Preliminary Design Review Michael Stephens, Eric Robinson, Alex Antonacci, Andrew Hellquist, Joe Backstrom, Bryan Overcast, Jeffrey Watters, Jonathan Melton, Marshall Moore, Matthew Lehmitz, Tal Wammen, Colin Lucas October 27, 2011 1
Preliminary Design Review Michael Stephens, Eric Robinson, Alex Antonacci, Andrew Hellquist, Joe Backstrom, Bryan Overcast, Jeffrey Watters, Jonathan Melton,
Dec 19, 2015
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1
Preliminary Design Review
Michael Stephens, Eric Robinson, Alex Antonacci, Andrew Hellquist, Joe Backstrom, Bryan Overcast, Jeffrey Watters, Jonathan Melton, Marshall Moore, Matthew Lehmitz, Tal Wammen, Colin Lucas
October 27, 2011
210/27/2011
Mission Overview
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Scientific Mission Overview
o Characterize the performance of electrically active heat shielding
oProposed method of reentry: o Electromagnetic Heat Shield
10/27/2011 Presenter: Tal Wammen
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Engineering Mission Overview
o Develop a standardized probe and deployment system.
o Develop a reliable and reusable standard electronic system.
10/27/2011 Presenter: Tal Wammen
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Theory and Concepts
o To design and build a standardized probe deployment system to test an advanced, electrically shielded reentry system.
o These concepts, as well as a standardized delivery mechanism, will provide a foundation to build future experiments.
10/27/2011 Presenter: Tal Wammen
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Theory and Concepts
o Research based from several papers regarding preventing radio black out.
10/27/2011 Presenter: Tal Wammen
o A strong magnet should repel charged particles.
o Particles striking the payload impart energy on the probe causing heat.
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Concept of Operations
10/27/2011 Presenter: Tal Wammen
t ≈ 0 minLaunch
End of Terrier Malamute Burn
t ≈ 1.7 minShedding of Skin t ≈ 2.8 min
Apogee
t ≈ 4.0 minProbe Deployment
t ≈ 8.2 minChute Deploys t ≈ 15 min
Splash Down
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Success Criteria
o Reduce heat on reentry of a probe.
o Confirm results with control.
o Create a standardized probe deployment platform enabling future progression in the field.
10/27/2011 Presenter: Tal Wammen
910/27/2011
System Overview
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Subsystem Definitions
10/27/2011 Presenter: Tal Wammen
System Abbreviation Description
AHHS
Electromagnet EM Generates a strong magnet force to reduce heat during reentry
Power POW Supplies power to the electromagnet and various sub systems.
Sensors SENS Provides data for temperature and other environment variables.
Wireless WR Provides wireless uplink to the rocket for safe data storage.Control CTRL Controls all major functions of the probe.
Recovery REC Slows descent so that radio uplink can be maintained.
Airframe AF Provides safe heat resistant housing for all components
Payload
Wallops Power WP Power provided by wallops during flight will control our systems.
Wallops Telemetry WT Telemetry provided by wallops during flight will allow us to transmit sensor data.
Sensors SENS Provide data for temperature as well as other environmental variables.
Wireless WR Provides the capability for the probe to transmit data for later recovery.
Payload Electrical System PES Provides necessary control, refines wallops interfaces, back up wallops interfaces.
Onboard Power POW Provides additional power as well as backup power after reentry.
Ejection System ES Provides the capability to retain probe safely as well as eject it freely.Wallops Deck WD Provides firm mounting of components.
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Subsystem Overview
10/27/2011 Presenter: Tal Wammen
Air F
r am
e
Mag
net
Pow
er
Reco
very
Cont
rol
Sens
ors
Wire
l ess
CTRL/POW
WR/CTRL
CTRL/REC
SENS/CTRLMN/POW
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Subsystem Overview
10/27/2011 Presenter: Tal Wammen
Nasa Deck
Ejection System
Wallops Power Wallops Telem
Onboard Power
PES
Wireless
WR/PESSENS/PES
POW/PES
WT/PES
ES/PES
WP/PES
Sensors
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Critical Interfaces
10/27/2011 Presenter: Tal Wammen
Abbreviation Breif description Possible solution
AHHS
MN/POW
The magnet will have to have a direct high capacity route to the battery if an electromagnet is used. High current wires at the same guage of the battery will need to be used.
