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7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Hopper-Flow of Lunar Regolith Simulants
in Reduced Gravity and Vacuum

Philipp Reiss, Philipp Hager, Alexander Hoehn
Institute of Astronautics
Technische Universität München
p.reiss@tum.de

05 November 2013
7th Regional Americas Conference of the ISTVS
Tampa, Florida

1
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Scope of the Experiment
Investigating the flowability of lunar regolith simulants
under reduced gravity and vacuum

Background:
Geophysical sampling instruments on Moon
Problem of transporting regolith in feeding systems

Here: Feed hopper

Phoenix ©NASA
SAM ©NASA

?

2

2
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems

Institute of Astronautics
Technische Universität München

05 November 2013 | Tampa, Florida

Flowability Parameters
Sample mass
Sample material

27 to 46 g

JSC-1A / NU-LHT-2M

Ambient pressure
0.07 to 6.10 mbar

Inclination angle of funnel
55 / 60 / 65 / 70 / 75 deg

Gravitation
1.00 / 0.38 / 0.16 g

Outlet width of funnel
8 / 13 / 18 mm

Funnel geometry
Symmetrical / asymmetrical
Pre-consolidation
Wall friction

Electrostatic charge

Vibration

Moisture

3

3
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Experiment Setup

24 hopper configurations

Sample container
(PVC, PC)

Vacuum chamber
4

4
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Experiment Setup

Experiment rack

Vacuum chamber with sample containers during operation

5

5
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems

Institute of Astronautics
Technische Universität München

05 November 2013 | Tampa, Florida

Experiment Overview
2
Lunar regolith simulants

124
Parabolas

13x Mars-g (0.38g)
12x Moon-g (0.16g)

~ 1000
Measurement
s

6x Zero-g (0g)

2-9 repetitions
during each parabola

JSC-1A ©USGS
NU-LHT-2M ©ArnoldReinhold

24
Hopper configurations

6

6
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems

Institute of Astronautics
Technische Universität München

05 November 2013 | Tampa, Florida

Flow Examples
Moon (0.16 g)

Moon (0.16 g)

NU-LHT-2M
60 deg inclination
8 mm outlet

© Philipp Reiss

Mars (0.38 g)

7

7
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Observations during Operation
•

Gas inclusions slow the material flow.

•

Material sticks to the walls of the sample container.

•

Sample volume expands (lower bulk density).

•

Random occurrence of arching and clogging.

•

Material flow lasts longer than one parabola (at Moon-g, ~26 s).

Exemplary
video stills:

8

8
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems

Institute of Astronautics
Technische Universität München

05 November 2013 | Tampa, Florida

Results and Conclusions
1.

Flow rate is proportional to gravity.

2.

Flow rate is proportional to outlet size.

3.

For constant flow rate the outlet size is inversely proportional to the gravity.
Flow rate vs. outlet size
(average and standard deviation)

Flow rate vs. gravity
(average and standard deviation)
3

0.45
JSC-1A

NU-LHT-2M
0.38 g / 1 g

0.3
JSC-1A

NU-LHT-2M

0.2
0.16 g / 1 g

0.15

Scale factor [-]

2.4
18 mm / 8 mm

2.2
2
1.8

13 mm / 8 mm

1.6

0.1

1.4

0.05

JSC-1A

NU-LHT-2M

1.2

0

1

1g
1g

8 mm

0.38 g
0.16 g

8 mm

13 mm
18 mm

© Philipp Reiss

Scale factor [-]

NU-LHT-2M

2.6

0.35

0.25

JSC-1A

2.8

0.4

9

9
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

Results and Conclusions
1.

Flow rate is proportional to gravity.

2.

Flow rate is proportional to outlet size.

3.

For constant flow rate the outlet size is inversely proportional to the gravity.

4.

Arching and clogging occurs randomly.

5.

Higher inclinations tend to lead to higher flow rates.

6.

Good repeatability and high flow rates for configurations with 65 deg, 70 deg, 8 mm, 13 mm.

7.

Best repeatability and moderate flow rate for asymmetrical configurations.

