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
80
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
ion
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
