Tethered Picosatellite Project
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Transcript of Tethered Picosatellite Project
OUR DESIGN
ENGR 490 (ME450 / MSE 480 / EECS 498) TEAM 6
B. Della Mora, P. Johnson, Z. Ni, A. Okorom, B. Richer, D. Samuel
Tethered “Pico” SatelliteSECTION INSTRUCTOR
Brian Gilchrist
SPONSOR
MiTEE
Student
Team
VALIDATIONPROJECT DESCRIPTIONThe MiTEE student team is researching
electrodynamic tethers for maintaining the orbit of
small satellites. The goal of our project is to design
both a picosatellite to conduct electrons for the
MiTEE 1 mission and a one-meter long boom
deployment mechanism. The satellite will be used to
gather data about the earth’s magnetic field for future
missions. Our picosatellite and deployment system
will be used in conjunction with the MiTEE team’s 3U
CubeSat and is constrained to a volume of 0.75U.
Our project illustrates a design for the picosatellite
itself and a boom deployment mechanism that will be
used in the MiTEE 1 mission in 2017.
Requirements Engineering Specifications
Meet NASA
standards
• Qualify to NASA GEVS
• CubeSat Design Spec[2].
Complete circuit for
thrust
• Minimize surface resistance
• Potential drop <2%
• Withstand 400V bias
• Boom insulated from
ionosphere
Minimize volume • Picosatellite, boom, and
deployment mechanism fit
within 0.75 U in CubeSat
Minimize mass • Picosatellite mass under
270 grams
• Center of mass within 1 cm
of attachment point
Function in orbit for
6 months
• Power source independent
of CubeSat
• Provide energy for entire
orbit
Data measurement • Tri-axis magnetic field
measurements
Communication • Wireless communication
• Omnidirectional 20-meter
range
Boom Deflection • Boom deflection <5 degrees
from CubeSat axis
Propulsion
provided by
electrodynamic
tether
Goal of MiTEE
project – two
tethered
picosatellites[1]
CubeSat with
deployed
picosatellite
(not to scale)
The stress-strain data allowed us to calculate the minimum storage
radius of the boom and use real material properties in our simulation.
We would like to express our gratitude to the following groups and individuals for their assistance and support with our project:
Prof. Mihaela Banu, Charlie Bradley, Tim Chambers, Wesley Chapkin, Dejiu Fan, Forrest Research Group, Prof. Brian Gilchrist, Prof. Rachel Goldman, Prof. Anthony Grbic, Prof. John Heron,
Aaron Lamoureux, Seungku Lee, Michigan Hybrid Racing, Miniature Tethered Electrodynamic Experiment Team, Zhiyuan “Hugh” Ni, Brendan Patterson, Daniel Shriver, Shtein Research
Group, Sodano Research Group, Student Space Systems Fabrication Laboratory, Prof. Alan Taub, Van Vlack Undergraduate Laboratory, Prof. Pete Washabaugh, and Ziwei Zeng.
Radiation pattern of the antenna
showing directional dependence
of the strength of the radio wave.
Low reflection coefficient around
2.4GHz represents high antenna
efficiency.
Our picosatellite (left) will deploy one meter from the MiTEE CubeSat on our fiberglass boom (right).
Boom
alignment
piece
Mechanism wall
Spool for boom Mechanism container
Boom
attachment
piece
AntennaPads for
electron
collection
Glass-
covered
solar cell
Using Abaqus to run a dynamic model of CubeSat attitude
adjustment, the boom deflection was calculated. We
determined that the deflection of a one-layer fiberglass
boom would be within engineering specifications.
Parameters Value UnitReceiving antenna gain 3.3 dBFSPL -66.25 dBPolarization Loss -3 dBPointing Error -3 dBEmitting Antenna Gain 3.3 dBTransmission Line Losses -2.5 dB3dB Margin -3 dBLink Budget -71 dBSensitivity -101 dBmMaximum RFout 0 dBmSurplus 30 dB
Link Budget for inter-satellite communication.
Communication/Electronics
We developed two designs based on tape
springs. The booms flatten and can be
rolled up in the deployment mechanism for
storage. They will be made of fiberglass
fabric and a thermoplastic polymer.
REFERENCES
[1] “MiTEE.” – Miniature Tether Electrodynamics Experiment. The University of Michigan, n.d. Web. 21
Jan. 2016
[2] Lee, Simon. CubeSat Design Specifications. Tech. San Luis Obispo: California Polytechnic State
University, 2014.
Circuit diagram for the electrical
components - Arduino microcontroller,
HMC5883L magnetometer, and
XBee RF module.
Boom Structure
Solar Cell Configuration
Communication
Power Generation
Energy generation with and without glass covering on solar cells.
Conductive indium-doped tin oxide (ITO) and fluorine-doped tin oxide
(FTO) glass coatings were also examined.
Deployment Mechanism Layout of Picosatellite
Using a MATLAB model to calculate the power and energy generated over the
course of one orbit, we were able to determine the required solar cell area.
Face-to-FaceBack-to-Back
Boom