MinnSpec Conceptual Design Review University of Minnesota / Augsburg College Douglas Carlson...
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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
MinnSpec Conceptual Design Review University of Minnesota / Augsburg College Douglas Carlson (Overall Team Lead), Bryce Schaefer (MinnRock II), Chris Woehrle
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
Slide 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
Slide 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.
Slide 4
Experiment We plan on flying three different experiments.
Spectroscopy using atmospheric sampling Spectroscopy of ambient
light Flight characterization
Slide 5
Who Will Benefit MinnSpec will prove the atmospheric
composition at various altitudes. Take the sampled data and compare
to previous flights
Slide 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
Slide 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.
Slide 8
Overall Functional Block Diagram Connection or triggered
readings G Switch Main Power MinnRock IIAugsSpec MinnSpec
Slide 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.
Slide 10
Preliminary Drawings Both spectroscopy experiments for now will
be above MinnRock II
Slide 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.
Slide 12
(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
Slide 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
Slide 14
Gantt Chart
Slide 15
Budget This project will be funded by the Minnesota Space Grant
Consortium Allotted spending approximately $3,000.
Slide 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?
Slide 17
Slide 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
Slide 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
gs)
Slide 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
Slide 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?
Slide 22
AugSpec Functional Block Diagram IMU Spectrometer Magnetometer
Microcontroller Data Logger Connection for triggered readings
Slide 23
Conceptual Design Review
Slide 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 rockets flight,
including: spin rate, 3D acceleration, light intensity, pressure,
and temperature, and the Earths magnetic field as a function of the
rockets 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 Earths magnetic field as a
function of the rockets 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)
Slide 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 years project originally planned on
including a GPS; however due to complications the GPS flew only as
ballast.
Slide 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.
Slide 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
Slide 28
History RockOn! 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.
Slide 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 gs of acceleration Sensors must not cause
electromagnetic interference
Slide 30
Success Criteria Data retrieval Analysis of data Projection of
data onto graphs Structural integrity of canister and boards
Scientific theory tested
Slide 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
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
Slide 35
General Overview of the other Spectroscopy experiment
Slide 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.
