A Deimos Impact and Observation Spacecraft This presentation details the initial mission concept proposed for project A.D.I.O.S.

1. Mission Concept
Team 3
FRUITCAKE - Focused Recoil Under ImpacT: Cubesat Analyzing Kinetic Experiment
DIOS MIO - Deimos Impact & Observation Spacecraft: Mars Intercept Orbit
Jeff Anderson, Thomas Blachman, Andrew Fallon, John Franklin, Samuel Gaultney,
David Habashy, Brian Hardie, Brandon Hing, Zujia Huang, Sung Kim, Jonathan Saenger

2. Mission Objectives
Objectives:
- Primary: Analysis of Deimos utilizing a spectrometer during a flyby analysis of a debris cloud created
by an artificial impactor.
- Secondary: Close proximity imaging of one face of Deimos.
Driving Requirements:
- Ability to create big enough plume to be analyzed.
- Ability to analyze plume and relay data back to earth.
- Ability to direct and release impactor off of main systems.
Overview:
Utilizing a 6U cubesat and the Mars 2020 trajectory, we plan to release an impactor into Deimos
to release a large dust plume. This plume will be analysed during a flyby with the spectrometer on board our
cubesat. In addition, our cubesat will take images of Deimos to improve the understanding of it’s geography.
This will also serve as our descope Both of these objectives fit well with the desired science objectives of the
Decadal survey.

3. Mission Success Criteria
Trajectory: Impactor impacts Deimos, Observer flyby successful
- Liftoff - Separation from M2020 rover
- Earth-Mars transfer orbit insertion - Mid-term adjustment burn
- Mars SOI adjustment burn - Final adjustment burn
- Impactor-Observer separation
Spacecraft: Both Impactor and Observer operational
- Post launch check - Mid-term check
- Mars SOI - major systems awaken - ADCS & spectrometer operational
- Imager operational
Systems: Data successfully transmitted
- Plume size enough for analysis - Image resolution and quality
- Antenna operational - Data upload sequence
Descope options:
- In the event that the impactor misses or malfunction the cubesat will take close up pictures of the surface.
- In the event of spectrometer failure images of plume can still provide data about the composition
- In the event of star tracker failure reduncies will be included.

4. OV-1

5. Mission Concept Trade Studies
Concept
weight
Asteroid
Detector
Mars-
Geyser
Surveyor
Mars-Lava
Tube
Surveyor
Deimos-
Lidar
Deimos-
impactor
Phobos-
Lander
Science Value 40% 5 7 8 6 7 7
Novelty 20% 3 5 8 8 8 6
Trajectory feasibility 15% 4 5 4 7 9 6
Hardware feasibility 15% 10 8 3 4 7 3
Risk -10% 3 3 9 5 7 8
Mitigation 10% 6 8 2 5 2 4
TRL 10% 8 8 4 7 8 7
Score 5.8 7.05 5.55 6.35 7.1 5.65

6. Impactor Feasibility and Design.
- Impactor:
- Impact speed: 3.75 km/s max.
- Impactor mass: 4 kg.
- Impact energy: 28.09375 MJ.
- Plume Calculation:
- Scaled to Deep Impact’s data.
- Impacted at 10.7 Km/s, mass of 200kg.
- Ejected 1.2*10^6 kg of material.
- Impact energy: 10,000 MJ.
- Plume Calculation:
- Material ejected: 2551 Kg.
-Lower risk and less complicated than landing.
-1 to 2 U’s in size.
-Contains own propulsion, navigation, and power for
post separation phase of flight.
- Propulsion:
- C-POD micro-cold gas propulsion system.
-Small and lightweight .5 U’s 1.25 kg
- Navigation:
- Star tracker: BCT Standard NST
-Off the shelf
- Vision based navigation: TBD
-Better suited for mission
- Power:
- Solar: 7.5 Watt surface panel
-Can provide power for long d
- 3 mah battery
-Smaller and cheaper
- Cost: TBD

7. Navigation/Trajectories
- Incoming Mars velocity = 1.515 km/s
- Ideal Deimos location (v = 1.35 km/s)
- ΔV < 0.1 km/s
- Worst case Deimos location
- Phase off by 180°
- Speed up
- ΔV = 0.257 km/s
- Slow down

8. Prograde vs Retrograde Trade-off
- Prograde
- Smaller impact velocity
- 1.05 km/s
- Smaller plume (less data)
- More time for flyby analysis
- Retrograde
- Higher impact velocity
- 3.75 km/s

9. Morphological Matrix - Architecture Alternatives
Architecture Decision Option 1 Option 2 Option 3 Option 4
Communication
EWC 27 HDR-TM X
Band Transmitter
MarCO
Spectrometer
Compact Ion and
Neutral Mass
COSIMA Amptek X-123SDD
Propulsion System Chemical Electric Cold Gas Hybrid
Chemical Hydrazine AF-M315E
Attitude Control Reaction Wheels Cold Gas Electrospray
Attitude Determination Star Trackers IMU Sun Sensors
Command & Data Handling iOBC Cube Computer

10. Spectrometer
Amptek X-123SDD
- Cost: $41,600
- Size: 7 x 10 x 2.5 cm
- Power: 2.5 Watts
- Weight: 180 grams
- Communication options through USB, Ethernet, or RS-232
- Data Transmission Rate: 9.6 kb/s (uplink and downlink)
- Current Application: X-ray Fluorescence (XRF)
- System Reliability: Miniature X-Ray Solar Spectrometer mission launched on December 6, 2015.
Compared to Compact Ion and Mass Spectrometer and COSMIA.

