TEAM CHINESE BANDIT OZONE PAYLOAD CRITICAL DESIGN REPORT (CDR) Zach Baum Harry Gao Ryan Moon Sean Walsh 1 TABLE OF CONTENTS Mission Goal Objectives Requirements Electrical Design Software Design Thermal Design Mechanical Design Payload Construction Plan Mission Operations Master Schedule Master Budget 2 MISSION GOAL Create a profile of ozone concentration with respect to altitude from ground level to 100,000ft. 3 Ozone sensor reading for 2012 UND/UNF HASP payload SCIENCE OBJECTIVES Map peak of ozone concentration in upper atmosphere. Create ozone concentration profile with respect to altitude. Map out any fluctuations within ozone profile. 4 TECHNICAL OBJECTIVES The payload must measure ozone concentration The onboard program will be able to: Take temperature readings within close proximity to ozone sensor Maintain proper operating temperature for all necessary components 5 SCIENCE REQUIREMENTS The payload must take measurements of ozone concentration every 3 seconds Team Chinese Bandits must receive time and altitude GPS information for analysis from LaACES management The payload must measure the peak ozone concentration to within .2ppmv 6 TECHNICAL REQUIREMENTS The payload must: Not have a mass greater than 500g Not exceed 3oz/in2 on any surface Have two holes 17in apart through which the payload will interface with the balloon Costs must remain within the allotted $500 budget for Chinese Bandits In order for the payload to create an ozone profile of the atmosphere, the following requirements must be met: Payload must take measurements of ozone concentration throughout the flight Payload must be recovered for post-flight analysis Altitude must be known to within 65 feet For the accuracy to be known within 65 feet, the following requirements must be met: Real-time clock must be synced with GPS time during pre-flight Real-time clock must be accurate to within 3 seconds of the LaACES LASSEN iQ GPS 7 SENSORS OZONE SENSORS ITO acts as a variable resistor whose resistance changes in the presence of ozone Applying a constant current allows us to relate the change in output voltage to the resistance and ozone concentration as measured by each sensor Has a small operating temperature range, therefore a thermal controlling system will be needed 8 SENSORS OZONE SENSORS Calibration data will be obtained from Dr. Patel The equation [𝑥 = (𝑦 − 𝑏)/𝑚] can be used to relate the resistance of each sensor to the ozone concentration Y = sensor resistance, X = concentration of ozone, m = slope of the calibration curve, b= y-intercept of curve 9 SENSORS THERMISTOR KC003T-ND thermistor Property Value Operating Temperature Range R0 (Resistance at 25°C) -50°C - 150°C Temperature Coefficient (@ 25°C) Accuracy (@ 25°C) -4.40%/°C Resistance at 20°C 12.5 kΩ Resistance at 30°C 8.055 kΩ 10 kΩ +/- 1°C 10 HEATER KHLV-101/5 Kapton Heater 1in. X 1in. Provides up to 5W of heat with 28V max voltage Property Value Resistance 150 Ω Current draw 80 mA Power draw 0.936 W 11 SENSOR INTERFACING OZONE SENSOR 12 OZONE SENSOR INTERFACING Zero temp-coefficient circuit for the constant current source Resistor value LM234 current (Ω) 0 10 100 600 1000 1400 1500 1600 2000 2400 2800 3200 3600 output (mA) 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.24 1.48 13 THERMISTOR INTERFACE Different constant current, op amp Output voltage 3V .2V Thermistor resistance 12.5KΩ 6.5KΩ 14 CONTROL ELECTRONICS BASIC STAMP PIN LAYOUT Pin no. 1 2 3 4 5 Pin no. 13 14 15 16 17 Pin Function I/O (EEPROM) RTC (EEPROM) Reset RTC DATA (RTC) I/O (RTC) 6 Pin Function Serial Out Serial In ATN Vss Data Output (ADC0838) RTC (ADC0838) 18 7 8 9 10 11 12 CS (ADC0838) NA LED Output LED Output LED Output LED Output 19 20 21 22 23 24 Data Output (ADC0834) RTC (ADC0834) CS (ADC0834) VDD RES Vss VIN 15 CONTROL ELECTRONICS ADC0838 PIN LAYOUT Pin no. Function Pin no. Function 1 CH0 11 2 CH1 12 Analog Ground VREF 3 CH2 13 Shift Enable 4 CH3 14 DO 5 CH4 15 SARS 6 CH5 16 CLK 7 CH6 17 DI 8 CH7 18 CS 9 COM 19 V+ 10 Digital Ground 20 VCC 16 CONTROL ELECTRONICS CIRCUIT INTERFACING Sensor Board (16 card edge connector ) 16 14 12 10 8 6 4 3 2 *Other pins not 16 wire Ribbon Cable S1 S2 S3 S4 S8 S7 S6 Common S5 Condition ing Board (8x2 pin Header) 1 2 3 4 5 6 7 8 9 *Other pins not used S1 S2 S3 S4 S8 S7 S6 C S5 17 CONTROL ELECTRONICS CIRCUIT INTERFACING Conditionin g Board (13x1 pin header) 1 2 3 4 5 6 7 8 9 10 *Other pins not used 26 wire Ribbon Cable Vcc (5V in) Vref (3V ref.) ADC0 (Thermistor I/O) Not used Not used Not used P0 (I/O ITO) P1 (RTC ADC0838) P2 (CS ADC0838) P3 (3V Vref.) BalloonSat (13x2 pin header) 1 3 5 7 9 11 13 15 17 19 All Even pins Ground *Other pins not used Vcc (5V in) Vref (3V ref.) ADC0 (Thermistor I/O) Not used Not used Not used P0 (I/O ITO) P1 (RTC ADC0838) P2 (CS ADC0838) P3 (3V Vref.) 18 POWER SUPPLY AND DISTRIBUTION Two power sources: one 9V, one 12V 19 HEATER AND RELAY CONFIGURATION Will Use a 2N3904 transistor as a relay BASICStamp will send 3V to base pin to saturate it, allowing the 12V load to flow through the transistor and power heater 10KΩ resistor placed before the base pin will limit the base current that can flow into the transistor 20 POWER BUDGET Consumer Ozone Sensors Thermistor Heater 80 mA 12 V Balloon Sat 53 mA 9V Total 213.01 mA Power Supply 1 Needed capacity Power Budget Voltage Consumption Rate 1 mA * 8 Variable sensors = 80 (dependent mA on sensor, 3V max) .01 mA 3V Power Supply 2 665.05 mAh 400 mAh Required 9 V Voltage 12 V Energy 400 mAh .05 mAh 400 mAh 265 mAh 1065.05 mAh AA Lithium Ion Voltage (per battery) 1.5 V Capacity(per 3000 mAh battery) 21 THERMAL DESIGN LaACES Thermal Flight Earth-Space Parameters Stefan-Boltzmann Isun (solar constant) T-space Flight altitude Isun UNIT S 1377.0 W/m2 Latitude 31 degrees T-float 210 K Albedo 0.5 4 K Day of year 141 day 30500 m Hour of day 14 hr 5.67E- W/m2 08 K4 1377 W/m2 Earth orbit eccentricity 0.01672 Declination angle 19.91164 deg T-earth 273 K 638000 0 m Inclination angle 29.14873 deg R-earth IR Fluxmin 160 W/m2 Internal Heat 2.96 W Payload Parameters View factor payloadearth View factor payloadspace 0.451 Sphere radius 0.103 m Effective Isolar 1360.54 Effective Isphere 339.12 ENERGY BALANCE calculations bladder thickness 0.000 m Qsun 15.824 W kevlar shell thickness 0.000 m Qalbedo 13.861 W bladder conductivity 0.026 W/mK Qpower 2.960 W kevlar shell conductivity 0.040 W/mK Q-IR 2.046 W 0.700 W/m2 W/m2 22 THERMAL DESIGN Insulation Parameters Total input: 34.690 W insulation absorptivity 0.350 hrad,earth 1.862 W/m2 K insulation thickness 0.019 m hrad,space 0.769 W/m2 K insulation emissivity 0.850 constant1 0.248 W/K insulation conductivity W/m 0.027 K constant2 0.103 W/K constant3 0.053 W/K Area Calculations Total sphere projected area 3.33E02 m2 Qrad-to-earth 2.295 W Total sphere surface area 1.33E01 m2 Qrad-to-space 28.542 W Qconv-at-float 3.853 W Total output: 34.690 W Ti outer 9.2 degC Ti inner 22.5 degC Tk inner 22.5 degC Tb inner Tavg interior air 22.5 degC 24.7 degC 23 MECHANICAL DESIGN 24 WEIGHT BUDGET Componen t Quantity Mass BalloonSat 