BlackBox Sat Critical Design Review Colorado State University-Pueblo April 2, 2004 Greg Barela Jose Segovia Enrique Cornejo

Mission Description To obtain certain individual atmospheric characteristic data. Measure acceleration activity and the Earth’s magnetic force. Store and retrieve collected data.

Mission Goals and NASA Benefits Collect sample satellite direction activity Observe acceleration of the Earth’s atmosphere during entire flight and landing Route gathered data from microprocessor to micro-cassette recorder. NASA Benefit: Determining direction for output video and still shot evaluation.

System Requirements Payload under 1.5kg On-board power supply Heating and ventilation subsystems External power engaging mechanisms

System Overview Basic outline of system

Subsystem Description We have nine subsystems which form our payload. – Sensors – Instrumentation amplifier – Relays – Signal converter – Micro-controller – Coding – Micro-cassette recorder – Shell – Heater Circuit

Magnetic Field Sensor Honeywell (HMC1001) + - 3mv/V/gauss 3-5Volt supply Bandwidth is over 1MHz Analog output

Accelerometer ±2 g Dual Axis Accelerometer Features 1000 G shock survival 3 V to 5.25 V Single supply operation Low Power < 0.6 mA Duty Cycle Output

Instrumentation Amp Gain =

Relays Double Pole Double Throw – 11.1mA contact rating – 5v coil voltage Single Pole Single Throw –.20mA contact rating – 5V coil voltage

A/D Converter ADC801LCN – 5V supply – 0V-5V input voltage range – 8-bit resolution

PIC16F84 18-Pin Enhanced Flash/EEPROM 8-bit µ -controller 68 bytes EEPROM 1K x 14 Program Memory

Objective of Coding Digital Output Accelerometer Sensor – Calibrate – Measure Tilt – Frequency Differentiation Linear Output Magnetic Field Sensor – A/D Conversion – Port Intializing – Delays

Computer Programming PICSTART Plus MPLAB SIM MPASM Assembler

Flowchart

Sony M-560V Voice Operated Recording 2AA battery supply 90 minute tapes 300Hz-4000hz 113 grams

Shell House all seven subsystems Protects subsystems from the changing environment Helps cushion on landing

Shell Hardware ¼’’ foam core forms the outer shell Aluminum tape for extra strength Glue to adhere the shell

Heater Circuit (3) 9V batteries (2) 6 Ohm 5 watt wire wound resistors

Payload Insulation Styrofoam – Help keep subsystems from freezing – Cushions the landing – Helps protect all sybsystems

System Interfaces Complete System Overview

Mass Budget

Project Organization Greg Barela : purchase parts, create schematics, sensor prototyping, circuit integration Jose Segovia: sensor modules programming, sensor to micro- processor research and evaluation, output data conversion. Enrique Cornejo: Payload construction, Heater Circuit, insulation and ventilation.

Budget

Schedule

Thanks you for your time. Are there any questions or suggestions?