CTRL/POW
The control sytem will need to not only supply but also control the power system to boot the probe up and shut it down. Power mosfets may be able to couple these systems together safely.
SENS/CTRLThe control system will need to be able to read data from the sensors. This can be accomplished with either an ADC system or digital bus.
WR/CTRL
The wireless system will need to carry data from the ctrl system to the rocket base station. This will be done typically via a UART port.
CTRL/RECThe control system will need to be activated at the proper time.
Power mosfets or relays could activate the control surfaces to release the power chute.
*/AHHSAll sub systems within the probe will need to be mounted securely and safely.
The probe body will need mounting holes at various places to keep electronics mounted firmly.
AHHS/Payload
The AHHS prove will need to be mounted to the payload firmly during ascent and allow the probe to be ejected safely and reliably.
Several options are being reviewed. One possible solution is a nylon cover over the probes that is released by burning attachments with nicrome wire.
Payload
WP/PES
Power provided through wallops will need to be routed to the PES system for safe distribution. Poly fuses and mosfets will be used to manage the power supply from wallops.
SENS/PESThe PES system will need to get data from the sensor subsystem. This can be accomplished with either an ADC system or digital bus.
ES/PES
The ejection system will need to get control signals from the PES at the right time to release the probe.
This can be accomplshed with power mostfets or relays to activate the release mechanism.
WR/PES
The wireless system will need to receive signals from the probes and relay the data back to wallops. This will be done typically via a UART port.
POW/PES
The backup power system will need to be connected to the PES to supply power in the event of a power failure. This will be done with standard battery connectors.
WT/PES
The wallops telemetry system will need to communicate with the PES to transmit data from the probes and onboard sensors. This will be accomplished via the telemetry connector.
*/PayloadAll systems will need to be firmly mounted to the payload during ascent. This will be accomplished in variouse ways depending on the sub system.
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System/Project LevelRequirement Verification Plan
10/27/2011 Presenter: Tal Wammen
Requirement Verification Method
Description
Produce a 1 Tesla Magnetic Field
Simulationand
Testing
Use an iron core with copper windings to produce an electromagnet. A Gauss meter to measure the magnetic field.
The payload structure will survive 50G forces with minimal deflections during launch.
Analysis SolidWorks will be used to subject our payload structure to a 50G uniform acceleration to measure deflections.
Probe Should Eject From the Payload Safely and Cleanly
Demonstration Probe will be against a spring, secured with a Wallops ribbon which is melted, releasing the probe.
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User Guide Compliance
10/27/2011 Presenter: Tal Wammen
Type Quantitative Constraint
Physical Envelope CylindricalDiameter: 12 inchesHeight: 6 inches
Weight 15 lbf ± 0.5 lbf
Center of Gravity (COG) ±0.5in from axial center of RockSat-X plate
Power and Telemetry 10x 0-5V 16-bit A/D Lines1 parallel lineOne asynchronous lineOne redundant power line (28V)3 non-redundant power lines1 GSE power line (28V)1 Ah capacity
High Voltage No high voltage lines required.
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Sharing Logistics
o Who are we sharing with?o University of Northern Colorado
o The possibility of a communication system between the AstroX payload and the UNC payload is being considered.
o Plan for collaboration?o Email, phone, road-trips to Greeley and Boulder
o Communication with UNC on a weekly basis.
o Grant UNC access to the AstroX private website.
10/27/2011 Presenter: Tal Wammen
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Subsystem Overview
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Subsystem: Magnet source
o 100 seconds of activation
o Must Sit for 5 Days
o Must be reliable and safe.
o Must perform well.
10/27/2011
Score Performance Safety Reliabiltiy WeightWeighting factor 10 10 10 5Commercial electromagnet 250 2 8 10 10Rare earth magnet 290 10 5 10 8Custom designed electromagnet 260 10 8 5 6
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Subsystem: Wireless
o Must transmit data after reentry.
o Critical to success.
o Must be able to operate legally.
