FP7/SPACE: Activity 9.2.1 Strengthening of Space foundations / Research to support space science and exploration - SPA.2009.2.1.01The research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under grant agreement n 241992

LANDING GEAR DEPARTMENTLANDING GEAR DEPARTMENT

Centro Italiano Ricerche Aerospaziali, Italy

CFS Engineering, Switzerland

NCSR Demokritos, Greece

ASTRIUM-ST SAS, Coordinator, France

CNRS/EM2C, France

Institute of Aviation, Poland

KYBERTEC, Czech Rep.

Lomonosov Moscow State University, Russia

Office National d’Etudes et de Recherches Aérospatiales, France

Von Karman Institute for Fluid Dynamics, Belgium

Main characteristics of a ballistic Earth re-entry.Effective max. total heat flux is about 11.6MW/m2, max. velocity 12.3km/sec (47.5Mach), total heat energy about

250MJ/m2.

Challenges:The main challenges faced by a ballistic, Sample-Return

Vehicle are:

1.Ensure the entry phase of the ballistic trajectory and sustain the thermal and aerodynamical loads encountered during the entry until impact.

2. Protect the payload from heat and mechanical loads throughout the re-entry until impact on the ground

3. Comply with the planetary requirements, typically ensure sample container integrity until impact and guarantee sealing conditions at any time of the mission and under any circumstances.

Concept:Ballistic, passive return of a soil sample from another planetary body in a Sample-

Return Capsule, entering and aero-braking through the Earth’s atmosphere at high velocity.

http://www.rastas-spear.eu/

Time [s]

HeatF

lux

[kW

/m2]

Mach

Velo

city

[m/s

]

Alti

tude

[km

]

0 10 20 30 40 50 600

2000

4000

6000

8000

10000

12000

14000

16000

10

20

30

40

50

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

0

20

40

60

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100

120

ConvectiveRadiativetotalMachVelocityZ

12300m/s

32.31

45.7

V=12300m/sZ=90.08km

11600kW/m2

V=10891m/sZ=57.48kmM=33.648832kW/m2

2932kW/m2

FP7/SPACE/2419921/9/2011 – 30/10/2011Total Budget: 2.3M€

Objective:“To increase Europe’s knowledge in high

speed re-entry vehicle technology to allow for planetary exploration missions

in the coming decades”

The specific Objectives are:

1.To better understand phenomena during high speed re-entry enabling more precise Capsule sizing and reduced margins.

2.To identify the ground facility needs for simulation

3.To master heat shield manufacturing techniques and demonstrate heat shield capabilities

4.To master damping at ground impact and flight mechanics and thus ensure a safe return of the samples

The PARTNERS:

CONCEPT OF A SAMPLE-RETURN VEHICLE FOR BALLISTIC EARTH RE-ENTRY

IF Carrier

Filling Foam

FS Structure

FS TPS

Lid TPS

Front Energy absorbing material

Rear Energy absorbing material

Lid structure

Internal insulation

Internal structure

Sample Canister

AFT TPS

WP1Review of System

Requirements

1.1 Atmosphere modelling

1.2 Trajectories

1.3 Aerodynamics & ATD

1.4 Vehicle Design

WP3Key Technologies for

High Speed Entry

3.1: Choice of TPS + Joints

3.2: Flow tests

3.3: Breadboard manufacturing

3.4: Crushable Structure

WP4Ablation- Flight Mechanics

Coupling assessment

4.1 Tools coupling

4.2 Ablation coupling assessment4.3 Engineering modellingCorrection by CFD

WP5Gas-Surface Interactions

Modelling

5.1: Review of surface roughness and blowing influence

5.2: Ground Experiment Preparation

5.3: CFD Modelling

5.4: Synthesis of WP

WP2Ground Facilities

Improvement

2.1: Analysis of Current Ground Facilities

2.2: Shock tube technology

2.3: Ballistic Range Technology2.4: Plasma Generator Technology

WP

6M

ana

gem

ent

, Dis

sem

inat

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an

d E

xplo

itatio

n

6.1

Man

agem

ent

6.2

Dis

sem

inat

ion

& E

xplo

itatio

n

2.5: Synthesis

The Work Plan

Radiation-Shapes-Thermal Protection Investigations

for High Speed Earth Re-entry