Project Bellerophon April 17, 2008

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Darleen McCoy
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1 Project Bellerophon April 17, 2008

2 Overview Telecommunications Flight Control Power Systems Vehicle Ground Data Processing Inputs Outputs Source Antennas Antennas Sensors Controls Supply Data Channels Data Channels Tracking Data Processing 1

3 Electronic Parts: Component Rating Commercial Class B Class S Commercial Requirements Infinite production lot size Class S Requirements Built one at a time No burn-in testing Extended burn-in time (up to 240 hours) No detailed failure analysis No life testing No traceability Extended failure analysis 1,000 hour life test on every lot Traceable to the raw materials > 1% failure per 1000 hours allowed % failures per 1000 hours allowed 1 NASA Electronics Parts Assurance Group 2

4 Telecom Analysis: Doppler Shift Frequency Shift due to Doppler Effect MHz 1.45 GHz 2.2 GHz 3.0 GHz Frequency Shift (k khz) Vehicle Velocity (m/s) 3

5 Telecom Analysis: Data Rate Change in Link Margin due to Data Rate MHz 1.45 GHz 2.2 GHz 3.0 GHz 3 db Margin Link Margin (d db) Data Rate (bps) x

6 Telecom Analysis: Path Length Change in Link Margin due to Signal Path Length MHz 1.45 GHz 2.2 GHz 3.0 GHz 3 db Margin Link Margin (db B) Path Length (km) 5

7 Telecom Design: Vehicle Link Budget Simplified Link Budget Item Value Units frequency 401 MHz transmitter power 5 Watts transmit antenna beamwidth 60 deg transmit antenna diameter 0.87 m equiv isotropic radiated power 12.3 db-w propagation path length 5,000 km receive antenna diameter 10 m receive antenna beamwidth 5.24 deg data rate 9,600 bps signal to noise ratio db carrier to noise density ratio db-hz bit error rate implementation loss -2 db final margin db Minimum Margin: Vehicle Margin: 3 db 39.2 db 6

8 Range Safety: Personnel 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. 7

9 Range Safety: Flight Corridor 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. 8

10 Non-Space-Rated Sensors Sensor Type Part Number Manufacturer Unit Price Thermal TS3-85 Cantherm $10.29 Pressure Measurement Specialties Inc. $ Flow Gems Sensors, Inc. $ Force FSS1500NSR Honeywell Sensing and Control $

11 Space-Rated Sensors Sensor Type Part Number Manufacturer Unit Price Thermal S /04 Honeywell Sensing and Control $800 Pressure PPTR Honeywell Sensing and Control $970 10

12 Sensor Reliability Analysis: Thermal Sensor Company Accuracy Reliability 270 Space Series Honeywell Aerospace ±2.8 C 100,000 Cycles MCP9700/9700A (non-space-rated) Microchip ±2 C none AS-TE (spacerated) Fluid Components International ± 0.3 C 200,000+ Hours Various (spacerated) Measurement Specialties ±0.01 C 3500 cycles (can be specified) This table details the reasons for differences in cost. 11

13 Power Supply: Power Budget Vehicle Flight Time Balloon Rise Time Percent of Energy Energy Operating Power Consumption Mass Power Consumption Mass Vehicle System Power (W) (Wh) (kg) (W) (Wh) (kg) Payload Propulsion Attitude Control Communications Command and Data Handling Thermal Power Management Total Safety Factor g Payload Case, Silver Zinc Battery, Balloon Launch 12

14 Power Supply: Battery Selection LiCF Li SOCl 2 AgZn Watt-Hours/Kilogram Watt-Hours/Liter Discharge Rate Low Moderate High Failure Tolerance Low Low High Cell Voltage 2.95V 3.1V 1.5V Experience Level High Moderate High Costs Low Low Low 13

15 Power Supply: AgZn Battery Silver Zinc (AgZn) Battery Property Value Weight (kg) Volts (V) Rated Capacity (Ah) Specific Energy (Whr/kg) Energy density (Whr/l) AgZn Benefits Can charge 4 to 6 times in case of scrub Capable of controlling gimballing, ignition, and range safety subsystems

16 Power Supply: Batteries Battery Weight Wh/kg Cost Silver-Zinc (AgZn) kg 110 ~$10,000 Lithium- Monofluoride (Li/CF) Lithium/Thionyl Chloride (Li/SoCl2) kg kg Estimate Cost: < $10,000 Weight: kg 15

17 Installation Cost Primary Contractor: Aircraft Electrician Median Salary 1 $40, Work Days per Year 240 Income Per Day $ Income Per Hour $21.35 Billing Rate Per Hour $32.02 At four weeks of billable work Installation Cost: $7, Salary data from 16

18 Telecom: Failure Analysis Telecom Equipment External Sources Reliability Factors For a low complexity system with redundancy 1 : Sources of Failure Radio Transmitter Receiver Antenna Data Handling Data processing Data wiring Doppler Shift Power Supply Orientation Misalignment 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,

19 Mass Budget First Stage: kg total (safety factor=1.2) -wiring: 2kg -sensors 1.02kg -battery 2kg Second Stage: 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: kg -Battery: 2kg Third Stage: 1.2 kg total (safety factor=1.2) -Wiring: 1 kg 18

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

21 Signal Projection: Assumptions 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. 20

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

23 : Cost Budget Unit Costs Wiring - Materials $ 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 22

Primary POC: Prof. Hyochoong Bang Organization: Korea Advanced Institute of Science and Technology KAIST POC

Primary POC: Prof. Hyochoong Bang Organization: Korea Advanced Institute of Science and Technology KAIST POC Title: Demonstration of Optical Stellar Interferometry with Near Earth Objects (NEO) using Laser Range Finder by a Nano Satellite Constellation: A Cost effective approach. Primary POC: Prof. Hyochoong