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Nitric Oxide and Piezo Dust Detector Probe

Conceptual Design Review

Virginia TechPresented by Stephen Noel

November 18, 2011

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CoDR Presentation Content

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• Section 1: Mission Overview– Implementation of Piezo Dust Detector and

Nitric Oxide Sensor in High Altitude– Theory and Concepts– Successful Data Collection, Storage, and

Transmission• Section 2: Design Overview

– Design Overview– Functional Block Diagrams– Payload Layout– Shared Deck Space Plan

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CoDR Presentation Contents

• Section 3: Management– Team Organization– Schedule– Budget– Mentors (Faculty, industry)

• Section 4: Conclusions

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Mission Overview

• Utilize Nitric Oxide sensor for NO concentration data collection in high altitudes– IMU data to accompany NO data– Optimal senor orientation– Successful data transmission and storage– Mechanical and thermal securing for reentry

• Successful implementation of Piezo Dust Detector and collection of space dust impact energy readings for Baylor University

– Optimal sensor orientation– Successful data transmission and storage– Mechanical and thermal securing for reentry

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Mission Overview: Theory and Concepts

• Nitric Oxide (NO) sensor– Measure concentration of NO as a

function of altitude– Flight heritage in RockSat-C (NOIME)

• Piezo Dust Detector (PDD)– Collect measurements of velocity and

energy from incoming dust particles– Existing flight heritage on UT satellite

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Mission Overview: Theory and Concepts (PDD)

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Mission Overview: Mission Requirements

• Project requirements– The system shall conform to the requirements set forth

in the 2011 RockSat-X User Guide– System shall meet power transmission requirements to

sensors– System shall transmit data via NASA Wallops telemetry– System should orient NO sensor for optimal data

collection– System shall collect data from PDD sensor– System should mechanically and thermally secure

sensors and integral components for reentry and recovery

• Minimum success criteria– NO data should be consistent with current global models– Shall gain flight heritage for PDD sensor

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crestock.com

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Preliminary ConOps (for Terrier-Orion)t ≈ TBD

Altitude: ~100 km

PDD On

t ≈ 15 min

Splash Down

t ≈ TBD

Altitude: TBD

Skirt Released

-G switch triggered

-NO and IME sensors on

-Begin data collection

t = 0 min

t ≈ 4.0 min

Altitude: 95 km

Engage Reentry Shield

Apogee

t ≈ 2.8 min

Altitude: ≈115 km

End of Orion Burn

t ≈ 0.6 min

Altitude: 52 km

t ≈ 4.5 min

Altitude: 75 km

Reentry

Altitude

t ≈ 5.5 min

Chute Deploys

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Mission Overview: Expected Results

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• Nitric Oxide concentrations in high altitude• Correlating to Dr. Bailey’s preliminary data • Compare to NOIME results• Will get clarification from Dr. Bailey on expected

results

• Energy and velocity readings of dust particles in space• Correlating to Baylor University’s preliminary data• Will get clarification from Baylor University on

expected results

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Design Overview

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• Utilizing NO sensor and IMU from NOIME (RockSat-C flight heritage)– NO sensor collects wavelength data around

220nm– IMU collects acceleration, angular rate, and

magnetic field data

• Collecting space dust velocity and energy with PDD– Little flight heritage

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Data Collection Block Diagram

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Nitric Oxide Sensor

Dust Particle Sensor

Inertial Measurement

Unit

ADC

Onboard Computer

Wallops Data Bus Flash StoragePower

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FBD – Mechanical System (rough diagram)

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Design Overview: RockSat-X 2011 User’s Guide Compliance

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• Mass Estimate– Same instruments as NOIME plus PDD– Will work with UW to keep from exceeding mass constraint

• No expectation of exceeding allotted physical space requirements• No deployables or booms expected• All telemetry lines (asynchronous, parallel, and 10 bit 0-5V A/D) will

have to be shared with UW• Will likely use two power/timer lines

– PDD should be powered on sometime after launch (NO probe has no known constraint)

• Since this payload will share a power and telemetry lines with UW, will work with UW’s constraints to divide utilities efficiently for both projects

• CG requirements – Will restrict the CG to within 1 inch of the center of the deck

• May need to use batteries for extra power– TBD

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Design Overview: Shared Can Logistics

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• Payload area will be shared with UW– The AstroX team strives to test an

electrically active heat shield prototype

• Plan for collaboration– Team leads will stay in contact via email– Solidworks models, mass budgets, power

budgets, etc. will be shared through a drop box account

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Management

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Graduate Advisor:

Robbie Robertson

Faculty Advisor:

Dr. Troy Henderson

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Management - Preliminary Schedule for the Semester

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Management

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• Monetary budget– Most components are being used from

last year’s RockSat-C mission– Free in-house shop time at VT– Other components TBD

• Team mentors– Dr. Kevin Shinpaugh– Dr. Troy Henderson– Dr. Scott Bailey

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• This mission will provide useful data of NO concentration in the upper atmosphere and velocity and energy of dust particles in space– Will also provide flight experience to these two

sensors• Must work closely with UW and work within

their mission constraints since they are further along in the design process

• Way forward– Investigate power and data storage/transmission

needs for all known components and sensors

Conclusion

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Conclusion

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