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,

10/27/20112 Mission Overview

Scientific Mission Overview o Characterize the performance of electrically active heat shielding o Proposed method of reentry: o Electromagnetic Heat Shield 10/27/20113 Presenter: Tal Wammen

Engineering Mission Overview o Develop a standardized probe and deployment system. o Develop a reliable and reusable standard electronic system. 10/27/20114 Presenter: Tal Wammen

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. 10/27/20115 Presenter: Tal Wammen

Theory and Concepts o Research based from several papers regarding preventing radio black out. 10/27/20116 Presenter: Tal Wammen o A strong magnet should repel charged particles. o Particles striking the payload impart energy on the probe causing heat.

Concept of Operations 10/27/20117 Presenter: Tal Wammen t ≈ 0 min Launch End of Terrier Malamute Burn t ≈ 1.7 min Shedding of Skin t ≈ 2.8 min Apogee t ≈ 4.0 min Probe Deployment t ≈ 8.2 min Chute Deploys t ≈ 15 min Splash Down

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. 10/27/20118 Presenter: Tal Wammen

10/27/20119 System Overview

Subsystem Definitions 10/27/ Presenter: Tal Wammen SystemAbbreviationDescription AHHS ElectromagnetEMGenerates a strong magnet force to reduce heat during reentry PowerPOWSupplies power to the electromagnet and various sub systems. SensorsSENSProvides data for temperature and other environment variables. WirelessWRProvides wireless uplink to the rocket for safe data storage. ControlCTRLControls all major functions of the probe. RecoveryRECSlows descent so that radio uplink can be maintained. AirframeAFProvides safe heat resistant housing for all components Payload Wallops PowerWPPower provided by wallops during flight will control our systems. Wallops TelemetryWTTelemetry provided by wallops during flight will allow us to transmit sensor data. SensorsSENSProvide data for temperature as well as other environmental variables. WirelessWRProvides the capability for the probe to transmit data for later recovery. Payload Electrical SystemPESProvides necessary control, refines wallops interfaces, back up wallops interfaces. Onboard PowerPOWProvides additional power as well as backup power after reentry. Ejection SystemESProvides the capability to retain probe safely as well as eject it freely. Wallops DeckWDProvides firm mounting of components.

Subsystem Overview 10/27/ Presenter: Tal Wammen

Subsystem Overview 10/27/ Presenter: Tal Wammen

Critical Interfaces 10/27/ Presenter: Tal Wammen AbbreviationBreif descriptionPossible 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/CTRL The 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/REC The 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. */AHHS All 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/PES The 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. */Payload All systems will need to be firmly mounted to the payload during ascent.This will be accomplished in variouse ways depending on the sub system.

System/Project Level Requirement Verification Plan 10/27/ Presenter: Tal Wammen Requirement Verification Method Description Produce a 1 Tesla Magnetic Field Simulation and 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. AnalysisSolidWorks 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 DemonstrationProbe will be against a spring, secured with a Wallops ribbon which is melted, releasing the probe.

User Guide Compliance 10/27/ Presenter: Tal Wammen TypeQuantitative Constraint Physical EnvelopeCylindrical Diameter: 12 inches Height: 6 inches Weight15 lbf ± 0.5 lbf Center of Gravity (COG)±0.5in from axial center of RockSat-X plate Power and Telemetry10x 0-5V 16-bit A/D Lines 1 parallel line One asynchronous line One redundant power line (28V) 3 non-redundant power lines 1 GSE power line (28V) 1 Ah capacity High VoltageNo high voltage lines required.

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 , 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/ Presenter: Tal Wammen

10/27/ Subsystem Overview

Subsystem: Magnet source o 100 seconds of activation o Must Sit for 5 Days o Must be reliable and safe. o Must perform well. 10/27/201118

Subsystem: Wireless o Must transmit data after reentry. o Critical to success. o Must be able to operate legally. 10/27/201119

Subsystem: Power Supply o 3 Minutes of Power o Must Sit for 5 Days o Large, Quick Draw Needed 10/27/201120

Subsystem: Heat Shielding o Silicone o Inexpensive o Reliable o Durable 10/27/201121

Subsystem: Ejection System o Spring w/Ribbon o Safe o Effective o Simple o Reliable 10/27/201122

Subsystem: Nose Geometry o Nose Assembly o Stable o Create Drag To Reduce Plasma Buildup 10/27/201123

Subsystem: Fin Attachment o Strong o Must survive Reentry o Create Drag to Stabilize Craft o Must Be Inexpensive 10/27/201124

Subsystem: Temperature sensor 25 Thermocouple Pros High temperature range Cons Additional hardware needed to interface with controller Integrated Chip Pros Cheap Easily interfaces with controller Cons Poor temperature range

10/27/ Conceptual Model

11/1/201027

10/27/ Electromagnet Modeling

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. μ is μ o * μ r, where μ o is the permeability of free space (4π E -7 H/m), and μ r is the permeability of soft iron (200). 10/27/201129

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. 11/1/201030

Preliminary Matlab results 11/1/201031

10/27/ Prototyping Design

Subsystem: Risk Matrix/Mitigation 11/1/ Consequence RSK1 RSK3 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.

Prototyping Plan o Electromagnet o Fabricate and Test o Ejection System o Fabricate and Test o Parachute System o Fabricate and Test 10/27/ Presenter: Tal Wammen Prototyping will begin later this month and carry into next semester

10/27/ Project Management Plan

Organizational Chart 10/27/ Presenter: Tal Wammen Project Manager Shawn Carroll Team Leader Tal Wammen Physics Faculty Advisor Dr. Paul Johnson Engineering Faculty Advisor Dr. Rob Erikson Aeroframe/Probe Housing Jonathan Melton Jeffrey Watters Joe Backstrom Andrew Hellquist Eric Robinson Advanced Heat Shield System Michael Stephens Joe Backstrom Jonathan Melton Andrew Hellquist Colin Lucas Alex Antonacci Jeffrey Watters Matthew Lehmitz Eric Robinson Bryan Overcast Payload Ejection System Michael Stephens Marshall Moore Bryan Overcast Alex Antonacci Electrical Power System Michael Stephens Marshall Moore Matthew Lehmitz Colin Lucas

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/ Presenter: Tal Wammen

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/ Presenter: Tal Wammen

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/ Presenter: Tal Wammen

Budget 10/27/ Presenter: Tal Wammen

Work Breakdown Structure 10/27/ 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

10/27/ Conclusions

Questions?