Self-Steering Antennas for CubeSat...
Transcript of Self-Steering Antennas for CubeSat...
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CubeSat Developers Workshop CalPoly - San Luis Obispo
March 9, 2004
Self-Steering Antennas for CubeSat Networks
Blaine Murakami and Wayne ShiromaUniversity of Hawaii
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Outline
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Overview of the UH Small-Satellite Program
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Motivation for Self-Steering Antennas
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UH’s Self-Steering Antenna Concept
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UH’s Mission in the University Nanosat-3 Program
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Overview of Bus Subsystems
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Overview of UH Small-Satellite Program
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UH’s first student-satellite project•
Mission: Experimental verification of in-house thermal modeling code•
Launch Date: Fall 2004•
Sponsors: –
Hawaii Space Grant Consortium–
Northrop Grumman Space Technology–
Boeing–
UH College of Engineering
Phase I (2001-2004): Mea Huaka’i I (Voyager)
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Mahalo: Jordi Puig-Suari, Roland Coelho, and Simon Lee
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Overview of UH Small-Satellite Program
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University Nanosat 3 Program (AFRL, AFOSR, NASA, AIAA)–
One of 13 participating universities –
UH is the only university developing CubeSat-class satellites–
Partnership with CalPoly
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Mission: Develop self-steering antenna technology for CubeSat Networks
Phase II (2003-2005): Mea Huaka’i II -
Hokulua (Twin Stars)
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Dual civilian/military small-satellite and UAV deployment from Pacific Missile Range Facility
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Launch services for small-satellite developers around the world
Overview of UH Small-Satellite Program
HiCADRE: Hawaii Center for Aerospace Deployment, Research, and Education
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Payload development for earth and space sciences•
Distributed web-based education
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Outline
•
Overview of the UH Small-Satellite Program
•
Motivation for Self-Steering Antennas
•
UH’s Self-Steering Antenna Concept
•
UH’s Mission in the University Nanosat-3 Program
•
Overview of Bus Subsystems
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Small-Satellite Networks
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Reduced life cycle cost–
Mass produced identical satellites–
Reduced launch costs•
Better performance–
Unlimited effective aperture sizes–
Multimission capability•
Improved reliability–
Graceful degradation–
Reconfigurable to minimize effects of failure
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Inherent adaptability–
New elements added to accommodate changes in requirements
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Future technology advances integratedCourtesy of TechSat 21 webpage
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Omnidirectional Crosslinks
Satellite 1
Satellite 2
Spy
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Self-Steering Crosslinks
Satellite 1
SpySatellite 2
Proposed Solution:Self-steering antennas that maintain a secure crosslink as satellites move about in the network
Secure link can be maintained without a priori knowledge of satellite locations
Self-tracking link
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Retrodirective Techniques
Corner Reflector Van Atta Array
Incoming Signal
Outgoing Signal
fRF = fIF
IncomingOutgoing
-3 -2 -1 0
-3-20 -1
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Local Oscillator fLO = 2fRF
fRF = f
Incoming RF
-3 -2 -1 0
Retrodirective Techniques
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Incoming wave–
From unknown direction–
Induce phase difference •
Phase conjugation–
Heterodyne mixers–
LO fed in phase–
fLO
= 2 fRF–
IF = phase conjugated RF•
Outgoing wave–
In direction of source
IF
Outgoing IF
+3 +2 +1 0
Heterodyne Method
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Outline
•
Overview of the UH Small-Satellite Program
•
Motivation for Self-Steering Antennas
•
UH’s Self-Steering Antenna Concept
•
UH’s
Mission in the University Nanosat-3 Program
•
Overview of Bus Subsystems
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UH Retrodirective Antenna Array
Local Oscillator fLO = 0.5f RF
Photos not to scale
Two-dimensional steeringCircularly polarized
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Retro Bi-static at 0 Degrees
-40
-30
-20
-10
0
-60 -40 -20 0 20 40 60
Theta (Degrees)
dBm
(Nor
mal
ized
)
-60° 60°
Source Horn
Receiver Horn
0°
Bistatic Radiation Cross Section Set Up
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Bistatic Radar Cross Section
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Outline
•
Overview of the UH Small-Satellite Program
•
Motivation for Self-Steering Antennas
•
UH’s
Self-Steering Antenna Concept
•
UH’s Mission in the University Nanosat-3 Program
•
Overview of Bus Subsystems
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Deployment Sequence
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Launch Vehicle Interface
~36 cm
15 cm
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CalPoly P-POD
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Well-established standardized interface
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Tested and qualified to NASA worst case vibration and thermal-vacuum environments
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Door deployer
will be triggered by deployment switch or launch vehicle
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Launch Vehicle Interface
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Deployment Sequence
QuickTime™ and a YUV420 codec decompressor are needed to see this picture.
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University Nanosat-3 Mission Timeline
P-POD ejected from ICU
P-POD door released
ICU Lightband
Integration
P-POD Sat 1 Sat 2
P-POD within ICU
Satellites deploy from P-POD
Tether is deployed
Tether is fully deployed
Interface plate
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University Nanosat-3 Mission Timeline
Sat 1 Sat 2
After battery is 80% charged and 1 hour has elapsed monopole antennas deploy
Satellites alternate beacon to Earth, autonomous operation
Upon receipt of ground signal receive command/downlink data
Begin antenna experiment: Self-Steering Mode
Switch antenna modes:
Fixed-Beam Mode
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Structures Subsystem
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T6 Aluminum Housing
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Exploded View
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Power Generation and Distribution
1MΩ
StructuralGround
CircuitGround
+ 8
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Frequency (HAM)
430–450 MHz
RF output
0.5 Watts (Low Mode)
Communications Systems - Kenwood TH-D7A
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RCM3400 Technical Specs
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29.4 MHz internal clock•
+3 to +3.45 V DC supply voltage @ 97mA
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Programmable in C (using Dynamic C)•
512K FLASH memory
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512K SRAM• 12-bit A-to-D Converter
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•
Operations–
HAM certified operators –
Antenna and equipment a top University of Hawaii –
Holmes Hall–
NOVA tracking software•
Hardware–
Yagi Antenna–
Yaesu Antenna Rotator/Controller–
LNA–
Yaesu FT-847 Transceiver–
PaComm
PicoPacket TNC–
Linux/PC Computer•
Software–
NOVA software tracks satellite/steers antenna via rotator/rotator controller (COM port serial interface)
–
Custom signal verification/handshaking protocol
–
Command/data GUI in development
Ground Station
Yaesu FT-847 Transceiver
435 MHz Antenna
435 MHz LNA
145 MHz Antenna
145 MHz LNA
Polarity Switcher
Polarity Switcher
TNC
Linux Based GS Software
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Conclusion
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UH will continue to be a strong contributor to and supporter of the CubeSat
community
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Demonstration of the first self-steering crosslinks
for picosatellite
communications
•
Thanks again to CalPoly