1. Avionics AAE 450 Spring 2008 Project Bellerophon April 17, 2008 Avionics

2. Overview Avionics Telecommunications Vehicle Antennas Data Channels Tracking Ground Antennas Data Channels Data Processing Flight Control Data Processing Inputs Sensors Outputs Controls Power Systems Source Supply Avionics AAE 450 Spring 2008 1

3. Electronic Parts: Component Rating CommercialClass BClass S Commercial RequirementsClass S Requirements Infinite production lot sizeBuilt one at a time No burn-in testingExtended burn-in time (up to 240 hours) No detailed failure analysisExtended failure analysis No life testing1,000 hour life test on every lot No traceabilityTraceable to the raw materials > 1% failure per 1000 hours allowed0.0001% failures per 1000 hours allowed 1 NASA Electronics Parts Assurance Group Avionics AAE 450 Spring 2008 2

4. Telecom Analysis: Doppler Shift Frequency Shift due to Doppler Effect Avionics AAE 450 Spring 2008 3

5. Telecom Analysis: Data Rate Change in Link Margin due to Data Rate Avionics AAE 450 Spring 2008 4

6. Telecom Analysis: Path Length Change in Link Margin due to Signal Path Length Avionics AAE 450 Spring 2008 5

7. Telecom Design: Vehicle Link Budget ItemValueUnits frequency401MHz transmitter power5Watts transmit antenna beamwidth60deg transmit antenna diameter0.87m equiv isotropic radiated power12.3dB-W propagation path length5,000km receive antenna diameter10m receive antenna beamwidth5.24deg data rate9,600bps signal to noise ratio50.82dB carrier to noise density ratio90.64dB-Hz bit error rate0.00001--- implementation loss-2dB final margin39.20dB Simplified Link Budget Minimum Margin: 3 dB Vehicle Margin: 39.2 dB Avionics AAE 450 Spring 2008 6

8.  Range Safety Officer (RSO) –An individual who is responsible for the remote destruction and consequent flight termination of the launch vehicle should it be deemed a hazard.  RSO Responsibilities –Evaluate the launch vehicle design as well as oversee the manufacturing process. –Monitors the launch vehicle and environmental conditions prior to launch. –Monitors and tracks the launch vehicle during flight.  Hiring –Budget $1,700 per launch, assuming a 5 day period. Range Safety: Personnel Avionics AAE 450 Spring 2008 7

9.  Flight Corridor –An imaginary zone that exists in a space above the launch range.  Application –Implemented so that if the launch vehicle where to experience a failure during flight, the vehicle will fall to the ground in an uninhabited area.  Termination –The launch vehicle must be destroyed if it flies outside the predetermined flight corridor. Range Safety: Flight Corridor Avionics AAE 450 Spring 2008 8

10. Non-Space-Rated Sensors Sensor TypePart NumberManufacturerUnit Price ThermalTS3-85Cantherm$10.29 Pressure2000260 Measurement Specialties Inc. $104.06 Flow26616Gems Sensors, Inc.$154.95 ForceFSS1500NSR Honeywell Sensing and Control $46.56 Avionics AAE 450 Spring 2008 9

11. Space-Rated Sensors Sensor TypePart NumberManufacturer Unit Price ThermalS311-641/04 Honeywell Sensing and Control $800 PressurePPTR Honeywell Sensing and Control $970 Avionics AAE 450 Spring 2008 10

12. Sensor Reliability Analysis: Thermal SensorCompanyAccuracyReliability 270 Space SeriesHoneywell Aerospace ±2.8°C100,000 Cycles MCP9700/9700A (non-space-rated) Microchip±2°Cnone AS-TE (space- rated) Fluid Components International ± 0.3° C200,000+ Hours Various (space- rated) Measurement Specialties ±0.01˚C3500 cycles (can be specified) This table details the reasons for differences in cost. Avionics AAE 450 Spring 2008 11

13. Power Supply: Power Budget Vehicle Flight TimeBalloon Rise Time Vehicle System Percent of Operating Power Power (W) Energy Consumption (Wh) Mass (kg) Power (W) Energy Consumption (Wh) Mass (kg) Payload5101.040.011030.000.27 Propulsion35707.250.0700.00 Attitude Control15303.110.0300.00 Communications10202.070.022060.000.55 Command and Data Handling 5101.040.011030.000.27 Thermal5101.040.0100.00 Power Management 25505.180.051030.000.27 Total10020020.720.1950150.001.36 1.5 Safety Factor30031.080.28752252.05 200g Payload Case, Silver Zinc Battery, Balloon Launch Avionics AAE 450 Spring 2008 12

