1. MinnSpec Conceptual Design Review University of Minnesota / Augsburg College Douglas Carlson (Overall Team Lead), Bryce Schaefer (MinnRock II), Chris Woehrle (AugSpec), Aurther Graff (MinnSpec) James Flaten, David Murr, Ted Higman, William Garrard(faculty advisors) 10.14.09

2. MinnSpec MinnSpec is composed of three teams, each assigned to a specific experiment suite. This presentation will show a general overview of the payload as a whole, followed by additional detail about each experiment. AugSpec MinnRock II MinnSpec

3. Objective Learn about spectroscopy and how it works Get data from two different sources and compare See the differences between gathering spectroscopy test samples Obtain meaningful data that can be further analyzed and shared with those who are interested.

4. Experiment We plan on flying three different experiments. Spectroscopy using atmospheric sampling Spectroscopy of ambient light Flight characterization

5. Who Will Benefit MinnSpec will prove the atmospheric composition at various altitudes. Take the sampled data and compare to previous flights

6. Expected Results Characterize some of the chemical components of the atmosphere as a function of altitude Characterize flight from pressure, acceleration, light sensors Measure magnetic field of the Earth over the trajectory Answer question can we receive GPS signals within this rotating rocket body

7. RockSat Payload Canister User Guide Compliance – Mass, Volume As of now we plan on using 0.5 of a canister and then we would be allotted approximately 10 lbs of weight. We expect to be below that weight so may have to add ballast. – Payload activation? We will be having a similar activation sequence. We will be using one power source and one activation switch. – Rocket Interface We will be using the same interface used in the RockOn! workshop and for RockSat last summer.

8. Overall Functional Block Diagram Connection or triggered readings G – Switch Main Power MinnRock IIAugsSpec MinnSpec

9. Power Basic System requirements: Power for laser – 1-2mA @ 3-5 volts Power for detectors – 1-2mA @ 3-5 volts Power for A/D, microcontroller, etc – not known at this time but comparable to laser power. System size – approx 2” x 6” x 1” System weight - < 2 lbs. Power Distribution All of the Minnesota teams will use a single power bus designed and constructed by the MinnSpec team. By doing power distribution this way we will only use one set of batteries and a single g-switch for the entire project. The battery stack will run a power supply module that will provide the various voltages required by Minnspec, AugSpec, and MinnRock II. These voltages are all expected to be in the 2-10 volt range. In addition, the power supply module will also supply a neutral current return which will allow us to create a current return path separate from the grounding of each project module – thereby minimizing the possibility of stray currents in the canister.

10. Preliminary Drawings Both spectroscopy experiments for now will be above MinnRock II

11. Shared Can Logistics Plan We will be sharing a canister with the University of Wyoming. The University of Wyoming will be working on a power system intended to draw power from the rotation of the rocket (if NASA will allow it) and assorted devices to support it: accelerometers to track the spin rate of the rocket, a GPS to track its location, and power output sensors (voltmeter, ammeter). We believe that both of us will be using an atmospheric port so we will design a way to share the atmospheric port. We are tentatively planning to use the bottom half of the canister. Currently in talks with Wyoming over design ideas.

12. (Preliminary) Schedule 7/31/2009 RockSat Payload User’s Guide Released 9/9/2009 Submit Intent to Fly Form 9/18/2009 Initial Down Selections Made 10/14/2009 Conceptual Design Review (CoDR) Due 10/16/2009 Conceptual Design Review (CoDR) Teleconference 10/19/2009 Earnest Deposit of $1,000 Due 10/30/2009 Online Progress Report 1 Due 11/4/2009 Preliminary Design Review (PDR) Due 11/6/2009 Preliminary Design Review (PDR) Teleconference 11/25/2009 Critical Design Review (CDR) Due 11/27/2009 Online Progress Report 2 Due 11/27/2009 Critical Design Review (CDR) Teleconference 1/8/2010 Final Down Select—Flights Awarded 1/22/2010 First Installment Due 1/29/2010 Online Progress Report 3 Due 1/30/2010 RockSat Payload Canisters Sent to Dedicated Customers 2/17/2010 Individual Subsystem Testing Reports Due