10/27/2011
Score Communication Range Reliablility Logistical ease AccessWeighting factor 10 10 5 5Pair of 900 Mhz Xbee 205 3 10 5 10STX2 transmitter 215 10 7 7 2Digi M10 255 10 7 7 10Spot communicator 220 10 7 5 5APPRS Packet radio 175 5 8 5 4
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Subsystem: Power Supply
o 3 Minutes of Power
o Must Sit for 5 Days
o Large, Quick Draw Needed
10/27/2011
Score Cost Safety Draw rate Weight Feasabiltiy ComplexityWeighting factor 5 10 8 5 10 7Super capacitor 295 8 8 1 7 9 6Batteries 218 3 6 5 5 5 4
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Subsystem: Heat Shielding
o Siliconeo Inexpensive
o Reliable
o Durable
10/27/2011
Score Safety Cost Durability Reliability Feasibility ComplexityWeighting Factor 3 8 9 9 9 8Thermal Soak 176 9 1 4 8 1 3Ablative 217 8 2 8 7 2 3Silicone 311 6 7 6 6 9 6
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Subsystem: Ejection System
o Spring w/Ribbono Safe
o Effective
o Simple
o Reliable
10/27/2011
Score Safety Cost Strength Reliability Weight Feasibility ComplexityWeighting Factor 3 8 9 9 8 9 8Scissor Lift 377 7 8 5 7 7 8 7Linear Actuator 317 8 3 7 8 6 6 4Spring w/ Ribbon 385 9 6 7 8 8 7 6
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Subsystem: Nose Geometry
o Nose Assemblyo Stable
o Create Drag To Reduce Plasma Buildup
10/27/2011
Score Cost Stabilization Drag Weight Feasibility ComplexityWeighting Factor 2 10 10 5 8 8Flat 196 3 9 1 2 9 1Conical 207 5 2 8 5 4 5Rounded 163 5 4 4 5 3 3
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Subsystem: Fin Attachment
o Strongo Must survive Reentry
o Create Drag to Stabilize Craft
o Must Be Inexpensive
10/27/2011
Score Cost Stabilization Strength Weight Feasibility ComplexityWeighting Factor 2 10 10 5 8 8Fin Can 202 5 5 3 8.00 4 5Mounted 240 3 5 8 8.00 6 2Machined 204 9 5 1 6 9 3Drag Tail 267 7 3 6 7 7 9
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Subsystem: Temperature sensor
ThermocouplePros• High temperature rangeCons• Additional hardware needed to
interface with controller
Integrated Chip Pros
• Cheap
• Easily interfaces with controller
Cons
• Poor temperature range
Score Range Precision Feasability CostWeighting factor 10 8 5 5Thermocouple 213 10 6 10 3Semiconductor 209 5 8 10 9
2610/27/2011
Conceptual Model
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Electromagnet Modeling
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Electromagnetic Equations
o Ampere’s Law:
Simplified to: Where B is the magnetic flux vector.
N is the number of turns.
L is the length, and I is the current.
is μ μo * μr, where μo is the permeability of free space (4πE-7 H/m), and μr is the permeability of soft iron (200).
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Electromagnet Matlab Code
o Equations implemented in matlab.
o Takes variety of parameters including: diameter, length, wire gauge and internal battery resistance.
o Another script loops through available parameters building potential electro magnets.
11/1/2010
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Preliminary Matlab results
11/1/2010
1 14 27 40 53 66 79 92 1051181311441571701831962092222352482612742873003133263393523653783914044174304434564690
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weightteslacoilcurrent
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Prototyping Design
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Subsystem: Risk Matrix/Mitigation
11/1/2010
Consequence
RSK1RSK3 RSK2
RSK5
RSK4
Possibility
o RSK1: Probe fails to be released.
o RSK2: Radio signal not acquired before splash down.
o RSK3: Probe fails during reentry.
o RSK4: Fins shear during reentry.
o RSK5: Recovery system fails.
