Mars Telecommunication Relay CubeSat Constellation Concept Rohan Deshmukh Swapnil Pujari Advisor: Professor David Spencer
Transcript
1. Rohan Deshmukh Swapnil Pujari Advisor: Professor David
Spencer
2. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work About Us Rohan Deshmukh
Swapnil Pujari School Georgia Institute of Technology Georgia
Institute of Technology Major Aerospace Engineering Aerospace
Engineering Hometown Fairfax, VA Alpharetta, GA Year 3rd Year 3rd
Year 5/17/2015 2
3. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Concept Motivation 5/17/2015 3
Credit: Charles Edwards, JPL
4. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Mars Communication
Architecture 2025 Dedicated Communications Orbiter (1-3 satellites)
5/17/2015 4 Credit: Charles Edwards, JPL
5. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Operational View 5/17/2015
5
6. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Video 5/17/2015 6
7. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work CubeSat Overview 5/17/2015
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8. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Structure/Sizing Deployment
Mechanisms: 1. < 3U CubeSat: PPOD (Poly-Pico Satellite Deployer)
2. > 3U CubeSat: CSD (Canisterized Satellite Dispensers) o CSD
Limitations for 6U: mass of 12 kg, size of 12 cm x 24 cm x 36 cm
35.7 cm 11.8 cm 22.2 cm Stowed CubeSat Configuration CSD Deployer
Mass: 7.9 kg 5/17/2015 8
9. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Solar Flux Inverse Square Law
Earth Solar Flux: 1370 W/m^2 @ 1AU Mars Solar Flux: 589.1 W/m^2 @
1.525 AU Power generation is proportional to the inverse square of
the distance to the sun Inverse Square Law Drives iterative process
of solar array sizing 57% Reduction in Solar Flux Density 5/17/2015
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10. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Power Subsystem Subsystem
Component Name Quantity EPS Clyde Space FLEX EPS 1 CS 30 Whr
Battery 1 CS Deployable Double Sided 6U Panels 4 CS 2UFixed Solar
Panels 1 Clyde Space FLEX EPS Clyde Space 30 Whr Battery CS
Deployable Double Sided 6U Panels: 21 cells per face -> 42 cells
on one panel -> 84 cells one side Solar Cell Efficiency: 28.3%
Area of one solar cell: 0.00275 m2 Total Solar Cell Area: 0.231 m2
CS 2U Body-Mounted Solar Panels 5/17/2015 10
11. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Satellite Communication Bands
UHF X-Band Ka-Band Space Communication Usage Used between landers,
rovers, and orbiters Current Standard in long range communication s
(rovers Earth) Developing Standard Advantages Less prone to
atmospheric interference Long Range Communication Greater Data
Transmission Disadvantages Smaller Distance coverage Requires Line
of Sight, More power Development & Testing Stages, Large
Propagation Losses Common Uses Broadcast TV, Cell Phones Radar,
Deep Space Network Radar, Deep Space Network 5/17/2015 11
12. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Todays Mars Relay Network
Testing Ka-Band 5/17/2015 12 Credit: Charles Edwards, JPL
13. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Tomorrows Mars Relay Network
MAVEN Agency: NASA Launch: Nov 18, 2013 Orbit: 150 x 6,200 km
elliptical 75 deg inclination Non-sun-synchronous Deep Space Link:
- Band X-band - Power Amplifier 100 W TWTA - High Gain Antenna 2 m
HGA (body fixed) Proximity Link: - Transceiver Electra (single
string) - Protocol CCSDS Proximity-1 - Antenna Quadrifilar Helix -
Forward Link - Frequency 435-450 MHz - Data Rate 8, 32, 128 kbps -
Coding (7,) Convolutional - Return Link - Frequency 390-405 MHz -
Data Rate 1, 2, 4, , 2048 kbps - Coding (7,) Convolutional, LDPC -
Other 8-bit I/8-bit Q open loop recording Suppressed Carrier
Modulation Adaptive Data Rates ExoMars/TGO Agency: ESA Launch: Jan
7-27, 2016 Orbit: 400 km circular 74 deg inclination
Non-sun-synchronous Deep Space Link: - Band X-band - Power
Amplifier 65 W TWTA - High Gain Antenna 2.2 m HGA Proximity Link: -
Transceiver Electra (dual string) - Protocol CCSDS Proximity-1 -
Antenna Quadrifilar Helix (2) - Forward Link - Frequency 435-450
MHz - Data Rate 8, 32, 128 kbps - Coding (7,) Convolutional -
Return Link - Frequency 390-405 MHz - Data Rate 1, 2, 4, , 2048
kbps - Coding (7,) Convolutional, LDPC - Other 8-bit I/8-bit Q open
loop recording Suppressed Carrier Modulation Adaptive Data Rates
5/17/2015 13 Credit: Charles Edwards, JPL
21. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Concept Summary An equatorial
constellation of 4 low-cost CubeSats in Mars orbit Augments telecom
relay capability for landed assets and a current/future orbiter
This concept is targeted for the 2020/2022 timeframe, deploying as
a secondary payload on Mars 2020 or a future Mars orbiter 5/17/2015
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22. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Concept Summary Optimized
Mass/Structure to fit CSD Deployer Requirements Sufficient margin
for future iterations of spacecraft development Performed
Telecommunications Link Budget: 1) Cubesat Earth: Ka-Band 2)
Cubesat Ground: UHF 3) Cubesat Orbiter: UHF Optimized to meet power
requirements of spacecraft bus Considered body & shadow shading
effects Analysis based on Sun-Mars-Earth Angle 5/17/2015 22
23. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Future Work Data Volume
Analysis Thermal Analysis Trajectory/Delta-V Analysis Risk
Management Assessment Cost Assessment End of Life Assessment
5/17/2015 23
27. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Solar Cell Shading Analysis
SME Worst Angle (46.6) Max Shading Effects (~6) 5/17/2015 27
28. Motivation/ Background Overview Flight System Technical
Resource Budgets Summary Future Work Future Missions to Mars: 2013
- 2023 J F M A M J J A S O N D J F M A M J J A S O N D J F M A M J
J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F M A
M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D J F
M A M J J A S O N D J F M A M J J A S O N D J F M A M J J A S O N D
Orbiters: ODY MEX MRO MAVEN ExoMars TGO Landers: Opportunity
Curiosity InSight ExoMars 2016 EDM ExoMars 2018 Lander ExoMars 2018
Rover Mars 2020 Rover 202320172016201520142013 20222021202020192018
... ... ... L M 18 Nov 22 Sep ... E E 28 Sep 19 Oct L 4 Mar - 26
Mar L 7 Jan - 27 Jan ... ... 19 Oct L 7 Jan - 27 Jan M ... E 15
Feb- 12 Feb L 26 Jul - 14 Aug E 17 Jan L 5 May - 28 May ... ... ...
... Cruise' Aerobraking' Primary'Science' Phase' Funded'Extended''
Mission'Phase' L' M E' Launch' MOI' EDL' Unfunded'Extended''
Mission'NoBonal'Plan' Legend:' 5/17/2015 28 Credit: Charles
Edwards, JPL