Harding Flying Bison RockSat-C 2012 Rocket Team Preliminary Design Review

1. Harding Flying Bison RockSat-C 2012 Rocket TeamPreliminary Design Review Harding University Bonnie Enix, Joshua Griffith, Will Waldron, Edmond Wilson, David Stair 22 October 2011

2. Mission Overview

3. Mission Overview – Mission Statement Design, build, test and fly a spectrometer that will measure transmission spectra of gases in Earth’s atmosphere at lower altitudes and the Sun’s irradiance at higher altitudes Tabulate and interpret spectra and create a technical report summarizing the results obtained and conclusions reached

4. Mission Overview – Concepts Percent of atmosphere below rocket as a function of time

5. Mission Overview – Concepts With the spectrometer located inside the Earth’s atmosphere, the Sun’s light can be used as the optical light source in obtaining transmission spectra of Earth’s atmosphere I0 I Computer with Data Storage Spectrometer Atmospheric Gases Sun

6. Mission Overview – Concepts Once above Earth’s atmosphere, the spectrum of the Sun’s surface can be measured without interference. I0 Computer with Data Storage Spectrometer Sun

7. Mission Overview – Concepts oxygen water Spectrum of Earth’s atmosphere at 297 ft. measured with flight spectrometer. Water and oxygen peaks are clearly visible.

8. Mission Overview – Theory Transmittance of light through a sample obeys the Beer-Lambert Law I(ν) I0(ν) Sample I0(ν) Intensity of radiation incident on the sample Intensity of radiation of frequency, I(ν) , after passing through the sample Absorption Cross Section at frequency, N Number of absorbing molecules per volume L Sample path length

9. Mission Overview – Timeline Altitude t ≈ 1.7 min Altitude: 95 km Event B Occurs t ≈ 4.0 min Altitude: 95 km Event C Occurs t ≈ 1.3 min Altitude: 75 km Event A Occurs Apogee t ≈ 2.8 min Altitude: ≈115 km t ≈ 4.5 min Altitude: 75 km Event D Occurs End of Orion Burn t ≈ 0.6 min Altitude: 52 km t ≈ 5.5 min Chute Deploys When G-switch activates payload, spectra will be measured at a frequency of 0.5 Hz for 6 minutes producing 720 spectra -G switch triggered -All systems on -Begin data collection t = 0 min t ≈ 15 min Splash Down

10. Mission Overview – Expected Results G-Switch will function properly to turn on electronics Batteries will be sufficient to power the payload for 20 minutes Instrument will perform well and 100 useable spectra will be recorded, 50 in the atmosphere and 50 above the atmosphere Concentrations of water vapor and oxygen will be measured as a function of altitude Ozone will be measured at higher altitudes Other pollutant gases may be detected

11. Mission Overview –Mission Significance This mission will advance technology, collect science data and develop operations capabilities by: Integration of science instruments with mobile platforms Advance autonomous exploration and data retrieval using self-contained mobile science systems

12. Overview – Benefits from Mission Success We are designing a suite of instruments to be deployed on the surface of Mars to measure the presence of biogases that might indicate life on that planet. The high altitude spectra obtained by our RockSat-C instrument will be similar in some ways to those expected on Mars in terms of gas density, pressure and temperature. The robustness and space mission readiness of our instruments will be verified by their excellent condition after going through the launch process at NASA Wallops Flight Facility including the rigorous pre-flight tests, launch and recovery.

13. System Overview

14. System Overview – Description of Payload The Harding University RockSat-C 2012 science payload consists of a spectrometer for repeatedly measuring the spectrum of the atmosphere recorded through the optical port of a NASA sounding rocket launched from Wallops Flight Facility eastward over the Atlantic. The apogee of the rocket trajectory is at an altitude of 115 km. There is an additional sensor that measures the total Solar irradiance as a function of altitude. An attitude and direction sensor is used to attempt to record the direction at which the spectrometer is pointed for each spectrum measured

15. System Overview – Subsystem Definitions Power Distribution – Power will be from a bank of five 9 volt batteries G-Switch – TBD Spectrometer – StellarNet EPP 2000 UVN-SR Total Irradiance Sensor – OSI Optoelectronics UDT-455UV Attitude and Direction Sensor -- YEI 3-Space Sensor Microprocessor – TERN Model EL Microprocessor with CF Memory

16. System Overview – Spectrometer Internal view of StellarNet EPP 2000 UVN-SR showing light path

17. Mission Overview – Spectrometer Spectrometer mounted on canister plate. Fixture to hold spectrometer lens and total irradiance sensor shown attached at front of plate, just left of center.