1 68.9g +/- 0.05g Measured Lithium AA Batteries (9V total unit) 6 88.3g +/- 0.1g Measured Lithium AA Batteries (12V total unit) 8 FOAMULA R Casing 1 ITO sensor 1 Total 117.9g 57.5g Uncertaint Calculate y d/Measur ed +/- 0.1g +/- 2 g 13g +/- 0.1g 345.6g +/- 2 g Measured Component Approximate Mass Operational Amplifier 57g Sensor Interface 15g Electrical Wiring 15g Heater and Thermistor 10g Glue, Paint, Structural Components 10g Total 112g Calculated Measured 25 PRE-FLIGHT SOFTWARE 26 PRE-FLIGHT SOFTWARE: INITIALIZATION STAGE 27 PRE-FLIGHT SOFTWARE: TESTING STAGE 28 FLIGHT SOFTWARE 29 FLIGHT SOFTWARE SUBROUTINES 30 FLIGHT SOFTWARE SUBROUTINES CONT. 31 POST FLIGHT SOFTWARE Byte Offset Data Description 0 1 2 3 4 5 6 7 8 9 10 11 Hour Minute Second ITO1 ITO2 ITO3 ITO4 ITO5 ITO6 ITO7 ITO8 Thermistor Timestamps the Data Reads ozone concentration Reads temperature of ITO Array 32 PAYLOAD CONSTRUCTION PLAN HARDWARE FABRICATION AND TESTING Full system testing will be conducted after each subsystem is tested and proven Payload design will be updates after testing A delay in any subsystem will cause combined testing to be delayed 33 INTEGRATION PLAN After each subsystem is tested, individual systems will be connected together to ensure interfaces work properly Electrical/software interfacing has been tested and proven Tests on interfacing electrical, mechanical, and thermal will ensure proper operation temperature can be maintained Testing will be done on all systems in a simulated flight to complete payload integration 34 FLIGHT SOFTWARE IMPLEMENTATION AND VERIFICATION Flight software was tested with electrical prototypes to ensure it was functioning correctly Pre-Flight will be loaded the day before flight to clear EEPROM and sync GPS time to RTC A computer located on site will be used to run programs and retrieve data 35 FLIGHT CERTIFICATION TESTING Tests will be conducted to ensure payload can survive flight Temperatures of -70°C to 30°C Pressure of .163mBar to 1000mBar Impact upon landing A shock test and a thermal/vacuum test will be conducted 36 SYSTEM TESTING PROCEDURE Payload needs to survive 8.94 m/s 𝑉= 2∗𝐻∗𝑔 8.9408 = 2 ∗ 𝐻 ∗ 9.8 H = 4.08m or 13.38 ft. Procedure checklist Power up payload Run preflight software Run flight software Drop from13.4 feet onto the floor Run post-flight software Verify that all onboard electronics are operating properly 37 VACUUM TEST PROCEDURES Power up payload Run preflight software Run flight software Place payload in Vacuum Testing Chamber Make sure that vacuum chamber is sealed and pressure gauge is turned on Simulate flight environment in vacuum testing chamber. This include having a temperature range -70 to 30C This include pressure of .163 mBar- 1000 mBar Run post-flight software Analyze and verify data 38 SYSTEM TESTING RESULTS ITO removed from box Preliminary tests Resistance vs Time 600.0 done to test if 500.0 sensors will work 400.0 Spark gap created in 300.0 box to create ozone 200.0 ITO warmed to operating ITO placed 100.0 ITO warmed to 25°C in box temperature and 0.0 placed in box until Seconds After Beginning Test 480 seconds After speaking with Dr. Patel, long reaction times may be due to not enough ozone to fully react, or not enough airflow across the sensor Resistance 1 30 59 88 117 146 175 204 233 262 291 320 349 378 407 436 465 494 523 552 581 Change in Resistance of original value of 1.4kΩ 39 PRE-LAUNCH REQUIREMENTS AND OPERATIONS: CALIBRATIONS Two Instruments that require calibration Thermistor Calibrate for low temperature