11. Propulsion
- Main Propulsion: Aerojet Rocketdyne 2U
MPS-130
- Dry Mass: 2.2 kg, Wet Mass: 3.5 kg
- MRL & TRL: 6
- Chemical Monopropellant: AF-M315E
- Expected Isp of 240 seconds
- 45% more dense than hydrazine
- Available 𝚫V = 367 m/s
- Assuming Spacecraft Payload Mass: 5.5 kg
- 3-axis stabilization
- Sensors
- IMU
- SMG Ellipse-A
- Star trackers
- BCT Thin Slice NST
- Actuators
- Thrusters
- Reaction wheels
- BCT RWP050
- Blue Canyon Technologies XACT ACS
- Contains Star Trackers, Reaction Wheels
- 1-sigma cross-axis pointing error better than
Attitude Determination
& Control

12. Power
- 2 Ukube-1 Single Deployable, Double-
Sided Solar Cells
- 6.5 mm Profile fits to 6U structure
- 40 W Peak Power at Mars, 20.8 W Average Orbit
Power
- Clyde Space XU CubeSat EPS
- Up to 12 Solar Panels
- 98% Efficient at 5V and 3.3V Regulators
- 18650B Lithium Ion Batteries

13. Communication
- Utilize MRO to transmit signal on DSN
- X-Band transmitter, 3 meter high gain antenna
- Need to be able to downlink 10 kb/s
- EWC 27 HDR-TM X-Band Transmitter
- Developed by SyrLinks
- Capable of LEO transmission to Earth DSN dish
- Downlink 5 Gb/s to 3 meter dish
- TRL9, 10W Power Req, 10x10x3cm, 300 g
- MarCO’s X-Band transmitter

14. Thermal Management
Combination of a variety of methods
- Structure
- Thicker structure surrounding payload allows better
heat dispersion.
- Payload set in trays to reduce heat loss/gain to
conduction
- Plastics utilized for insulation, Metals for heat
conduction
- Radiators
- Over electronics that will heat in use to disperse

15. Command and Data Handling
ISIS On Board Computer (iOBC); Flight Heritage since 2014
400 MHz 32-bit ARM9 processor and 3.3V power supply
94g mass with dimensions 96 x 90 x 12.4 mm
Two 8GB high reliability SD cards or two any size standard SD cards
TRL: 6 to 7
iOBC Costs: $4918.76 to $11,011.31 (EM/FM daughter Boards Optional)
Cube Computer
4-48 MHz, 32-bit ARM Cortex-M3-based MCU

16. References
- "Green High Delta V Propulsion for Cubesats." Web. <http://www.rocket.com/files/aerojet/documents/CubeSat/crop-MPS-
130%20data%20sheet-single%20sheet.pdf>
- Spores, Ronald, Robert Masse, Scott Kimbrel, and Mclean Chris. "GPIM AF-M315E Propulsion System." 15 July 2013. Web.
<https://www.rocket.com/files/aerojet/documents/CubeSat/GPIM%20AF-M315E%20Propulsion%20System.pdf>.
- Richardson, J. E., Dr. (2013, February/March). An examination of the Deep Impact collision site on Comet Tempel 1 via Stardust-NExT:
Placing further constraints on cometary surface properties.
<https://www.researchgate.net/publication/256461959_An_examination_of_the_Deep_Impact_collision_site_on_Comet_Tempel_1_via_Star
dust-NExT_Placing_further_constraints_on_cometary_surface_properties>
- http://www.syrlinks.com/en/products/cubesats/hdr-x-band-transmitter.html
- http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2915&context=smallsat
- https://marscubesatworkshop.jpl.nasa.gov/static/files/presentation/Asmar-Matousek/07-MarsCubeWorkshop-MarCO-update.pdf
- http://www.cubesatshop.com/product-category/command-and-data-handling/
- http://bluecanyontech.com/wp-content/uploads/2016/07/RW.pdf
- http://bluecanyontech.com/wp-content/uploads/2016/07/NST.pdf
- http://bluecanyontech.com/wp-content/uploads/2016/08/ADCS_F.pdf
- http://www.nasa.gov/sites/default/files/files/3_Mars_2020_Mission_Concept.pdf
- https://directory.eoportal.org/web/eoportal/satellite-missions/m/minxss#foot7%29
- http://amptek.com/products/x-123sdd-complete-x-ray-spectrometer-with-silicon-drift-detector-sdd/#6
- http://lasp.colorado.edu/home/minxss/