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Prototyping Plan
o Electromagneto Fabricate and Test
o Ejection Systemo Fabricate and Test
o Parachute Systemo Fabricate and Test
10/27/2011 Presenter: Tal Wammen
Prototyping will begin later this month and carry into next semester
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Project Management Plan
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Organizational Chart
10/27/2011 Presenter: Tal Wammen
Project ManagerShawn Carroll
Team LeaderTal Wammen
Physics Faculty AdvisorDr. Paul Johnson
Engineering Faculty AdvisorDr. Rob Erikson
Aeroframe/Probe HousingJonathan MeltonJeffrey WattersJoe Backstrom
Andrew HellquistEric Robinson
Advanced Heat Shield SystemMichael Stephens Joe Backstrom
Jonathan Melton Andrew HellquistColin Lucas Alex Antonacci
Jeffrey Watters Matthew LehmitzEric Robinson Bryan Overcast
Payload Ejection SystemMichael StephensMarshall MooreBryan OvercastAlex Antonacci
Electrical Power SystemMichael StephensMarshall Moore
Matthew LehmitzColin Lucas
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Mechanical Schedule
o Major Mechanical Milestones:o Design Freeze at CDR (11/29/2011)
o Blueprints submitted for manufacturing by CDR
o Mechanical prototype constructed mid-January, 2012
o Mechanical prototype fully tested by end of January, 2012
o Impact and submersion testing
o Electromagnet Testing
o Plasma Testing
o Structural Testing
o Drop Testing
10/27/2011 Presenter: Tal Wammen
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Electrical Schedule
o Major Electrical Milestones:o Electrical Schematics completed by CDR (11/29/2011)
o Components ordered by end of November
o Electrical assembly and testing starting this month
o Control function test
o Telemetry and SD card output test
o Fully functioning payload by early next semester
10/27/2011 Presenter: Tal Wammen
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Budget
o Mass Budget (14 lbs)o Structure (4lb)
o Probe Housing (1lb)
o NASA Structure (3lb)
o Probe (6.5lb)
o Electromagnet (5lb)
o Aeroshell(1lb)
o Parachute(0.5lb)
o Ejection System (0.5lb)
o Electrical System (2lb)
o Battery(1lb)
10/27/2011 Presenter: Tal Wammen
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Budget
10/27/2011 Presenter: Tal Wammen
Device Price Qty TotalXbee 54.95 1 54.95 http://www.sparkfun.com/products/9099Antenna 9.95 1 9.95 http://www.sparkfun.com/products/5587.2 V NiMH Battery 19.99 1 19.99 http://www3.towerhobbies.com/cgi-bin/WTI0001P?I=LXXUP0&P=8Thermocouple 10 2 20 http://www.adafruit.com/products/270Amplifier 10 2 20 http://www.sparkfun.com/products/307SD card holder 2 1 2Power mosfets 4 1 4Arduino MegaNichrome wire 17.32 1 17.32 http://www.amazon.com/Nickel-Chromium-0-0320-Diameter-Length/dp/B000FMUF3A/ref=sr_1_1?ie=UTF8&qid=1318867750&sr=8-1PC boards 33 1 33
Xbee 54.95 1 54.95 http://www.sparkfun.com/products/9099Antenna 9.95 1 9.95 http://www.sparkfun.com/products/5587.2 V NiMH Battery 19.99 2 39.98 http://www3.towerhobbies.com/cgi-bin/WTI0001P?I=LXXUP0&P=8Thermo couple 10 2 20 http://www.adafruit.com/products/270Amplifier 10 2 20 http://www.sparkfun.com/products/3079V 2 2 4 WalmartIron core 15 1 15Copper wire 138 1 138PC boards 33 1 33Rare earth magnet 417 1 417
Total 933.09
AHHS
Payl
oad
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Work Breakdown Structure
10/27/2011 Presenter: Tal Wammen
Advanced Heat Shield System
Payload Ejection System (PES)Aeroframe/Probe Housing
• Finalize Schematics• Design Freeze at CDR• Order Parts by End of Fall Semester• Build Circuits• Test Systems
• Finalize Design• Design Freeze at CDR• Order Parts by End of Fall Semester• Build Prototype• Test prototype
• Finalize Design• Design Freeze at CDR• Submit Work Request• Test Prototype
4210/27/2011
Conclusions
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Questions?
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