Team Name

MinnSpecConceptual Design ReviewUniversity of Minnesota / Augsburg CollegeDouglas Carlson (Overall Team Lead), Bryce Schaefer (MinnRock II),Chris Woehrle (AugSpec), Aurther Graff (MinnSpec)James Flaten, David Murr, Ted Higman, William Garrard(faculty advisors)10.14.091MinnSpec 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.AugSpecMinnRock IIMinnSpecObjectiveLearn about spectroscopy and how it worksGet data from two different sources and compareSee the differences between gathering spectroscopy test samplesObtain meaningful data that can be further analyzed and shared with those who are interested.ExperimentWe plan on flying three different experiments.Spectroscopy using atmospheric samplingSpectroscopy of ambient lightFlight characterization

Who Will BenefitMinnSpec will prove the atmospheric composition at various altitudes. Take the sampled data and compare to previous flights Expected Results

Characterize some of the chemical components of the atmosphere as a function of altitudeCharacterize flight from pressure, acceleration, light sensorsMeasure magnetic field of the Earth over the trajectoryAnswer question can we receive GPS signals within this rotating rocket body

6RockSat Payload Canister User Guide Compliance

Mass, VolumeAs 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 InterfaceWe will be using the same interface used in the RockOn! workshop and for RockSat last summer.

7Overall Functional Block DiagramConnection or triggered readingsPowerBasic System requirements:Power for laser 1-2mA @ 3-5 voltsPower 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 1System weight - < 2 lbs.

Power DistributionAll 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.

Preliminary DrawingsBoth spectroscopy experiments for now will be above MinnRock II

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.

11(Preliminary) Schedule 7/31/2009 RockSat Payload Users 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 SelectFlights 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

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

Gantt Chart

BudgetThis project will be funded by the Minnesota Space Grant ConsortiumAllotted spending approximately $3,000.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?

16AugSpecMission OverviewIMU(inertial measurement unit)Real-time characterization of the flight of the rocketBetter sensors for better post-flight characterizationSpectrometerReduce the vibrations and shocks experienced by the spectrometerObtain a spectrum (Absorption vs. Altitude)The ability to trigger spectra readings based off of positionDesignTwo separate systemsIMU, Magnetometer, MicrocontrollerSpectrometer, accelerometerIMU systemReal-time stream of ascii data to loggerSpectroscopy systemAccelerometer: measure the reduction of vibrations and jerksSpectrometer: absorption density (Absorption vs. Altitude)Fiber optic cableShoftride shock absorber systemSpectrometer can handle up to ~6 g's rms (dynamic) for 10 min with no ill effects (not yet known if it can handle 20 gs)HardwareIMU: two optionsAtomic IMU 6 Degrees of Freedom - XBee ReadyDimensions: 1.85 x 1.45 x 0.975 inches (47 x 37 x 25 mm)Input voltage: 3.4V to 10V DCCurrent consumption: 24mA (75mA with X-bee)IMU 6DOF Razor - Ultra-Thin IMU (looking into it)Input voltage: 2.7-3.6VDCLow power consumptionMagnetometer MicroMag 3-Axis Magnetometer500uA @ 3.3V DCSpectrometerRed Tide SpectrometerDimensions (in mm): 89.1 x 63.3 x 34.4. Mass: 190 gAccelerometer Triple Axis Accelerometer Breakout - ADXL335Dimensions: 0.7x0.71.8 and 3.6VDC

Hardware ContinuedMicrocontroller Arduino Pro Mini 168 - 3.3V/8MHzDimensions: 0.7x1.3" (18x33 mm)Less than 2 gramsData Logger Logomatic v2 Serial SD DataloggerDimensions: 1.5x2.480 mA (worst case)Shock Absorber ideasSoftride flexible metalFoam/gel (if allowed)LiPoly batteries1000 mAh?

AugSpec Functional Block DiagramIMUSpectrometerMagnetometerMicrocontrollerData LoggerConnection for triggered readingsMinnRock IIConceptual Design ReviewObjectiveThe 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 rockets flight, including: spin rate, 3D acceleration, light intensity, pressure, and temperature, and the Earths magnetic field as a function of the rockets altitudeSpin rate with a single light sensor3D acceleration (x, y, z) as a function of timeThe inner pressure and temperature within the canisterThe Earths magnetic field as a function of the rockets altitudeThe trajectory of the rocket using a GPS

Other objectivesCapture still pictures while in flight using a camera (possibly with use of a mirror system)GPSWe 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 years project originally planned on including a GPS; however due to complications the GPS flew only as ballast. CameraPrevious 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.Other sensorsThe 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 conditionsThe GPS and camera have experimental purposes, we want to get a better idea of the conditions under which either device can function HistoryRockOn! 2008 Characterization of the rockets 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 rockets flight. Boards captured 3D acceleration data, spin rate, temperature, pressure, and the Earths magnetic field. The camera and GPS employed by the board did not successfully capture data.

Requirements for overall payloadWeight: < 10 lbsCenter 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 requirementAll sensors must withstand 20 gs of accelerationSensors must not cause electromagnetic interference

Success CriteriaData retrievalAnalysis of dataProjection of data onto graphsStructural integrity of canister and boardsScientific theory testedBenefitsMinnRock II will characterize many aspects of the rockets flight, allowing a multi-faceted view of the rocket during the flightDetermine the effectiveness of a GPS and a camera on the rocketComparing the data with previous data from other flights and NASAs own predicted dataEquipment (tentative)Accelerometers: Analog Devices AD22279-A-R2 (ADXL78)Magnetometers: Honeywell HMC1053Light sensors: Microsemi LX1972IBC-TRCamera: Canon Powershot A570 ISTemperature: National Semiconductor LM50CIM3GPS: SiGe GN3S Sampler v2Pressure: Honeywell ASDX030A24R

Functional Block DiagramComputerMain Power G-switchMemoryCameraGPSConclusionHaving performed a similar experiment in the past, our group knows what it takes to get things doneWe have more EE and CSCI people on the team this year, which means more help with the boards and codeWe have familiarity with the deadlines and scope of the projectMinnSpecGeneral Overview of the other Spectroscopy experiment 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 onewe 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.