7. Padin, S. (2003). Design Considerations for a Highly Segmented Mirror. Retrieved from: http://authors.library.caltech.edu/5664/1/PADao03b.pdf

8. Postman, M. (2007). Advanced Technology Large-Aperture Space (ATLAS) Telescope: A Technology Roadmap for the Next Decade. Retrieved from: http://www.stsci.edu/institute/atlast/documents/Submitted_proposal_TEAM_DISTN.pdf

9. Fundamental Optics. Retrieved from: http://cvimellesgriot.com/Products/Documents/TechnicalGuide/Fundamental-Optics.pdf

10. Naval Post Graduate School. (2012). Conference Papers. Retrieved from: http://www.nps.edu/academics/gnclab/Conference.html

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Thank you for your time!

Jesus [email protected] 19

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BACKUP CHARTS

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CONCEPT - COMPLEX SUBSYSTEMSCONCEPT - COMPLEX SUBSYSTEMSLarge Space Aperture Architecture ComparisonLarge Space Aperture Architecture Comparison

ALDCST HST JWST Herschel Space Observatory

Type of Mirror Segmented Monolithic Segmented Monolithic

Primary Aperture (m) 20 2.4 / 0.3 6.5 3.5

Mirror Mass (kg)

635 (mirrors, actuators) 828 705 300 (full telescope)

Wavelength (μm)

.11 - 2 (UV,IR) 0.8 – 2.5 (IR)0.1 – 0.8 (UV, visible) 0.6 to 28 (IR) 60 to 500 (IR)

OrbitEarth-Sun L2

Lagrange point; 1.5 million km

LEO; 570km Earth-Sun L2 Lagrange point; 1.5 million km

Earth-Sun L2 Lagrange point; 1.5 million km

Resolution 10 μm in IR 0.1 arcsec in red light;Main camera; 16M pixels

2 μm in IRMain camera: 32M pixels 5 – 50 arcsec

Size (L x W) (m) TBD 13.2 x 4.2 22 x 12 9 x 4.5

Mission Length 10 yr? 15 5-10 yr >3

Total Dev Cost ($M) <$1B $1.5B $1B €1.1

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Preliminary Mass CalculationsPreliminary Mass Calculations

• From Patterson, K., Pellegrino, S., Breckinridge, J. Shape correction of thin mirrors in a reconfigurable modular space telescope

Complete mirror structure w/ areal density ~2kg/m^2:

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COMPLEX SUBSYSTEMSCOMPLEX SUBSYSTEMSArchitecture - StructureArchitecture - Structure

Hex-Frame Contains•ADC•Comm Link Enhancement•Layer Stabilization•Network Communication

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CONCEPT - COMPLEX SUBSYSTEMSCONCEPT - COMPLEX SUBSYSTEMSArchitecture – Secondary Mirror & InstrumentsArchitecture – Secondary Mirror & Instruments

6U CubeSat

10cm

10cm

Secondary Mirror Deployer Instruments

(Camera, Optical/IR Sensors, etc)

Focal Plane Detector

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Formation Flying Control ChallengesFormation Flying Control Challenges

• Complexity– Systems of systems (interconnection/coupling)

• Communication and Sensing– Limited bandwidth, connectivity, and range– What? When? To whom?– Data Dropouts, Robust degradation

• Arbitration– Team vs. Individual goals

• Resources– Always limited, especially on a CubeSat

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Hubble Space TelescopeHubble Space Telescope

• Payload: Optics: The telescope is an f/24 Ritchey-Chretien Cassegrainian system with a 2.4 m diameter primary mirror and a 0.3 m Zerodur secondary. The effective focal length is 57.6m. The Corrective Optics Space Telescope Axial Replacement (COSTAR) package is a corrective optics package designed to optically correct the effects of the primary mirror's aberration on the Faint Object Camera (FOC), Faint Object Spectrograph (FOS), and the Goddard High Resolution Spectrograph (GHRS). COSTAR displaced the High Speed Photometer during the first servicing mission to HST.

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Hubble Space TelescopeHubble Space Telescope

• Instruments: The Wide Field Planetary Camera (JPL) consists of four cameras that are used for general astronomical observations from far-UV to near-IR. The Faint Object Camera (ESA) uses cumulative exposures to study faint objects. The Faint Object Spectrograph (FOS) is used to analyze the properties of celestial objects such as chemical composition and abundances, temperature, radial velocity, rotational velocity, and magnetic fields. The FOS is sensitive from 1150 Angstroms (UV) through 8000 Angstroms (near-IR). The Goddard High Resolution Spectrometer (GHRS) separates incoming light into its spectral components so that the composition, temperature, motion, and other chemical and physical properties of objects can be analyzed. The HRS is sensitive between 1050 and 3200 Angstroms.