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.