1. Titan Mariner Spacecraft Study Titan Team! IPPW-5 June 24, 2007

2. Introduction Assumptions –An orbiter is in place at Titan in an orbit to provide telecom relay Planned Titan flagship orbiter would meet this requirement UHF telecom –Lander would be additive to rather than redundant with the planned Titan flagship lander and balloon –Landing near the southern pole in Titan summer (2030) –Lacus Ontario is predominately liquid methane Mission Overview –Titan liquid lander with a tethered balloon for meteorology and imaging –Target Launch Date: 2023 –Target Landing Site: Lacus Ontario in Southern Hemisphere Lacus Ontario 235 km X 70 km Out of Scope for this study –Carrier spacecraft to Titan

3. Science Objective Determine the composition of the volatiles and condensates in the atmosphere and at the surface including hydrocarbons and nitriles, on a regional scale, in order to understand the hydrocarbon cycle. Determine the climatological and meteorological variations of temperature, clouds and winds. Determine the depth of any liquid body, its electrical conductivity, sedimentation and composition.

4. Surface Science Highlights Instrument Mass (kg) Powe r (W)Science ObjectivesHeritage Lander GC - MS2540Sample atmosphere, liquid, shoreline. Determine Methane/Ethane ratioMSL Camera43Observe weather systems above probeMER Accelerometer11Determine motion of probeHuygens SONAR11Profile lake bed, detect precipitation, detect wavesHuygens Spectrometer22 Classification of EM radiation environment and atmospheric composition analysisExomars Balloon Camera43Observe local panoramic regionMER Met. Package52Observe meteorological conditions at set altitudes (boundary layer) various missions

5. Mission Architecture Titan Approach: Direct Communications: –Relay during EDL events (using orbiter) –Relay every 5 hrs during surface ops (using orbiter) Entry Configuration –45 deg sphere cone with 2.5 m diameter Entry Sequence –Backshell sep:2 km altitude (drogue chute) –Balloon reel out:BS + 5 sec (100 m tether) –H.S. sep:reel out + 20 sec –Zodiac Inflation:H.S. sep + 5 sec Surface Configuration –Floating structure –Balloon used for propulsion

6. Entry Trajectory Parameters Entry Velocity:7 km/s Entry FPA:-60 deg Peak Heat Flux:80 W/cm^2 Heat Load:3.6 kJ/cm^2 Peak g’s:15 g’s Entry to Splashdown:1.3 hours

7. Altitude vs Velocity

8. Titan Atmospheric Entry 7 km/s Backshell separation Inflatable Aerodynamic Decelerator Deployment & Heatshield Jettison Liquid Methane Lake Splash-Down Setting Sail for Land EDL Sequence of Events

9. Toe-in Landing into liquid methane Liquid Methane Lake Wind Descent Configuration 10 m/s Descent rate Imaging Platform MET Instruments Sea-Faring Configuration Descent and Operational Configurations

10. Titan Zodiac Inflatable “Zodiac” Boat RTG Warm & Sealed Electronics Box Contains flight system components and science payload (except for imaging platform and MET instruments)

11. System Control Requirements No prop system Deploying the inflatable aerodynamic decelerator deployment –IMU/G-switch activation Passive Terminal Descent –Surface imaging during descent Liquid impact at 10 m/s

12. Aeroshell Description TrajectoryGeometryAero/ThermalTPS Entry Angle -60deg Shape Blunt nosed 45deg sphere cone Ballistic Coefficient 97 kg/m^2 Material Norcoat Liege, Phenolic Cork Entry Velocity 7km/s Aft shape Hemisphere Stagnation Heating Rate 80W/cm^2 Material Density 460 kg/m^3 Control Method Ballistic Diameter 2.5m Integrated Heat Load ~3600J/cm^2 Thickness 1.6 cm

13. Mass Equipment List

14. Possible International Collaboration Orbiter already an international effort Potential international collaboration with science instruments

15. Titan Team Questions?