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 IgoTeam Captain

David Fifield

Matt Hanley

Video Sat Field Sat Solar Sat

Professor Keith NorwoodFaculty 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

Accelerometers Gyroscopes 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 $ 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

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 UnitWire

VideoSat Mass Budget

Camera unit 38g   Secure Digital card 2g        Housing 300g         Insulation 100g         Chemical heating  (3) 20g Structural and Hardware 150g

        

Estimated mass 610g

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

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?