13. 2/19/2010 Individual Subsystem Testing Reports Teleconference 2/26/2010 Online Progress Report 4 Due 3/24/2010 Payload Subsystem Integration and Testing Report Due 3/26/2010 Payload Subsystem Integration and Testing Report Teleconference 4/9/2010 Final Installment Due 4/9/2010 Weekly Teleconference 1 4/14/2010 First Full Mission Simulation Test Report Due 4/16/2010 Weekly Teleconference 2 (FMSTR) 4/23/2010 Weekly Teleconference 3 4/30/2010 Weekly Teleconference 4 5/7/2010 Weekly Teleconference 5 5/14/2010 Weekly Teleconference 6 5/19/2010 Second Full Mission Simulation Test Report Due 5/21/2010 Weekly Teleconference 7 (FMSTR 2) 5/28/2010 Weekly Teleconference 7 6/2/2010 Launch Readiness Review (LRR) Teleconference 6/4/2010 Weekly Teleconference 8 (LRR) 6/11/2010 Weekly Teleconference 9 6/17/2010 Visual Inspections at Refuge Inn 06-(18-21)-2010 Integration/Vibration at Wallops 6/23/2010 Presenatations to Next Years RockSat 6/24/2010 Launch Day

14. Gantt Chart

15. Budget This project will be funded by the Minnesota Space Grant Consortium Allotted spending approximately $3,000.

16. Conclusions/Questions We need verification that we can have access to both an optical port and atmospheric port. Update on the question to NASA earlier last month. Wavelength transmission profile of the optical port?

18. Mission Overview 1. IMU(inertial measurement unit)  Real-time characterization of the flight of the rocket  Better sensors for better post-flight characterization 2. Spectrometer  Reduce the vibrations and shocks experienced by the spectrometer  Obtain a spectrum (Absorption vs. Altitude)  The ability to trigger spectra readings based off of position

19. Design  Two separate systems IMU, Magnetometer, Microcontroller Spectrometer, accelerometer  IMU system Real-time stream of ascii data to logger  Spectroscopy system Accelerometer: measure the reduction of vibrations and jerks Spectrometer: absorption density (Absorption vs. Altitude) Fiber optic cable “Shoftride” shock absorber system Spectrometer can handle up to ~6 g's rms (dynamic) for 10 min with no ill effects (not yet known if it can handle 20 g’s)

20. Hardware  IMU: two options Atomic IMU 6 Degrees of Freedom - XBee Ready Dimensions: 1.85 x 1.45 x 0.975 inches (47 x 37 x 25 mm) Input voltage: 3.4V to 10V DC Current consumption: 24mA (75mA with X-bee) IMU 6DOF Razor - Ultra-Thin IMU (looking into it) Input voltage: 2.7-3.6VDC Low power consumption  Magnetometer MicroMag 3-Axis Magnetometer 500uA @ 3.3V DC  Spectrometer Red Tide Spectrometer Dimensions (in mm): 89.1 x 63.3 x 34.4. Mass: 190 g  Accelerometer Triple Axis Accelerometer Breakout - ADXL335 Dimensions: 0.7x0.7“ 1.8 and 3.6VDC

21. Hardware Continued  Microcontroller Arduino Pro Mini 168 - 3.3V/8MHz Dimensions: 0.7x1.3" (18x33 mm) Less than 2 grams  Data Logger Logomatic v2 Serial SD Datalogger Dimensions: 1.5x2.4“ 80 mA (worst case)  Shock Absorber ideas “Softride” flexible metal Foam/gel (if allowed)  LiPoly batteries  1000 mAh?

