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?