NSF PACER Program Physics & Aerospace Catalyst Experiences Louisiana State University (LSU) A. M. Espinal Mena, V.González Nadal, J. Díaz Valerio Faculty Advisor: Dr. H. Vo Aerospace Balloon Imaging Testing with Accelerometer (ABITA) Experiments The Interamerican Geospace Research Experiments (TIGRE) Team Scientific Presentation 7/30/2008

Management Plan Team TIGRE member roles:  A. M. Espinal Mena: Electronics design and prototype.  J. Diaz Valerio: Mechanical design and fabrication.  V. Gonzalez Nadal: Software design and implementation. Team TIGRE webpage:

Mission Balloon Dynamics Reference: BEXUS 5 Experiment ( Altitude Sensing and Determination System )

Balloon Flight ACES-08

Balloon Flight ACES-11

Scientific Background Reference: Lyndon State College, Department of Meteorology Height

Scientific Requirement  Record the flight time of payload  Observe the surrounding environment of the balloon  Record outside & inside temperature  Obtain the vector acceleration of the balloon payload

Technical Requirements  Develop a payload weigh < 500 g.  Maximum capital cost of $ 500.  Collect data for 4 hours.  Required to have a RTC on board  Include a three axis accelerometer to record vibration/shock

System Design

Principal of Operation  Data gathered from:  Temperature sensor  Digital video camera  Accelerometer  Altitude – GPS How does the experiment correlate the data?

Electrical Design

Temperature Sensor and camera control

Diode Temperature Sensor

Calibration Diode Temperature Sensor Y = ( ° C)X ° C

Internal Temperature Sensor (HOBO)

ADXL330 Three Axis Accelerometer

Calibration – Accelerometer X Axis Y = ( g)X – 2.860g

Calibration – Accelerometer Y Axis Y = ( g)X – 2.955g

Calibration – Accelerometer Z Axis Y = ( g)X – 2.860g

32480 Digital Video Camera

Digital Video Camera Control System

Power Budget ComponentCurrent (mA) BalloonSat56 3 AD822 OpAmps & 1 LM33428 Three axis accelerometer (ADXL330) 3 Temperature Sensor5 Voltage-to-Frequency Converter 6 Digital Camera160

Mechanical Design

Payload Fabrication

Thermal Test

Thermal Test Results

Vacuum Test

Shock Testing

Weight Budget

Software Design

Software Requirements  Control Instruments  Time Stamp  Temperature Sensor  Accelerometer  Digital Camera  Calibrate Data  Analyze Data  Interpret Data

Data Format and Storage ByteDescription 1Time Stamp: hour 2Time Stamp: minute 3Time Stamp: second 4Temperature 5Accelerometer: X axis Max 6Accelerometer: X axis Min 7Accelerometer: X axis Average 8Accelerometer: Y axis Max 9Accelerometer: Y axis Min 10Accelerometer: Y axis Average 11Accelerometer: Z axis Max 12Accelerometer: Z axis Min 13Accelerometer: Z axis Average

Pre-flight

During flight

Post- Flight  Data acquisition from BalloonSat

Data Analysis Plan  Level 0: Raw Data - Data downloaded from BASIC Stamp and saved using Term 232  Level 1: Calibrated Data - Convert digital values into physical quantity  Level 2: Analysis -Data interpreted using Excel and Graphical Analysis -Frame grabber to analyze video image -Accelerometer’s frequency using Spectrogram

EEPROM Test: Power Outage (Min.)

Vacuum Test

Thermal Test (Hr:Min)

“Spinning” and Shock Test (Hr:Min)

Outside Temperature: Vacuum (Hr:Min)

Outside Temperature: Thermal

Payload Track Pre-Launch

Altitude VS Time

Ascending Rate

Altitude VS Temperature

Temperature VS Time: Inside

Temperature VS Time: Outside

Outside Temperature: Filtered

Accelerometer Average Values

Accelerometer Average Values (LPF)

Analysis: Average Acceleration

Spectogram Data Launch Cut-Down Landing

Video Analysis

Acceleration: Max Values

Max Values: Filtered

Acceleration: Min Values

Min Values: Filtered

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Predicted Location of Payload Recovery

Actual Location of Payload Recovery

Conclusions Successfully gathered data for the entire flight. Recorded the surrounding environment of the payload. Recorded vector acceleration of the payload. Discovered ways to improve further payload development.