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Louisiana State University (LSU)NSF PACER ProgramPhysics & Aerospace Catalyst Experiences
A. M. Espinal Mena, V.Gónzalez Nadal, J. Díaz ValerioFaculty Advisor: Dr. H. Vo
Aerospace Balloon Imaging Testing with Accelerometer (ABITA) Experiments
The Interamerican Geospace Research Experiments (TIGRE) Team
Preliminary Design Review (PDR)
6/30/2008
Outline
Goals, Objectives & Requirements Payload Design Payload Development Plan Payload Construction Plan Project Management Master Schedule Risk Management and Contingency
Mission
To determine balloon dynamics.
Reference: BEXUS 5 Experiment (Altitude Sensing and Determination System)
Scientific Objectives
Obtain images of the surrounding environment Create a model of the balloon movements Determine rotational & translational movement
Technical Objectives
Develop a payload less or equal to 500 g Have a maximum cost of $ 500 Collect data for about 4 hours balloon flight
Science Background
Reference: Lyndon State College, Department of Meteorology
Scientific Requirements
Record the flight time of payload
Observe the surrounding environment of the balloon
Record outside temperature
Obtain the vector acceleration of the balloon payload
Know the rate of tilt change and its relationship with the acceleration
Technical Requirements
Require to have a real time clock on board Include video camera capable of recording 4 hours Include a three axis accelerometer to record
vibration/shock Compare data at high rates Record tilt of payload
Electrical Design
ADXL330 Three Axis Accelerometer
Digital Video Camera
1N4001 Diode Temperature Sensor
Control Electronics
Power Supply
Power Budget
Component Current (mA)
BalloonSat ~56
3 Buffers ~3 (1 each)
Three axis accelerometer (ADXL330)
~0.32
Temperature Sensor (Diode) ~1
Voltage to Frequency Converter
~ 5 (1.67 each)
Total Current ~64.32
Power Budget
Estimated Requirement : 257.28 mA-hour
The 9V battery will supply: 750 mA-hour at -20 C Note: The camera has its on power supply & also its own
memory
Mechanical Design
General Design
The “Giammanco” Model?Foam core construction.Component placement and its importance.Mechanical design and construction.
External Structure
Front, Cross Section and Bottom View of Model
Multi-View Enclosure Model
Internal Structure
Multi-View Internal Model
Front, Cross Section and Hidden Lines View of Model
New Design
Advantages:Components are placed in modular spaces.Physically smaller than original design.Structurally stronger.Ease of access to components.
Redesigned Enclosure
The above picture depicts the payloads enclosure, insert and lid.
Multi-View of External Design
Redesigned Enclosure
Multi-View of Assembled Model
Picture above depicts assembled enclosure, open and sectioned views.
So why a new design?
New Design
Disadvantages:Still in the drawing board.Design might be heavier than original.Complexity of construction.
Assembly and Disassembly
Weight budget
Component: Weight:
BalloonSat Board 67g
Video Camera 42.3g
Accelerometer ~19g
Temperature Sensor ~2g
Conditioning Circuitry ~30g
Camera Power Supply 48.6g
Electronics Power Supply 46.6g
Payload Enclosure ~150g
Cables and Connectors ~40g
Total: ~447.5g
Payload Development
Phases are required to build our payload:• Electronics design.• Software design and testing.• Mechanical design and construction.• Assembly, testing and modification to the payload.
Payload Fabrication
The order of fabrication is as follows:• Ordering of components needed.• Component prototyping and functionality assurance.• Mounting components onto PCBs.• Construction of payload enclosure.• Testing and certifying that all components work together.
Software Design
Software RequirementsControl Instruments
- Time Stamp
- Temperature Sensor
- Accelerometer
- Digital Camera
Calibrate DataAnalyze DataInterpret Data
Data Format and Storage
EEPROM will have to store 13 bytes per minute for 4 hours from the
4 * 60 minutes = 240 minutes13 bytes * 240 minutes = 3, 120 bytes for the whole
flight
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
Software: Pre- Flight
Software:During Flight
• Main loop: After every minute
Software:During Flight• The accelerometer Loop: If one minute has not passed
Software: Post- Flight
Data Analysis Plan
• Level 0: Raw Data - Data downloaded to BASIC STAMP and saved using Term 232
• Level 1: Calibrated Data- Convert digital values into physical quantity
• Level 2: Analysis-Data interpreted using Graphing Analysis -Frame grabber to analyze video image
-Accelerometer’s frequency using Spectrogram
Work Breakdown Schedule
Risk Management & Contingency
Management Plan
Team TIGRE member roles:
-Ana M. Espinal Mena: Electronics design.
-Jonathan Diaz Valerio: Mechanical design & fabrication.
- Victoria Gonzalez Nadal: Software Design and implementation.
Team TIGRE webpage: www.pjarea.com/wiki