22. AugSpec Functional Block Diagram IMU Spectrometer Magnetometer Microcontroller Data Logger Connection for triggered readings

23. Conceptual Design Review

24. Objective The MinnRock II board is a flight characterization board similar to the board that flew last year, the MinnRock (I) project. We aim to look at many aspects of the rocket’s flight, including: spin rate, 3D acceleration, light intensity, pressure, and temperature, and the Earth’s magnetic field as a function of the rocket’s altitude Spin rate with a single light sensor 3D acceleration (x, y, z) as a function of time The inner pressure and temperature within the canister The Earth’s magnetic field as a function of the rocket’s altitude The trajectory of the rocket using a GPS Other objectives Capture still pictures while in flight using a camera (possibly with use of a mirror system)

25. GPS We wish to look at the possibility of use of a GPS on the rocket under the flight conditions. (speeds greater than mach 1, and a spin rate of 6 Hz). Last year’s project originally planned on including a GPS; however due to complications the GPS flew only as ballast.

26. Camera Previous flights using a camera have experienced difficulties, speculation exists that the cameras used could not successfully extend their lens under the forces present, and have therefore failed to capture more than a few single pictures at a time. We plan to try minimizing the g-forces experienced by the camera by placing it along the axis of the rocket pointing vertically then use a mirror system to look out the window.

27. Other sensors The sensors will continually capture data over the entire flight of the data to provide significant data for subsequent flights, and will give us a good idea of how effective the sensors are under flight conditions The GPS and camera have experimental purposes, we want to get a better idea of the conditions under which either device can function

28. History RockOn! 2008 Characterization of the rocket’s flight. The flight included accelerometers, pressure sensors, temperature sensors, and Geiger counter. The pressure sensors did not have a high enough range to capture data in the pressurized canister. RockOn! 2009 & RockSat 2009 (MinnRock payload) Characterization of the rocket’s flight. Boards captured 3D acceleration data, spin rate, temperature, pressure, and the Earth’s magnetic field. The camera and GPS employed by the board did not successfully capture data.

29. Requirements for overall payload Weight: < 10 lbs Center of gravity within 0.1 x 0.1 x 1 inch (x, y, z) Max height: 6 in. Max diameter: 9.2 in. Compliance with NASAs no-volt requirement All sensors must withstand 20 g’s of acceleration Sensors must not cause electromagnetic interference

30. Success Criteria Data retrieval Analysis of data Projection of data onto graphs Structural integrity of canister and boards Scientific theory tested

31. Benefits MinnRock II will characterize many aspects of the rockets flight, allowing a multi-faceted view of the rocket during the flight Determine the effectiveness of a GPS and a camera on the rocket Comparing the data with previous data from other flights and NASAs own predicted data

32. Equipment (tentative) Accelerometers: Analog Devices AD22279-A-R2 (ADXL78) Magnetometers: Honeywell HMC1053 Light sensors: Microsemi LX1972IBC-TR Camera: Canon Powershot A570 IS Temperature: National Semiconductor LM50CIM3 GPS: SiGe GN3S Sampler v2 Pressure: Honeywell ASDX030A24R

33. Functional Block Diagram Microcontroller Light sensorMagnetometerThermometerAccelerometerPressure sensor Computer Main PowerG-switch Memory CameraGPS

34. Conclusion Having performed a similar experiment in the past, our group knows what it takes to get things done We have more EE and CSCI people on the team this year, which means more help with the boards and code We have familiarity with the deadlines and scope of the project

35. General Overview of the other Spectroscopy experiment

36. MinnSpec The main effort of the MinnSpec team will be a near infrared absorption spectroscopy experiment which will measure absorption of near infrared radiation (wavelengths slightly in excess of 1000 nm) in order to detect the presence of certain gasses. In particular, water vapor has a very strong absorption line near 1100nm and this system should be very effective at detecting the presence of water. Figure of an experiment similar to the one we plan to fly. The basic system will be similar to the commercial system shown above but will not require pumps or dewars. The system will not need a pump since it will simply be connected to the atmosphere outside the rocket via a tube and will be at the same pressure as the pressure near the rocket. Nor will it require a dewar and coolant, as the lasers operating in the near infrared do not require cooling. The MinnSpec system will use the same basic splitter and detector method shown above which enables the system to compare the absorption of a known reference gas to the gas in the sample sell region. The variation on the system we will likely use diverts the reference beam before it passes through the sample cell and obtains its reference in that way.