RockSat-C 2012 PDR Harding Flying Bison RockSat-C 2012 Rocket Team Preliminary Design Review Harding University Bonnie Enix, Joshua Griffith, Will Waldron, Edmond Wilson, David Stair 22 October

RockSat-C 2012 PDR Mission Overview 2

RockSat-C 2012 PDR Mission Overview – Mission Statement 3 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

RockSat-C 2012 PDR Mission Overview – Concepts Percent of atmosphere below rocket as a function of time

RockSat-C 2012 PDR 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 5 SunAtmospheric GasesSpectrometer Computer with Data Storage I0I0 I

RockSat-C 2012 PDR Mission Overview – Concepts Once above Earth’s atmosphere, the spectrum of the Sun’s surface can be measured without interference. 6 SunSpectrometer Computer with Data Storage I0I0

RockSat-C 2012 PDR Mission Overview – Concepts 7 Spectrum of Earth’s atmosphere at 297 ft. measured with flight spectrometer. Water and oxygen peaks are clearly visible. oxygen water

RockSat-C 2012 PDR Mission Overview – Theory 8 Intensity of radiation of frequency, Intensity of radiation incident on the sample, after passing through the sample Absorption Cross Section at frequency, N L Transmittance of light through a sample obeys the Beer-Lambert Law Sample path length Number of absorbing molecules per volume Sample I (ν)I (ν) I0(ν)I0(ν) I (ν)I (ν) I0(ν)I0(ν)

RockSat-C 2012 PDR Mission Overview – Timeline t ≈ 1.3 min Altitude: 75 km Event A Occurs t ≈ 15 min Splash Down t ≈ 1.7 min Altitude: 95 km Event B Occurs -G switch triggered -All systems on -Begin data collection t = 0 min t ≈ 4.0 min Altitude: 95 km Event C Occurs 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 Event D Occurs Altitude 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

RockSat-C 2012 PDR Mission Overview – Expected Results 10 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

RockSat-C 2012 PDR Mission Overview – Mission Significance 11 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

RockSat-C 2012 PDR Overview – Benefits from Mission Success 12 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.

RockSat-C 2012 PDR System Overview 13

RockSat-C 2012 PDR System Overview – Description of Payload 14 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

RockSat-C 2012 PDR System Overview – Subsystem Definitions 15 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

RockSat-C 2012 PDR System Overview – Spectrometer 16 Internal view of StellarNet EPP 2000 UVN-SR showing light path

RockSat-C 2012 PDR Mission Overview – Spectrometer 17 Spectrometer mounted on canister plate. Fixture to hold spectrometer lens and total irradiance sensor shown attached at front of plate, just left of center.

RockSat-C 2012 PDR System Overview – Location of Components 18 Location of the two mounting plates, spectrometer, light collecting lenses of spectrometer and total irradiance sensor.

RockSat-C 2012 PDR System Overview – Functional Block Diagram 19 Lens UV/VIS Spectrometer Signal Conditioner for CCD Array Embedded Controller with 2 GB Memory PD Signal Conditioner for Photodiode G-Switch Power Distribution System Battery Power Supply RBF Fiber Optic Cable Black lines – power Blue lines -- signal

RockSat-C 2012 PDR System Overview – Power Distribution 20 Embedded Controller Embedded Controller G-Switch Power Distribution System Battery Power Supply RBF Signal Conditioner for CCD Array Signal Conditioner for CCD Array UV/VIS Spectrometer Signal Conditioner for Photodiode Signal Conditioner for Photodiode Functional block diagram of power distribution system.

RockSat-C 2012 PDR System Overview – Spectrum Capture 21 Embedded Controller with 2 GB Flash Memory Embedded Controller with 2 GB Flash Memory Fiber Optic Cable ADC 0CLK 1CLK 2 φCLKφROG V out V GG UV/VIS Spectrometer Signal Conditioner for CCD Array V signal in V signal out Functional block diagram of spectrometer interfaced to embedded controller.

