Section 1: Mission Overview Mission Statement Mission Objectives Section 2: The Payload! User’s...
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Transcript of Section 1: Mission Overview Mission Statement Mission Objectives Section 2: The Payload! User’s...
Drexel RockSAT Launch Readiness Review
Kelly Collett • Christopher Elko • Danielle JacobsonMay 27, 2012
LRR Presentation Contents• Section 1: Mission Overview
• Mission Statement• Mission Objectives
• Section 2: The Payload!• User’s Guide Compliance• Beta Prototype Testing
• Section 3: Check-In Readiness• Plans for Integration• Documentation
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Mission OverviewDrexel RockSat Team 2011-2012
Mission Statement
Develop and test a system that will use piezoelectric materials to convert
mechanical vibrational energy into electrical energy to trickle charge on-board power
systems.
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Mission Overview• Demonstrate feasibility of power generation
via piezoelectric effect under Terrier-Orion flight conditions
• Determine optimal piezoelectric material for energy conversion in this application
• Classify relationships between orientation of piezoelectric actuators and output voltage
• Data will benefit future RockSAT and CubeSAT missions as a potential source of power
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Payload DesignDrexel RockSat Team 2011-2012
Design Overview
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Microcontroller G-switch
Accelerometer ArrayPiezo Arrays
Camera
Flight Decks
Standoff Supports
Batteries
Payload Design beta
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Beta payload with wiring connections ready for vibration testing
• Beta payload includes modifications to:• Camera housing• Organization of EPS
components on top deck• Transistors and relays
used to control power for EPS and VVS
• Cantilever length: 3.0 in.
Physical Specs eurekasat payload
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Requirement UG Spec Status
Mass 2.42 lb
Volume ½ can H: 4.3”D: 9.3”
Payload CG 1”x1”x1” x0.23” y0.21” z0.43”
Activation Method 1.SYS.2 We think so…
Structure Mounts Top, bottom bulkheads
Sharing Fully Developed? Integration Successful
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PEA ICamera
Rectifier + Capacitor
PEA II
Rectifier + Capacitor
Accelerometer II
Rectifier + Capacitor
Rectifier +Capacitor
PEA III PEA IV
Electrical Design
9V Battery G-Switch Wallops
InternalMemory
3-AA Batteries
SD CardMemory
Accelerometer IArduino
Microcontroller
Power connectionData connection
Legend
Latching Relay
9V BatteryPower (G-switch=1)
Updates Since FMSTR• Beta prototype complete and tested• VVS functioning
• Switched to AA batteries, no regulator• Modified camera mounting bracket
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Testing Updates
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• Increased length of cantilevers• Lowered maximum output• Alpha: over 1 V for “diving board”• Beta: about 0.55 V
Testing Updates
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Mission Requirements
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Primary Objectives Complete?
Power generation via the piezoelectric effect under Terrier-Orion flight conditions Yes
Classify the relationships between the orientation of piezoelectric actuators and output voltage Yes
Ensure system activates upon launch Yes
Data is autonomously recorded to SD card Yes
Secondary Objectives
Visual data recorded to SD card Yes
Data collection systems are self powered Yes
Voltage generated purely from launch vehicle Yes
Accepted for flight with RockSAT-C program Yes
ALMOST, CAPTAIN!ARE YA READY KIDS?!
ReadinessReady!• Travel arrangements set• Payload is assembled and ready to go• Integration with TempleAlmost Ready!• Documentation• For Drexel Payload and Canister
• Check-in Procedure
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Integration
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Canister Sharing with Temple• Method of Integration: standoffs• Height: 9.07”• Combined Weight: 6.74 lb• Combined CG: x-1.32” y2.04” z2.10”• NOTE: material properties discrepancies• CG to be adjusted with systematic ballast
placement• Procedure: tighten standoffs
Complete Payload
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Complete Payload
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Temple
Drexel
øCanister Integration
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9.07”overallheight
9.30”overall
diameter
6.73 lbs.overallweight
standoffs
means of integration
Action Items• Finish up documentation• Mostly drawings• Parts accounting• Tidying of documents
• Ballasting, staking, etc.• To be completed after integration with Temple• Mostly at Wallops
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Check-In Inspections
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• Check-in procedure partially completed• So far so good
Final QuestionsDrexel RockSat Team 2011-2012
Questions• None right now! :D
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Thank you!Questions?