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Matt Chapin, Nick Wackel, Olon Pierce Preliminary Design Review THF-15
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Overview Physical Craft Ground Systems Cost Background Objectives
Critical System Drivers Mission Design Physical Craft Ground Systems Cost Overview of PowerPoint Provide Background for the mission State Mission Objectives and success criteria Establish Critical System Drivers for trade studies Present Mission Segment Design Propose the best physical crafts to complete the mission Introduce a plan for ground systems Estimate the total cost of the THF-15 project 10/14/14 THF-15
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Landsat 8 Launched February 11, 2013 Sponsored by NASA and the USGS
Forty-year-old program Continuously obtains human sustainment intelligence Food Water Forests Food production and water consumption Deforestation 10/14/14 THF-15
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Sensor Thermal Infrared Sensor (TIRS)
Utilizes new, lower-cost technology to measure land surface temperature Tracks water consumption Design life of three years TIRS uses Gallium Arsenide Quantum Well Infrared Photodetector arrays (LOW COST) to detect thermal infrared wavelengths of light Important application is tracking water consumption based on surface temperature measurements TIRS was a late addition to TIRS and had therefore had a reduced design life of only 3 years 10/14/14 THF-15
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Key Players Data affects all facets of society
National Aeronautics and Space Administration Systems development and launch segment United States Geological Survey (USGS) Ground systems structure and mission operations Data affects all facets of society Mission provides direct benefit to economy Info that can only be acquire from space Major reason for success - continuity of images over its entire lifespan Long-term future of program is uncertain If started today, New mission development, LANDSAT 9, would take around 5 years operational in 2019 TIRS expires in 2016 3 year gap is lifespan of new TIRS 10/14/14 THF-15
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Mission Objectives Intercept Landsat 8 Deploy repair robot
Install new TIRS Detach and enter parking orbit 10/14/14 THF-15
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Critical System Drivers
In order of importance 10/14/14 THF-15
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Sun-Synchronous (SSO)
Performance Mission success is the most critical driver Component Requirements Payload Robot: 100 kg Sensor: 240 kg Orbit Sun-Synchronous (SSO) ΔV Budget Burn for Intercept Burn for Retirement Interface Secure Connection Robot Deployment 10/14/14 THF-15
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Schedule Existing TIRS will expire in early 2016
Goal of initial operating capability within two years 10/14/14 THF-15
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Risk Failure to reach orbit Failure to connect with Landsat 8
Disrupt orbit or damage satellite Failure to retire safely Most risk mitigation occurred with launch segment selection (vehicle reliability, site location & scheduling, weather) Detailed development of bus will minimize interface risk 10/14/14 THF-15
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Cost Physical parameters Orbit Complexity Autonomy
Mass and volume of payload and bus Orbit Complexity Orbit maintenance and attitude control Autonomy 10/14/14 THF-15
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Mission Design 10/14/14 THF-15
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Launch Segment Drivers: Parking orbit Target orbit - SSO
Timing - Intercept Parking orbit Pro - Flexible launch window Con - Two-stage launch vehicle Intercept mission launch must occur when target’s orbital plane intersects the launch site Time to LEO is in seconds to minutes range 10/14/14 THF-15
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Orbit Sun-synchronous Intercept at apogee (minimum velocity)
Characteristic Landsat 8 Eccentricity 9.07e-5 km Perigee 708 km Apogee 710 km Inclination 98.23° Period 98.93 min Sun-synchronous Intercept at apogee (minimum velocity) ΔV - Impact velocity Launch to parking orbit -> upper stage burn to reach inclination and wait for timing Apogee intercept will reduce delta v required to decrease impact velocity 10/14/14 THF-15
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Satellite-to-Satellite Interface
Secure connection Proximity sensor Robot deployment Fully autonomous repair Communication Mission status Lock-on -> deploy robot -> constant communication with ground station -> mission complete -> disengage 10/14/14 THF-15
