Mission ConceptTeam 3

FRUITCAKE - Focused Recoil Under ImpacT: Cubesat Analyzing Kinetic ExperimentDIOS 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

Mission ObjectivesObjectives:

- 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.

Mission Success CriteriaTrajectory: 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.

OV-1

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

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.

- Plume size: 2.5 Km^3 at 1 Kg/m^3.

- 10 mins to full plume.

-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 durations.

- 3 mah battery-Smaller and cheaper

- Cost: TBD

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

- ΔV = -0.186 km/s

Assumptions: circular Deimos orbit, incoming velocity is constant, linear path on approach, maneuver at Mars SOI

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

- Bigger plume

- Less time for data-gathering

- Less margin for error in trajectory

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

SpectrometerAmptek 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.

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 V = 367 m/s𝚫- Assuming Spacecraft Payload Mass: 5.5 kg

- Results in 42% V margin over worst case 𝚫scenario

- Cost Savings

- Simplified range operations

- 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

8 arcseconds

Attitude Determination & Control

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

- 12V Battery Bus

- Custom battery protection circuitry

- Total Cost: $250,000

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

- Developed by JPL

- 8 kb/s transmitter directly to DSN, large

- Unproven technology

Thermal ManagementCombination 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 heat to other instruments

- Utilization of the Sun’s thermal energy

Command and Data HandlingISIS 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

2GB MicroSD socket

50-70g with dimensions 90 x 96 x 10 mm

TRL: 6

Cube Computer Costs: $5028.75

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_Stardust-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/- http://atomfizika.elte.hu/muszerek/Amptek/Amptek-Price-List-June14.pdf