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Titan Mariner Spacecraft Study
Titan Team!
IPPW-5
June 24, 2007
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 Ontario235 km X 70 kmOut of Scope for this study
– Carrier spacecraft to Titan
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.
Surface Science Highlights
InstrumentMass (kg)
Power (W) Science Objectives Heritage
Lander
GC - MS 25 40 Sample atmosphere, liquid, shoreline. Determine Methane/Ethane ratio MSL
Camera 4 3 Observe weather systems above probe MER
Accelerometer 1 1 Determine motion of probe Huygens
SONAR 1 1 Profile lake bed, detect precipitation, detect waves Huygens
Spectrometer 2 2Classification of EM radiation environment and atmospheric composition analysis Exomars
Balloon
Camera 4 3 Observe local panoramic region MER
Met. Package 5 2 Observe meteorological conditions at set altitudes (boundary layer)various missions
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
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
Altitude vs Velocity
Titan Atmospheric Entry7 km/s
Backshell separation
Inflatable Aerodynamic Decelerator Deployment & Heatshield Jettison
Liquid Methane Lake
Splash-DownSetting Sail for Land
EDL Sequence of Events
Toe-in Landing into liquid methane
Liquid Methane Lake
Wind
Descent Configuration
10 m/sDescent rate Imaging Platform
MET Instruments
Sea-FaringConfiguration
Descent and Operational Configurations
Titan Zodiac
Inflatable “Zodiac” Boat
RTG
Warm & Sealed Electronics Box
Contains flight system components and science payload (except for imaging platform and MET instruments)
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
Aeroshell Description
Trajectory Geometry Aero/Thermal TPS
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
Mass Equipment ListTitan Mariner Mass Breakdown
Mass (kg) Power (W)Spacecraft Structure
Aeroshell
Heat Shield 68
Back Shield 72
Heat Shield Seperation 3
Back Shield Seperation 4.5
Inflatable Aerodynamic Decelerator 20
Inflation system 15
Boat/Zodiac 10
Inflation system 4
Science Instruments 46.55 61.2
Power Systems (RTG, LiON Battery & power Electronics.)
67 11 110 W, 40 A-hr
Spacecraft Systems 11 102
Spacecraft Structure 150
Entry Mass 471.05 174.2
Payload Mass 323.55 174.2
Possible International Collaboration
• Orbiter already an international effort
• Potential international collaboration with science instruments
Titan Team
Questions?