Transcript Hubble Space Telescope - University of Southern California

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
– 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
2
RATIONALE
• 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
TIMELINE OF TECHONOLOGIES FOR
ADVANCED TELESCOPES
2012
2013
2014
2015
2016
2017
2018
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
Direct Tech Insert
2020’s
JWTS
Direct Tech Insert
ARReST
STRaND-1
STRaND-2
S-Android Logo
Payload
contains Google
Nexus
Smartphone;
Nexus will fully
control nanosat
Kinect
ATLAST-8m
ATLAST-9.2m
ATLAST-16m
S-Android Logo
Kinect Tech for 3D modeling
spacial awareness
4
ASSUMPTIONS / 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
5
CONCEPT - 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
6
CONCEPT - 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
7
CHALLENGES
Deployable mirror segment alignment
Achieving 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 mitigation
Power management of segmented architecture
8
COMPLEX SUBSYSTEMS
Nth Layer
N
2
1
1st Inner Layer (center)
2nd Inner Layer
Architecture - Structure
Launcher
• Launcher to hold
multiple layers
• Layers deployed in
sequence
• Each layer contains 6
segments
• Each segment
contains N mirrors
9
COMPLEX SUBSYSTEMS
Architecture - Structure
Nth CubeSat Layer of
Mirror
Hex-Frame: provides stability
and links Pod’s together
Top view of Nth Layer
Flexible joints connecting sat’s
Top view of Nth Layer
Expands to create
Hexagon Shape
10
COMPLEX SUBSYSTEMS
Architecture - 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
11
COMPLEX SUBSYSTEMS
Architecture – Structure Layers
Layer
1
2
3
4
5
20
50
75
100
# of Mirrors
per Layer
6
12
18
24
30
120
300
450
600
Total Mirrors:
Total CubeSats:
Total Layers:
Total Segments:
Diameter
0.3
0.5
0.7
0.9
1.1
4.1
10.1
15.1
20.1
30,300
30,300
5,050
600
12
CONCEPT - COMPLEX SUBSYSTEMS
Architecture – 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
Primary material:
Polyvinylidene flouride (PVDF)
370μm
http://www.kiss.caltech.edu/study/largestructure/technology.html
13
CONCEPT - COMPLEX SUBSYSTEMS
Architecture – 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
CONCEPT - EVOLUTION
•
•
•
•
•
•
•
Mirror packaging
Mirror wavefront sensors
Flight formation sensors
Adaptive optics systems
Mirror actuators
CubeSat P-POD and dimension growth
Instrumentation (cameras, sensors, etc)
15
CONCLUSIONS
• 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
16
FUTURE QUANTITATIVE STUDY
•
•
•
•
•
•
•
•
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
17
REFERENCES
1.
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-pellegrinobreckinridge.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
18
Thank you for your time!
Jesus Isarraras
[email protected]
19
BACKUP CHARTS
20
CONCEPT - COMPLEX SUBSYSTEMS
Large Space Aperture Architecture Comparison
ALDCST
HST
JWST
Herschel Space
Observatory
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)
Earth-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 IR
Main 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
Type of Mirror
Orbit
21
Preliminary 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:
23
COMPLEX SUBSYSTEMS
Architecture - Structure
Hex-Frame Contains
• ADC
• Comm Link Enhancement
• Layer Stabilization
• Network Communication
24
CONCEPT - COMPLEX SUBSYSTEMS
Architecture – Secondary Mirror & Instruments
10cm
6U CubeSat
Focal Plane
Secondary Mirror Detector
Deployer
Instruments
(Camera, Optical/IR
Sensors, etc)
25
Formation 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
26
27
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Hubble 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.
Hubble 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.