1. Matt Chapin, Nick Wackel, Olon Pierce Preliminary Design Review THF-15

2. 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

3. 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

4. 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

5. 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

6. Mission Objectives Intercept Landsat 8 Deploy repair robot
Install new TIRS
Detach and enter parking orbit
10/14/14
THF-15

7. Critical System Drivers
In order of importance
10/14/14
THF-15

8. 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

9. Schedule Existing TIRS will expire in early 2016
Goal of initial operating capability within two years
10/14/14
THF-15

10. 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

11. 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

12. Mission Design
10/14/14
THF-15

13. 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

14. 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

15. 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

16. 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

17. Physical Craft
10/14/14
THF-15

18. 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

19. 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

20. Will launch with Atlas V 401 based on launch requirements and reliability
10/14/14
THF-15

21. 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

22. 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

23. Houses mission payload, propulsion system, and communications structure
10/14/14
THF-15

24. Ground Systems
10/14/14
THF-15

25. 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

26. 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

27. 10/14/14
THF-15

28. 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

29. Data Flow Diagram
10/14/14
THF-15

30. Cost
10/14/14
THF-15

31. 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

32. 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

33. Total Cost
Total cost ~ $370,000,000
10/14/14
THF-15

34. Questions Matt Chapin Nick Wackel Olon Pierce mrchapin@crimson.ua.edu
Olon Pierce
10/14/14
THF-15

35. References http://www.nasa.gov http://www.usgs.gov
10/14/14
THF-15