14. Power Supply: Battery Selection LiCFLi SOCl 2 AgZn Watt-Hours/Kilogram 130185110 Watt-Hours/Liter 160240200 Discharge Rate LowModerateHigh Failure Tolerance Low High Cell Voltage 2.95V3.1V1.5V Experience Level HighModerateHigh Costs Low Avionics AAE 450 Spring 2008 13

15. Power Supply: AgZn Battery AgZn Benefits  Can charge 4 to 6 times in case of scrub  Capable of controlling gimballing, ignition, and range safety subsystems Silver Zinc (AgZn) Battery PropertyValue Weight (kg)2.3 - 4.5 Volts (V)1.6 - 1.85 Rated Capacity (Ah).8 - 800 Specific Energy (Whr/kg)55 - 286 Energy density (Whr/l)55 - 262 1 http://www.eaglepicher.com/ Avionics AAE 450 Spring 2008 14

16. Power Supply: Batteries Estimate Cost: < $10,000 Weight: 2.3-4.5 kg BatteryWeightWh/kgCost Silver-Zinc (AgZn)2.3-4.5 kg110~$10,000 Lithium- Monofluoride (Li/CF) 2.3-4.5 kg130 -------- Lithium/Thionyl Chloride (Li/SoCl 2 ) 2.3-4.5 kg185 -------- Avionics AAE 450 Spring 2008 15

17. Installation Cost Primary Contractor: Aircraft Electrician Median Salary 1 $40,984.00 Work Days per Year240 Income Per Day$170.77 Income Per Hour$21.35 Billing Rate Per Hour$32.02 At four weeks of billable work Installation Cost:$7,172.20 1 Salary data from www.salary.com Avionics AAE 450 Spring 2008 16

18. Telecom: Failure Analysis Sources of Failure Telecom Equipment Radio Transmitter Receiver Antenna Data Handling Data processing Data wiring External Sources Doppler Shift Power Supply Orientation Misalignment Reliability Factors For a low complexity system with redundancy 1 : Part Class Reliability Class B: 98.75% Class S: 99.87% Assumptions - Simple system - Low radiation dose - Reliability based on a five year mission plan 1 Wertz, 404. Avionics AAE 450 Spring 2008 17

19.  First Stage: 6.024 kg total (safety factor=1.2) -wiring: 2kg -sensors 1.02kg -battery 2kg  Second Stage: 30.2664 kg total (safety factor=1.2) -Telecom: 10 kg-CPU: 0.85 kg -Sensors: 1.02 kg-Range Safety: 9.23 kg -Wiring: 2 kg-IMU: 0.122 kg -Battery: 2kg  Third Stage: 1.2 kg total (safety factor=1.2) -Wiring: 1 kg Mass Budget Avionics AAE 450 Spring 2008 18

20.  Launch lock (US Patent 6508437)  Motorized release  Explosive Bolt/Spring sequence 1  Explosive/Slingshot Sequence 1 (Professor Filmer), (International Reference Guide to Space Launch Systems pg 296) Payload: Launching Options Avionics AAE 450 Spring 2008 19

21.  Assumptions Made –The Earth is spherical in shape. –The area where the signal intercepts the Earth is circular. –Neglect any antenna mounting errors or design issues. –Neglect any atmospheric anomalies which may refract the signal. –The signal propagation from a cluster of directional antennas can be estimated using a omnidirectional antenna. –The signal propagation from an omnidirectional antenna is spherical in shape. Signal Projection: Assumptions Avionics AAE 450 Spring 2008 20

22. 1 Professor Filmer, Purdue University School of Aeronautics and Astronautics Approximate Ground Equipment Costs 1 Radio ($1,200) Antennas ($500) Computer ($2,000) Misc ($500) Total: $4,200 Example Case: Small Payload Launch Vehicle LV Ground TrackBalloon Ground Track 236.09 km120.74 km Mean Propagation Radius 4,995.4 km Launch Vehicle Tracking Avionics AAE 450 Spring 2008 21

23. Avionics: Cost Budget UnitCosts Wiring - Materials$ 500 - Installation$ 7,500 CPU$ 10,000 IMU$ 15,000 Sensors (500 each)$ 8,000 Battery$ 10,000 Range Safety$ 20,000 Ground Tracking$ 24,000 Total$ 95,000 Avionics AAE 450 Spring 2008 22