NSF PACER ProgramPhysics & Aerospace Catalyst ExperiencesLouisiana State University (LSU)

A. M. Espinal Mena, V.González Nadal, J. Díaz ValerioFaculty 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: www.pjarea.com/wiki

Mission Balloon Dynamics

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

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

Data gathered from:Temperature sensorDigital video cameraAccelerometerAltitude – GPS

How does the experiment correlate the data?

Electrical Design

Temperature Sensor and camera control

Diode Temperature Sensor

Calibration Diode Temperature Sensor

Y = (-0.04579° C)X +38.68° C

Internal Temperature Sensor (HOBO)

ADXL330 Three Axis Accelerometer

ADXL330 Three Axis Accelerometer

Calibration – Accelerometer X Axis

Y = (0.02282g)X – 2.860g

Calibration – Accelerometer Y Axis

Y = (0.02291g)X – 2.955g

Calibration – Accelerometer Z Axis

Y = (0.02282g)X – 2.860g

Digital Video Camera Control System

Power BudgetComponent Current (mA)

BalloonSat 56

3 AD822 OpAmps & 1 LM334 28

Three axis accelerometer (ADXL330)

3

Temperature Sensor 5

Voltage-to-Frequency Converter

6

Digital Camera 160

Mechanical Design

Payload Fabrication

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 StorageByte Description

1 Time Stamp: hour

2 Time Stamp: minute

3 Time Stamp: second

4 Temperature

5 Accelerometer: X axis Max

6 Accelerometer: X axis Min

7 Accelerometer: X axis Average

8 Accelerometer: Y axis Max

9 Accelerometer: Y axis Min

10 Accelerometer: Y axis Average

11 Accelerometer: Z axis Max

12 Accelerometer: Z axis Min

13 Accelerometer: 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

ConclusionsSuccessfully 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.