RockSat-C 2012 PDR System Overview – Spectrum Capture 22 Two clock signals are required for the CCD array to read out data at V out фROG фCLK V out

RockSat-C 2012 PDR System Overview – Irradiance Measure 23 Embedded Controller with 2 GB Memory Embedded Controller with 2 GB Memory PD Signal Conditioner for Photodiode A photodiode, sensitive to ultraviolet and visible light, is used to measure the total irradiance of the Sun as a function of altitude.

RockSat-C 2012 PDR System Overview – User Guide Compliance 24 RequirementPayload RequirementStatus Mass allotment:your allotmentTBD Volume allotment: your allotmentTBD The payload’s center of gravity (CG): In 1”X1”X1” envelope of centroid (or in area designated for sharing teams? TBD Activation met under requirement: (either 1.SYS.1 or 1.SYS.2) 1.SYS.2Not Yet Structure mounts:Top and bottom bulkheads. No mounts to sides of cans. Yes Sharing:Fully developed?No

RockSat-C 2012 PDR System Overview – Critical Interfaces 25 Interface NameBrief DescriptionPotential Solution Power Distribution Board (PDB) The electrical power system boards will need to mount to the RockSat-C deck to fix them rigidly to the payload canister. The connection should be sufficient to survive 20Gs in the thrust axis and 10 Gs in the lateral axes. Buckling is a key failure mode. Heritage shows that stainless steel or aluminum stand-offs work well. Sizes and numbers required will be determined by CDR. Spectrometer (UVN-SR) The spectrometer must be fixed rigidly to the main canister chassis plate. The connection should be sufficient to survive 20Gs in the thrust axis and 10 Gs in the lateral axes. Use of four Screws should be enough to achieve the desired robustness Embedded Controller (TERN-EL) The TERN Model EL Embedded Controller must be rigidly connected to our RockSat-c secondary chassis plate. The controller has pre-drilled clearance holes for 4-40 screws. The circuit board is made so that these holes are grounded Secure plastic standoffs will have to be used to mount the embedded controller. Otherwise, there will be a direct electrical connection between the canister and the controller which is unacceptable. Attitude and Direction Sensor (YEI 3-Space) TBD G-Switch The G-switch will be mounted to an L-bracket that is attached to the chassis plate with 8-32 screws.. The connecting wires will be soldered to the G-switch and to the PDB

RockSat-C 2012 PDR System Overview – RockSat-C 2012 User’s Guide Compliance 26 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

RockSat-C 2012 PDR System Overview – Sharing Logistics 27 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 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 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

RockSat-C 2012 PDR System Overview – EPS: Risk Matrix 28 Consequence Entire mission failsPartial Mission failure Little to no data collected Once above clouds, measurements will be successful G-Switch doesn’t activate electronics Batteries drain before end of flight Microcontroller has malfunction Sunlight too low due to cloud cover Possibility

RockSat-C 2012 PDR Prototyping Plan 29

RockSat-C 2012 PDR Prototyping Plan 30 Concern about over saturating the detector or not enough light EPP 2000 UVN-SR YEI 3- SPACE G-Switch TERN EL Not sure of how to use attitude and direction finder as it applies to rocket trajectory Concern that G-Switch circuit will drain batteries prematurely The functionality of the microcontoller board needs to be verified before CDR Take spectra under various amounts of Sunlight to find range Use the sensor in order to understand how it functions Design and test a more robust G-Switch curcuit Risk/ConcernAction Program microcontroller to test its ability to carry out its assignment.

RockSat-C 2012 PDR Project Management Plan 31

RockSat-C 2012 PDR Project Management – Organizational Chart 32 Bonnie Enix Software & Testing Joshua Griffith Software & Testing Will Waldron Hardware & Electronics Edmond Wilson Mentor & Logistics David Stair Technician & Graphic Artist

RockSat-C 2012 PDR Project Management – Schedule 33 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!

RockSat-C 2012 PDR Project Management – Budget 34 ItemAmountTotal Canister & Fees7000 Travel & lodging for launch week1800/person7200 Student Fellowship 8 weeks at 40 hr/wk 4000/student12000 Materials & Components1500 Total$27,700

RockSat-C 2012 PDR 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 Conclusion – Main Action Items 35

RockSat-C 2012 PDR THE END! 36 THANK YOU COSGC & WFF!