of 20°C Calibrate for high temperature range of 35°C ITO Sensor Do not have necessary equipment to calibrate Will be provided by Dr. Patel of the University of North Florida 40 PRE-LAUNCH REQUIREMENTS AND OPERATIONS: CALIBRATION PROCEDURES Thermistor Fill glass with cold water in a heat metal container Place thermometer and thermistor Record the sensor reading using the voltmeter and flight software for temperature from 20°C to 35°C ITO Will be provided by Dr. Patel 41 ITO Circuit Thermistor PRE-LAUNCH CHECKLIST Event Time Time Needed Materials Needed Verify all systems are flight ready 2 days before flight 12 hours before flight 20 minutes The full Chinese Bandits payload, multimeter 15 min. Set time of BalloonSAT clock 12 hours before flight 15 min. Replace battery packs with fresh, tested packs 12 hours before flight 5 min. The full Chinese Bandits payload, one computer with BASIC Stamp Editor software, one 9-pin serial cable The full Chinese Bandits payload, one computer with BASIC Stamp Editor software, one 9-pin serial cable, the LaACES GPS unit with computer hookups Fresh, tested 9 and 12 volt battery packs Load Flight Software onto the BalloonSat 12 hours before flight 5 min. Connect battery packs, close and seal payload lid 1 hour before flight 5 min. Run Pre-Flight Software The full Chinese Bandits payload, one computer with BASIC Stamp Editor software, one 9-pin serial cable Tape 42 FLIGHT REQUIREMENTS, OPERATIONS AND RECOVERY Batteries will provide the BalloonSat and sensors with enough power for the duration of the flight EEProm will have enough memory to take measurements for the duration of the flight Must find and recover EEProm during recovery; Extra BallonSats will be brought in order to retrieve the data from the EEProm 43 DATA ACQUISITION AND ANALYSIS PLAN: GROUND SOFTWARE The following procedure will be used to complete Ground Software and export flight data. 44 DATA ACQUISITION AND ANALYSIS PLAN: DATA ANALYSIS PLAN ADC values will be converted into ozone measurements in PPM(Parts Per Million) Thermistor values will be converted to degrees in Celsius Sync GPS value with time to get altitude data 45 DATA ACQUISITION AND ANALYSIS PLAN: DATA ANALYSIS PLAN (CONTINUED) The following graphs will be made from flight data to help with the analysis process Ozone vs. altitude Ozone vs. time Temperature vs. time Ozone vs. temperature Expected uncertainties for thermistor will be 1 percent while the uncertainties for the ozone sensor will be 0.2ppm 46 PROJECT MANAGEMENT WBS 47 PROJECT MANAGEMENT WBS 48 PROJECT MANAGEMENT WBS 49 STAFF ORGANIZATION AND RESPONSIBILITIES Category Team Member Project Manager Zach Baum Software Developer and Lead Mechanical Lead Harry Gao Electrical Lead Harry Gao Calibrations Harry Gao Integration Zach Baum Version Control and Editing System Testing Ryan Moon Sean Walsh Sean Walsh 50 MASTER BUDGET EXPENDITURE PLAN Parts For Testing (1) Quantity 1 1 1 Parts For Testing (2) 1 1 1 1 1 1 Part no. ADC088S102 CIMT/NOPBND LM234Z6/NOPB-ND AT24C512CSSHM-B-ND 2N7002K-T1E3CT-ND KHLV-101/5 Description 8 channel ADC Unit Price $3.09 Total Price $3.09 Constant Current Source 64KB EEPROM Transistor for relay Heater $1.27 $1.27 $1.76 $1.76 $0.38 $0.38 $31.00 $18.99 TIP112TUND 24LC512-I/PND ADC0834CC N/NOPB-ND LM234Z6/NOPB-ND ADC0838CC N/NOPB-ND ITO Sensor for Testing Transistor for relay 64KB EEPROM 4 Channel ADC Constant Current Source 8 channel ADC $31.00 Shipping Total $0.66 $1.96 $1.96 $3.11 $3.11 $1.27 $1.27 $2.97 $8.91 Borrowed $0.00 Shipping Total $14.94 Ozone Sensor $0.66 51 MASTER BUDGET EXPENDITURE PLAN Parts for Fabrication 24 AA Energizer L91 batteries Batteries for power supply 6 AD822ANZ-ND Op-Amp for ITO’s $6.28 2 AD820 $4.54 $9.08 18 3299W-104LFND LM234Z6/NOPB-ND TIP112TU-ND Op-Amp for Thermistor Variable resistor $2.60 $46.80 Constant Current Source Transistor for relay Back-up heater Back-up EEPROM Printed Circuit Board $1.27 $15.24 $0.66 $1.32 $31.00 $1.96 $31.00 $1.96 $177.70 $177.70 Borrowed $0.00 $0.46 $5.52 $8.14 $8.14 Shipping Total $18.99 Total Total Expected Expenditure $416.85 $502.18 12 2 1 1 1 1 12 1 KHLV-101/5 24LC512-I/PND PCB Flight-ready ITO sensor 445-5327-ND Pack of Real Velcro 10microF capacitor $49.95 for 24pack $49.95 $37.68 52 MASTER BUDGET MATERIAL ACQUISITION PLAN Material BalloonSat Qua ntiti es 1 How Acquired When Needed When to Order Supplied by LaACES Supplied by LaAces Ordered from Digikey Calibration and testing Calibration and testing Calibration and testing Already Have 1 week before fabrication already have Capacitors, resistors, wires, etc ADC088S102CIMT/NOPBND 8 channel ADC LM234Z-6/NOPB-ND Constant Current Source x 12 Ordered from Digikey AT24C512C-SSHM-B-ND 64KB EEPROM 2 Ordered from Digikey 2N7002K-T1-E3CT-ND Transistor for relay 1 Ordered from Digikey One for Calibration and testing, the rest for fabrication One for Calibration and testing, the other for backup Calibration and testing KHLV-101/5 Heater TIP112TU-ND 1 Ordered from Omega Ordered from Calibration and testing Calibration 1 1 Already Have Already Have Need 1 more already have already have 53 MASTER BUDGET MATERIAL ACQUISITION PLAN 24LC512-I/P-ND 64KB EEPROM 1 Ordered from Digikey Calibration and testing already have ADC0834CCN/NOPB-ND 4 Channel ADC 1 Supplied by LaAces Calibration and testing already have LM234Z-6/NOPB-ND Constant Current Source 1 Ordered from Digikey Calibration and testing already have ADC0838CCN/NOPB-ND 8 channel ADC 1 Ordered from Digikey Calibration and testing already have ITO Sensors 1 Borrowed Calibration from Dr. Patel and testing already have 24 AA Energizer L91 batteries Batteries for power supply AD822ANZ-ND Table 22: Material Acquisition Plan Op-Amp for ITO’s 6 Order Online through Amazon Fabrication Need to order 1 week before fabrication Ordered from Digikey Fabrication Need to order 1 week before fabrication 54 RISK MANAGEMENT AND CONTINGENCY PLAN System Risk Contingency Trigger Plan Electrical Not returning correct data Calibration and testing in simulated conditions Changes in output related to unexpected conditions Electrical Interface and component problems Faulty wiring and components Harry Mechanical Inclement weather Weather Sean/Ryan Electrical/M echanical Inability to maintain operating temperature Testing components hardware and software before, during, and after assembly Structurally sound and sealed mechanical design and testing Using a heater and thermistor, testing in simulated Extreme cold Team Who is responsible Team 55 RISK MANAGEMENT AND CONTINGENCY Electrical Frying EEPROM All systems Loss of payload All systems Loss of team member Project Not meeting Management deadlines All systems Over budget Have backup parts, and use extreme caution preflight Prepare failure report Carelessness Zach Loss of payload during flight Rest of team Increased would pick up workload responsibilitie s Set early Poor project management deadlines to allow for mistakes to be fixed Find cheaper Not enough money and more cost-effective components Team/LaACE S staff Team Zach Team 56