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Post-Mission Operations
ΔV for maneuvers Retirement options Decrease momentum for reentry - Less fuel required Hohmann transfer orbit super-synchronous - More orbital capabilities, but increased fuel budget 10/14/14 THF-15
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Physical Craft 10/14/14 THF-15
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Payload Fairing Dimensions
Launch Vehicle Requirements SSO Two-stages Payload capabilities Specification Falcon 9 Atlas V 401 Stage 1 9 Merlin 1D Engines Common Core Booster Stage 2 Merlin 1C Vacuum Engine Centaur Upper Stage Payload to SSO 7,348 kg 6,670 kg Payload Fairing Dimensions 5.2 diameter 13.1 length 4.2 m diameter 12.0 m length # of Launches to SSO 3 While looking for Launch Vehicles we decided there were 3 main constraints Sun Synchronous with the landsat Two-Stages-for parking orbit And needed to accommodate our payload 10/14/14 THF-15
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Reliability >> Affordability
Atlas V 401 25 out of 25 successful launches 3 out of 3 SSO launches Launched Landsat 8 Cost ~ $200 million Falcon 9 12 out of 13 successful launches 0 SSO launches Delay Issues Cost ~ $3.3 million At The End of the day we had to go with the reliability of the Atlas V 10/14/14 THF-15
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Will launch with Atlas V 401 based on launch requirements and reliability
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Payload Repair Robot TIRS Fully-autonomous
Continuous mission data transmission Specifications: 100 kg , 0.5 m3 TIRS Specifications: 240 kg , 4.0 m3 Dimensions: 1.1 x 1.4 x 2.0 m 10/14/14 THF-15
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Bus 3-axis attitude control Features: Dimensions: 1.3 x 1.5 x 2.6 m
Onboard solar panel Communications antenna Reaction wheel Dimensions: 1.3 x 1.5 x 2.6 m Deployment face in direction of motion Solar panel always receiving energy because of SSO Nadir-pointing comm antenna Reaction wheel for small adjustments to attitude for line up 10/14/14 THF-15
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Houses mission payload, propulsion system, and communications structure
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Ground Systems 10/14/14 THF-15
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Launch Station Vandenberg Air Force Base SLC-3E
° N, ° W Over-ocean polar trajectory Inclination range from 51°-145° Atlas V 401 has clear range for July 2016 Most important is launch date scheduled for July 2016 VAFB is prime SSO launch site 10/14/14 THF-15
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Mission Operations Existing USGS Landsat 8 ground stations
Sioux Falls, South Dakota Fairbanks, Alaska Svalbard, Norway Global ground station link capabilities Landsat International Cooperator Network Stations downlink mission and telemetry data and uplink commands 10/14/14 THF-15
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Command/Control/Communications
Existing USGS infrastructure Three requirements: High-accuracy position data Low latency Continuous communication GPS to know exactly where both satellites are and the trajectory Fast data transfer to initiate repair mission Comm between robot and command to confirm success throughout repair 10/14/14 THF-15
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Data Flow Diagram 10/14/14 THF-15
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Cost 10/14/14 THF-15
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Non-Recurring Costs Total Non-Recurring Cost ~ $300,000,000 Software
Value Total Lines of Code 40,000 Cost Per Month $16,667 Lines Per Month 111 Total Cost $6,000,126.13 First Flight Unit CER ($K) Cost Drivers X1 Cost THF-15 Bus Y=110.2*X1 X1=Spacecraft 800 $88,160,000 Launch Cost ULA Atlas V 401 $200,000,000 Total Non-Recurring Cost ~ $300,000,000 10/14/14 THF-15
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Recurring Costs Total recurring cost per year ~ $10,000,000 Manpower
Number Salary Number of Years Cost Engineers 50 $140,000 7 $49,000,000 Technicians 25 $105,000 $18,375,000 Total recurring cost per year ~ $10,000,000 10/14/14 THF-15
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Total Cost Total cost ~ $370,000,000 10/14/14 THF-15
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Questions Matt Chapin Nick Wackel Olon Pierce mrchapin@crimson.ua.edu
Olon Pierce 10/14/14 THF-15
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References http://www.nasa.gov http://www.usgs.gov
10/14/14 THF-15
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