AstroX NASA Sub-Orbital Flight for Dust and Micrometeorite Collection

NASA Sub-Orbital Flight for Dust and Micrometeorite Collection

Mission Overview

RockSat-X

• NASA’s 4th _{year of RockSat} program

• First year of RockSat-X

• Allows students access to open space

• Mission experiments open to the imagination

Mission Overview

Scientific Mission

• Primary Experiment:

Collect space dust

• Samples donated to Geology

Museum

• Secondary Experiments: Capture flight data

• Thermal readings • Seismic/Vibration data • Photographs of payload operation Source: http://www.ucar.edu/news/releases/2006/ images/thermosphere-satsm.jpg Thermosphere

Mission Overview

How To Accomplish Mission

• Design an extendable boom

with a dust collector

• Aerogel dust collectors

• Design electronic systems for:

• Control sensors

• Record data

• Actuating boom

• Interfacing with NASA Wallops telemetry

• Placed in a Terrier – Orion

Rocket

Source : http://stardustnext.jpl.nasa.gov

Mission Overview

Design Overview

NASA Design Parameters

Type Quantitative Constraint

Physical Envelope Cylindrical

Diameter: 12 inches Height: 12 inches Weight 30 ± 1 lb_f

Center of Gravity (COG) ± 0.5 in from axial center of RockSat-X plate Power and Telemetry 8x 0-5V 10-bit A/D Lines

1x Asynchronous Line at 15.36 kBd (19.2 kBd nom.) 3x Timer controlled power lines

Design Overview

Pre-Flight

• Cleanroom installation of aerogel

• Evacuate boom interior

• Prevent degassing

• Minimize aerogel contamination

Design Overview – Mechanical Structure

Launch

Launch: o 25 G loadings o 50 G impulses o ̴ 1.3 to 4.8 Hz spin rate o 7 lb_f centrifugal force

o Maximum of 57 lb_f on front face

Stress Strain Displacement 50G 25 G 4.8 Hz Material Choice: o 6061 – T6 Aluminum Alloy Testing: o 3 point bending test o Shaker table test 100 ksi 9.5 x 10 -6 6 x 10-5_in

Design: o Teflon bearings o 2 lb_f friction load o 13 aerogel tablets o 15 inch reach Testing:

o Low thermal loading test o Tape reel test

o Friction test

Apogee:

o ̴ 77 mile elevation o Boom fully extended o -50 °F environment

o Zero gravity environment o ̴ 0.5 Hz spin rate

o 0.75 lb_fcentrifugal force

Retraction:

o Boom fully retracts ̴ 10 sec

o ̴ 3 minute window for collection o ̴ 100-600 particles captured o Begins to free fall

Design Overview – Mechanical Boom

Apogee – Collection Window

Skin Shed:

o 50 mile elevation - Thermosphere o Rotation slows

o Boom deploys ̴ 6 sec

Δ𝐿 = 𝐿α_𝑙Δ𝑇 = 0.006 in Design Overview – Mechanical Seal

Reentry – Splashdown

Reentry:

o 350 °F reentry environment

o ̴ 10 Hz tumbling rate upon descent o 30 lb_f centrifugal force

Chute Deployment:

o Payload returns to ambient conditions o ̴ 4 miles above Earth

Splashdown:

o 40 mph impact

o Boom is sealed water tight o Vacuum aided

o ̴ 15 minutes after launch

Design:

o Tapered seal

o High temperature rubber o Vacuum assisted in last 25

miles

Testing:

o High thermal loading test o Leak test

𝐹_{𝑖𝑚𝑝𝑎𝑐𝑡} = 𝑚𝑑𝑣

Design Overview

Electrical Subsystems

• Processor:

• Arduino Uno (ATmega 328)

• Motor: • Beetle B231 DC Gearmotor • Camera: • OmniVision AA5620 5MP • Accelerometers: • X, Y axes (± 5/18 G) • Z axis (± 5/250 G) • Temperature Sensor • DS18B20 (-67 to 257 °F) • Software

Mission Overview

Benefits and Social Impact

• Benefits

• Future RockSat Participants

• Provide more specific flight parameters

• UW Geology Museum

• Provide research samples

• Provide new display materials

• Expand interplanetary geology exhibit

• Continued space exploration

• Social Impacts

• Earth and space pollutants • Taxpayer dollars

To-Do List

• Full electronic integration

• Finish Astro-X testing

• Wallops compliance testing

• LAUNCH!

Schedule

• June 8 – Launch Readiness Review

• June 10 – Payload Checkouts at Wallops

• June 20-22 – Environmental Testing at Wallops • July 8 – Post Environmental Tag-Up

• July 16-17 – Final Payload Inspections (GO/NO GO) • July 18-19 – Final Payload Integration

• July 21 – Launch! • July 22-23 – Contingency Launch

Budget

Weight Budget

• Allowable Weight (30 ± 1 lb_f) • Mechanical (9 lb_f) • Electrical (3 lb_f) • Camera (0.25 lb_f) • Sensors (0.25 lb_f) • Electrical system (2.5 lb_f) • Total Weight (12 lb_f) • Ballasting (~18 lb_f) Weight Budget

Mechanical Camera Sensors Electrical System Ballasting

Budget

Monetary Budget

• Predicted vs. Actual

Construction Supplies Predicted Costs Actual Costs Difference

Structure $300.00 $130.00 $170.00 Aerogel $300.00 $610.00 $310.00 Sensors $225.00 $250.00 $25.00 Electrical System $200.00 $400.00 $200.00 Other Supplies $260.00 $150.00 $110.00 Sub-Total $1,285.00 $1,540.00 $255.00 Flight $14,000.00 $14,000.00 $0.00 Total $15,285.00 $15,540.00 $255.00

Conclusions

• Improvements

• Composite tape reel

• Gradient density aerogel

• Larger dust collector surface area

• More extension

• Changing design parameters

• More organized assembly

Special Thanks

• CEAS Machine Shop

• Dr. Carl Frick • Dr. Paul Johnson • Mr. Scott Morton • Dr. David Walrath • UW Physics Department • UW Geology Museum

• Wyoming NASA Space Grant Consortium

Classic Silica Aerogel

• Amorphous silicon dioxide (SiO₂)

• Density of ̴ 0.0034 lb_m/in3

• ̴ 96% air

• Open cell structure

• High compressive strength • Dissolves in water

Actuator

• Motor

• Exerts 44 lb_f

• Spool and frame

• Nylon offsets

• Tape reel