DemoSat IV Critical Design Review Metropolitan State College of Denver April 21, 2006

Three missions in two payloads FieldSat and SolarSat will be in one payload. VideoSat will be in another.

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

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

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

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

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

Field/SolarSat System Interfaces

FieldSat Subsystem Overview FieldSat subsystem contains an inertial measurement unit Three gyroscopes to measure rotation Accelerometers to measure linear acceleration Altimeter

FieldSat Subsystem Schematic IMU AccelerometersGyroscopes Altimeter Microcontroller

FieldSat Subsystem Interface Inputs: Kinematic motion Outputs: Altitude Acceleration in three dimensions Rotation of three axes

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

SolarSat Subsystem Schematic Solar cells Deployment solenoid Solar measurement unit Microcontroller

SolarSat Subsystem Interface Inputs: Deployment signal from microcontroller. Outputs: Lumens, voltage, and current measurements.

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

Field/SolarSat Monetary Budget Gyro Sensors (3)Donated Micro-controller Board$ SD Board (2)$ SD Cards (2)$ Accelerometers (2)Donated Altimeter$ Solar Cells (2)$ Incidentals*$ * includes all necessary hardware Total$

VideoSat Mission Description Sensor Platforms Audio High-Resolution Video Estimated Recording Time: 135min Launch Ascent Descent Landing Recovery

VideoSat Mission Goals Record a large sum of audio/video data for playback Recover data after sub-orbital descent Self-contained unit

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.

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)

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)

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.

VideoSat Unit Subsystem Purpose Record Audio Record Video Store Data Light and Sound Storage (2GB SD flash drive) Lens Microphone Camera Unit

Unit Subsystem Interface Inputs: Light Sound Outputs: Video with sound 10 frames/sec 640 x 480 pixel resolution

VideoSat Insulation Subsystem Purpose Protect from extreme cold of high altitude environment Protect from impact during landing (2GB) Foam Chemical heating packet

VideoSat Structural Subsystem Purpose Firmly attach camera to payload tether Protect from impact during landing (2GB) Mounting Brackets Housing

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

VideoSat Mass Budget Camera unit 38g Secure Digital card 2g Housing300g Insulation100g Chemical heating (3) 20g Structural and Hardware150g Estimated mass610g

VideoSat Monetary Budget Camera unit $ Secure Digital card$ Housing$ Insulation$ Chemical heating (3)$ 5.00 Structural and Hardware$ Total$

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

Any Questions?