10

10
7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems
05 November 2013 | Tampa, Florida

Institute of Astronautics
Technische Universität München

This work was supported by:
› Project LUISE-2 (DLR grant no. 50JR1210)
› German aerospace agency (DLR)
› European Space Agency (ESA)
› Centre National d'Etudes Spatiales (CNES)
› Novespace
› Kayser-Threde GmbH
› IGEP at Technische Universität Braunschweig
› ILM at Otto von Guericke Universität Magdeburg

Philipp Reiss
Institute of Astronautics
Technische Universität München
p.reiss@tum.de

11

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Hopper-Flow of Lunar Regolith Simulants in Reduced Gravity and Vacuum

  • 1. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Hopper-Flow of Lunar Regolith Simulants in Reduced Gravity and Vacuum Philipp Reiss, Philipp Hager, Alexander Hoehn Institute of Astronautics Technische Universität München p.reiss@tum.de 05 November 2013 7th Regional Americas Conference of the ISTVS Tampa, Florida 1
  • 2. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Scope of the Experiment Investigating the flowability of lunar regolith simulants under reduced gravity and vacuum Background: Geophysical sampling instruments on Moon Problem of transporting regolith in feeding systems Here: Feed hopper Phoenix ©NASA SAM ©NASA ? 2 2
  • 3. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems Institute of Astronautics Technische Universität München 05 November 2013 | Tampa, Florida Flowability Parameters Sample mass Sample material 27 to 46 g JSC-1A / NU-LHT-2M Ambient pressure 0.07 to 6.10 mbar Inclination angle of funnel 55 / 60 / 65 / 70 / 75 deg Gravitation 1.00 / 0.38 / 0.16 g Outlet width of funnel 8 / 13 / 18 mm Funnel geometry Symmetrical / asymmetrical Pre-consolidation Wall friction Electrostatic charge Vibration Moisture 3 3
  • 4. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Experiment Setup 24 hopper configurations Sample container (PVC, PC) Vacuum chamber 4 4
  • 5. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Experiment Setup Experiment rack Vacuum chamber with sample containers during operation 5 5
  • 6. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems Institute of Astronautics Technische Universität München 05 November 2013 | Tampa, Florida Experiment Overview 2 Lunar regolith simulants 124 Parabolas 13x Mars-g (0.38g) 12x Moon-g (0.16g) ~ 1000 Measurement s 6x Zero-g (0g) 2-9 repetitions during each parabola JSC-1A ©USGS NU-LHT-2M ©ArnoldReinhold 24 Hopper configurations 6 6
  • 7. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems Institute of Astronautics Technische Universität München 05 November 2013 | Tampa, Florida Flow Examples Moon (0.16 g) Moon (0.16 g) NU-LHT-2M 60 deg inclination 8 mm outlet © Philipp Reiss Mars (0.38 g) 7 7
  • 8. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Observations during Operation • Gas inclusions slow the material flow. • Material sticks to the walls of the sample container. • Sample volume expands (lower bulk density). • Random occurrence of arching and clogging. • Material flow lasts longer than one parabola (at Moon-g, ~26 s). Exemplary video stills: 8 8
  • 9. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems Institute of Astronautics Technische Universität München 05 November 2013 | Tampa, Florida Results and Conclusions 1. Flow rate is proportional to gravity. 2. Flow rate is proportional to outlet size. 3. For constant flow rate the outlet size is inversely proportional to the gravity. Flow rate vs. outlet size (average and standard deviation) Flow rate vs. gravity (average and standard deviation) 3 0.45 JSC-1A NU-LHT-2M 0.38 g / 1 g 0.3 JSC-1A NU-LHT-2M 0.2 0.16 g / 1 g 0.15 Scale factor [-] 2.4 18 mm / 8 mm 2.2 2 1.8 13 mm / 8 mm 1.6 0.1 1.4 0.05 JSC-1A NU-LHT-2M 1.2 0 1 1g 1g 8 mm 0.38 g 0.16 g 8 mm 13 mm 18 mm © Philipp Reiss Scale factor [-] NU-LHT-2M 2.6 0.35 0.25 JSC-1A 2.8 0.4 9 9
  • 10. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München Results and Conclusions 1. Flow rate is proportional to gravity. 2. Flow rate is proportional to outlet size. 3. For constant flow rate the outlet size is inversely proportional to the gravity. 4. Arching and clogging occurs randomly. 5. Higher inclinations tend to lead to higher flow rates. 6. Good repeatability and high flow rates for configurations with 65 deg, 70 deg, 8 mm, 13 mm. 7. Best repeatability and moderate flow rate for asymmetrical configurations. 10 10
  • 11. 7th Regional Americas Conference of the International Society for Terrain-Vehicle Systems 05 November 2013 | Tampa, Florida Institute of Astronautics Technische Universität München This work was supported by: › Project LUISE-2 (DLR grant no. 50JR1210) › German aerospace agency (DLR) › European Space Agency (ESA) › Centre National d'Etudes Spatiales (CNES) › Novespace › Kayser-Threde GmbH › IGEP at Technische Universität Braunschweig › ILM at Otto von Guericke Universität Magdeburg Philipp Reiss Institute of Astronautics Technische Universität München p.reiss@tum.de 11