18. System Overview – Location of Components Location of the two mounting plates, spectrometer, light collecting lenses of spectrometer and total irradiance sensor.

19. System Overview –Functional Block Diagram Power Distribution System Battery Power Supply G-Switch RBF Signal Conditioner for CCD Array UV/VIS Spectrometer Lens Fiber Optic Cable Embedded Controller with 2 GB Memory Signal Conditioner for Photodiode PD Black lines – power Blue lines -- signal

20. System Overview – Power Distribution Power Distribution System Battery Power Supply G-Switch RBF Embedded Controller Signal Conditioner for CCD Array Signal Conditioner for Photodiode UV/VIS Spectrometer Functional block diagram of power distribution system.

21. System Overview – Spectrum Capture Vout Signal Conditioner for CCD Array UV/VIS Spectrometer VGG Fiber Optic Cable Vsignal out Vsignal in φCLK φROG Embedded Controller with 2 GB Flash Memory ADC 0 CLK 1 CLK 2 Functional block diagram of spectrometer interfaced to embedded controller.

22. System Overview – Spectrum Capture фROG фCLK Vout Two clock signals are required for the CCD array to read out data at Vout

23. System Overview – Irradiance Measure Embedded Controller with 2 GB Memory Signal Conditioner for Photodiode PD A photodiode, sensitive to ultraviolet and visible light, is used to measure the total irradiance of the Sun as a function of altitude.

24. System Overview – User Guide Compliance

25. System Overview – Critical Interfaces

26. System Overview – RockSat-C 2012 User’s Guide Compliance The mass of our entire payload will be less than half the total allowable mass of 20.0 lb which includes the canister mass. The center of gravity is yet to be established We are using DC circuits with a maximum voltage requirement of 20 VDC and 300 mA We require 1 optical port

27. System Overview – Sharing Logistics Who will you be sharing a canister with ? We will be sharing our canister with Frostburg State University. We don’t know yet what their project is. Plan for collaboration -- How do you communicate? We sent them a preliminary plan by email and they haven’t responded. How will you share designs (solidworks, any actual fit checks before next June)? We will send our SolidWorks drawings to them and communicate with them via email and phone. Structural interface – will you be joining with standoffs or something else (again, be wary of clearance)? We don’t know what our sharing arrangements will be. grandpmr.com

28. System Overview – EPS: Risk Matrix

29. Prototyping Plan

30. Prototyping Plan Risk/Concern Action Concern about over saturating the detector or not enough light Take spectra under various amounts of Sunlight to find range EPP 2000 UVN-SR Not sure of how to use attitude and direction finder as it applies to rocket trajectory Use the sensor in order to understand how it functions YEI 3-SPACE Concern that G-Switch circuit will drain batteries prematurely Design and test a more robust G-Switch curcuit G-Switch Program microcontroller to test its ability to carry out its assignment. The functionality of the microcontoller board needs to be verified before CDR TERN EL

31. Project Management Plan

32. Bonnie Enix Software & Testing • Joshua Griffith Software & Testing • Will Waldron Hardware & Electronics Project Management – Organizational Chart • David Stair Technician & Graphic Artist • Edmond Wilson Mentor & Logistics

33. Project Management – Schedule • What are the major milestones for your project? • (i.e. when will things be prototyped?) • CDR • When will you begin procuring hardware? • Think all the way to the end of the project! • Rough integration and testing schedule in the spring • Etc, etc, etc • Format: • Gant charts • Excel spreadsheet • Simple list • Whatever works for you! Don’t let the schedule sneak up on you!

34. Project Management – Budget

35. Conclusion – Main Action Items Parcel out CDR template and begin creating CDR Begin software development that will lead to operation of spectrometer, irradiance and attitude and direction sensors Create primary canister plate and mount spectrometer to it Learn to use Attitude and Direction Sensor Seek additional funding from aerospace industries in Arkansas Begin process of applying for an Arkansas NASA Workforce Development undergraduate Fellowship for each of the three student participants

36. THE END! THANK YOU COSGC & WFF!