![Possible Mission Names
FRUITCAKE
Focused Recoil Under ImpacT: Cubesat Analyzing Kinetic Experiment
DIOS MIO
Deimos Impact & Observation Spacecraft: Mars Intercept Orbit
IMPACT
Intercepting Moon Plume & Analyzing Composition of Target
GUNTER
verifyinG Unknown compouNds Through dEimos Reconnaissance
DIMAS
Deimos Impactor for Material Analysis Spectrometry
CAMMIPS
Cubesat Analysis of Martian Moons via Infrared Plume Spectrometry
DECIMATE
DEimos Composition IMpactor sATEllite Mission
VADER
Verifying mAterials on DEimos spectRonomy
Verification & Analysis of DEimos oRigins
Volatiles Assay of DEimos Rheology
Verification Assessment of DEimos Rheology
Verification and Assessment of DEimos Resile
Verification and Assessment of DEimos Reliquiae
Verification and Assessment of DEimos Rejectamenta
Verification and Assessment of DEimos Regolith
Verification and Assessment of DEimos Refringency
Verification and Assessment of DEimos Redound
Verification and Assessment of DEimos Rasure
For impactor: OBliterator-1 [a.k.a. OB-1]](https://image.slidesharecdn.com/payloadspresentationadios-170221223402/85/Payloads-Presentation-for-Project-A-D-I-O-S-15-320.jpg)
Payloads Presentation for Project A.D.I.O.S.
- 1. Payloads Team 3 Jeff Anderson, Thomas Blachman, Andrew Fallon, John Franklin, Samuel Gaultney, David Habashy, Brian Hardie, Brandon Hing, Zujia Huang, Sung Kim, Jonathan Saenger DIMAS Deimos Impactor for Material Analysis Spectrometry
- 2. Mission Concept Mission Goal: Direct an impactor into Deimos at high velocities to launch a plume of surface and subsurface debris into space. The plume will be analyzed by a infrared spectrometer to determine the what compounds comprise Deimos. This will determine whether Deimos is a C or D type asteroid, or Mars ejecta. In addition, prebiotic volatile concentration will be analyzed to determine asteroid contributions to early life. Mission Objectives: - Impact Deimos with impactor and release plume. - Analyse spectral absorption patterns of plume to determine compounds of Deimos to determine its origins. - Measure levels of subsurface volatiles to learn about origin of volatile compounds in planets.
- 3. OV-1
- 4. Science Goals - Determine whether Deimos is a captured asteroid or accreted from Mars. - Low absorption in the 1.3µm range denotes asteroid origin. - Carbon, clay, silicate rocks (oxides), c-type are guessed to be 22% water in form of hydrated minerals, anhydrous formations - Determined the amount and type of subsurface volatiles. - High Levels of volatiles indicate outer solar system origin. - Data will shed light on how asteroids seed planets with water and volatile organics.
- 5. Plume Analysis Recap Diameter Ejecta Velocity Depth >1.57 m>5.56 m/s^2 for 5% of ejecta >15 m for loose sand - 5720 kg of material ejected to escape velocity - 50 mins to full plume - 5.5 km high, 4 km wide plume -Plume is possible to utilize according to the planetary protection rules and regulations. - Spectrometer will have an operational time of 10 minutes, up to 160 secs of data retrieval
- 6. Key Requirements for Instrument Selection - Spectrometers - Must have a spectronomy range of 1.0 µm-2.25 µm. - Physical range of greater than 50 km - Size must be less than 2U - Must make measurements in under 80 secs. - Impactor - Must produce large enough plume to fit scanning cone of spectronomer. - Must be able to arrive 50 minutes before spectrometer. - Must not contaminate spectronomy readings, by avoiding materials in the 1.0
- 7. Impactor Trade Studies Time Released Before Impact (hours) ΔV Required (m/s) Weight of Fuel (kg) Approximate Power Required (Wh) Risk (1-10) 24 130 1.2 60 4 48 65 0.7 120 6 72 30 0.43 180 7 Power Source Size (cm) Weight (kg) TRL Solar 38.1 x 31.5 x 10.2 2.35868 9 Battery 7 x 3 x 2 - 7 x 3 x 6 0.032 - 0.096 9
