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DemoSat IV Critical Design Review Metropolitan State College of Denver April 21, 2006
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Three missions in two payloads FieldSat and SolarSat will be in one payload. VideoSat will be in another.
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Project Organization Evan Spitler Jason Helms Sarah Ryan Devlin Thyne Jason Igo Team Captain David Fifield Matt Hanley Video Sat Field Sat Solar Sat Professor Keith Norwood Faculty Advisor
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Field/SolarSat System Requirements The payload module must weigh less than 1.5kg Record orientation and vibration data and store it on large-capacity media using Inertial Measurement Unit (IMU) Deploy a solar panel and measure its efficiency before and after impact
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Field/SolarSat Mission Descriptions FieldSat To record on-board orientation and vibration during flight SolarSat To deploy a solar panel and measure the efficiency before and after impact
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Mission Goals and NASA Benefit FieldSat To develop and integrate new attitude and orientation designs SolarSat To test the efficiency of the deployed solar panels Assess damage to deployed solar panels after impact
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Field/SolarSat System Overview The central component of this package is a microcontroller The Field and Solar subsystems communicate with the microcontroller Raw data from the subsystems will be recorded on flash memory for later analysis
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Field/SolarSat System Interfaces
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FieldSat Subsystem Overview FieldSat subsystem contains an inertial measurement unit Three gyroscopes to measure rotation Accelerometers to measure linear acceleration Altimeter
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FieldSat Subsystem Schematic IMU AccelerometersGyroscopes Altimeter Microcontroller
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FieldSat Subsystem Interface Inputs: Kinematic motion Outputs: Altitude Acceleration in three dimensions Rotation of three axes
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SolarSat Subsystem Overview SolarSat subsystem contains the solar cells, deployment latch, and solar measurement unit (SMU) Solar cells will be thin-film variety and will collect a broad range of light wavelengths SMU measures lumens, voltage and current Deployment latch will be a solenoid
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SolarSat Subsystem Schematic Solar cells Deployment solenoid Solar measurement unit Microcontroller
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SolarSat Subsystem Interface Inputs: Deployment signal from microcontroller. Outputs: Lumens, voltage, and current measurements.
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Field/SolarSat Mass Budget Sensors 20 g Micro-controller board < 100 g Secure Digital board (2) < 50 g Secure Digital card (2) 2 g Battery/other power source 100 g Heating, insulation 100 g Waterproofing, etc. 150 g Case 300 g Solar Cells 450 g Estimated mass 1254 g
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Field/SolarSat Monetary Budget Gyro Sensors (3)Donated Micro-controller Board$ 33.00 SD Board (2)$ 36.00 SD Cards (2)$ 28.00 Accelerometers (2)Donated Altimeter$150.00 Solar Cells (2)$ 150.00 Incidentals*$ 300.00 * includes all necessary hardware Total$ 750.00
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VideoSat Mission Description Sensor Platforms Audio High-Resolution Video Estimated Recording Time: 135min Launch Ascent Descent Landing Recovery
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VideoSat Mission Goals Record a large sum of audio/video data for playback Recover data after sub-orbital descent Self-contained unit
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VideoSat NASA Benefit Visually survey landing sites before committing to them Remotely scout for natural resources Bodies of gas Mineral deposits Additional sensors can be added for expanded mission depth Thermal-Band Infrared RADAR Et al.
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VideoSat System Requirements Component: Camera unit Battery (onboard) Audio microphone (onboard) Flash Drive (2GB installed) Thermal Protection Chemical heat pack (hand warmer) Impact Protection Foam Mounting Hardware (material to be determined) (hardware to be determined)
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Camera Mounting Brackets VideoSat System Overview Camera Unit Microphone Battery (3.7v Li ion) Storage (2GB SD flash drive) Lens Tether Interface Member Foam Insulation (2GB) Chemical heating packet (not to scale)
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VideoSat Subsystems Overview Unit Subsystem Contains the Camera, audio recorder, battery and storage device Insulation Subsystem Protection from impact and extreme cold Structural Subsystem Mounts unit and insulation subsystems to the tether.
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VideoSat Unit Subsystem Purpose Record Audio Record Video Store Data Light and Sound Storage (2GB SD flash drive) Lens Microphone Camera Unit
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Unit Subsystem Interface Inputs: Light Sound Outputs: Video with sound 10 frames/sec 640 x 480 pixel resolution
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VideoSat Insulation Subsystem Purpose Protect from extreme cold of high altitude environment Protect from impact during landing (2GB) Foam Chemical heating packet
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VideoSat Structural Subsystem Purpose Firmly attach camera to payload tether Protect from impact during landing (2GB) Mounting Brackets Housing
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VideoSat System Interface Most subsystem interfaces are mechanical in nature An externalized switch will be mounted on the housing Insulating Foam Activation Switch Camera Unit Wire
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VideoSat Mass Budget Camera unit 38g Secure Digital card 2g Housing300g Insulation100g Chemical heating (3) 20g Structural and Hardware150g Estimated mass610g
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VideoSat Monetary Budget Camera unit $ 150.00 Secure Digital card$ 100.00 Housing$ 30.00 Insulation$ 15.00 Chemical heating (3)$ 5.00 Structural and Hardware$ 100.00 Total$ 400.00
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Schedule Pre- CDR February Establish Team March Research and Development April Design and Cost Analysis Post-CDR May Finalize design and initial Prototyping June Acquisition of required materials July Construct and test August Launch and Compile Data
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Any Questions?
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