- 8. Impactor: Obliterator-1 (OB-1) Power (Passive) 2.5 Watts Power (Active) 10 Watts Data Volume N/A Size 2U Mass 4 kg - Impactor will be a 2U separable cubesat, with it’s own propulsion, navigation, and power for a 72 hour separation period. - Impactor cannot be made of iron compounds and should reduce using plastics and magnesium. As many components as possible should be made of aluminium and copper. - Impactor will have an independent operational time of 72 hours. - Propulsion: - C-POD micro-cold gas propulsion - Small and lightweight .5 U’s 1.25 kg - Navigation: - Star tracker: BCT Standard NST -Off the shelf - Power: - 180 watt hour battery -Smaller and cheaper
- 9. Instrument ARGUS mini-INMS BIRCHES Mass (g) 230 600 2000 Volume (U) 0.18 1.1 1.5 Power (W) 1.4 1.8 5 Spectrum (nm) 900-2500 0-2000 0-4000 Range (km) 600 675.924 100 Data Rate (Mb/s) 1 0.0013 10 FOV (degrees) 0.15 20 12 Cost ($) 49,500 15,000 200,000 TRL 8/9 6/7 8/9 Mass Spectrometer Trade Studies
- 10. Mass Spectrometer: ARGUS - Passive infrared spectrometer - Operates in 1000 nm to 1700 nm range - Extended range version goes to 2400 nm - Won the Alouette Award - Operates in 230 grams - Aperture: 15 mm - The Dimensions are; - w = 45 mm - l = 50 mm - h = 80 mm - Volume = 180000 mm3 = 0.18 U - Flight heritage: CanX-2 (Canadian Advanced Nanosatellite eXperiment-2) - Integration Time Ranges: 500 microsecond to ~4 seconds - Data transmitted in 100 ms - Can adjust number of scans for co-adding spectra
- 11. Total Payload Resources Summary ARGUS Spectrometer Impactor Total Mass (g) 230 4032 4262 Volume (U) 0.18 2 2.18 Power (W) 1.4 2.5-10 3.9-11.4 Spectrum (nm) 900-2500 N/A Range (km) 600 N/A Data Rate (Mb/s) 1 0 1 FoV (degrees) 0.15 Cost ($) 49,500 TBD TRL 8/9 6/7
- 12. Risk Assessment1. Spectrometer Out of Range a. Ample range incorporated into trade studies. 2. Spectrometer Performance Failure a. High TRL selected 3. Impactor Misses a. ADCS and Propulsion have high TRL 4. Impactor Fails Separation a. Surface Spectrometry 5. Plume Size Failure 4 1 5 3 6, 2 Likelihood Consequence
- 13. Questions?
- 14. Sources Richardson, J. E., Melosh, H. J., Artemeiva, N. A., & Pierazzo, E. (n.d.). Impact Cratering Theory and Modeling for the Deep Impact Mission: From Mission Planning to Data Analysis. Deep Impact Mission: Looking Beneath the Surface of a Cometary Nucleus, 241-267. doi:10.1007/1-4020-4163-2_10 “CanX-2 (Canadian Advanced Nanosatellite eXperiment-2)” Available: https://directory.eoportal.org/web/eoportal/satellite-missions/c-missions/canx-2#references “Argus IR Spectrometer Kit, Space Grade” Available: http://thothx.com/product/argus-1000sk-infrared-spectrometer-kit/. Reuter, D., “BIRCHES: Mars Cubesat Instrument,” Mars Cubesat Workshop Available: https://marscubesatworkshop.jpl.nasa.gov/static/files/presentation/clark-pamela/35-birches.pdf. P. Clark, R. Macdowall, D. Reuter, R. Mauk. A Broadband IR Compact High Resolution Spectrometer (BIRCHES) for a Lunar Water Distribution (LWaDi) Cubesat Mission
- 15. Possible Mission Names FRUITCAKE Focused Recoil Under ImpacT: Cubesat Analyzing Kinetic Experiment DIOS MIO Deimos Impact & Observation Spacecraft: Mars Intercept Orbit IMPACT Intercepting Moon Plume & Analyzing Composition of Target GUNTER verifyinG Unknown compouNds Through dEimos Reconnaissance DIMAS Deimos Impactor for Material Analysis Spectrometry CAMMIPS Cubesat Analysis of Martian Moons via Infrared Plume Spectrometry DECIMATE DEimos Composition IMpactor sATEllite Mission VADER Verifying mAterials on DEimos spectRonomy Verification & Analysis of DEimos oRigins Volatiles Assay of DEimos Rheology Verification Assessment of DEimos Rheology Verification and Assessment of DEimos Resile Verification and Assessment of DEimos Reliquiae Verification and Assessment of DEimos Rejectamenta Verification and Assessment of DEimos Regolith Verification and Assessment of DEimos Refringency Verification and Assessment of DEimos Redound Verification and Assessment of DEimos Rasure For impactor: OBliterator-1 [a.k.a. OB-1]