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Mission type Microgravity research
Operator ESA
COSPAR ID 2005-005C
SATCAT no. 28544
Spacecraft properties
Manufacturer NLR/Rafael
Launch mass 129 kilograms (284 lb)
Start of mission
Launch date 12 February 2005, 21:03:01 (2005-02-12UTC21:03:01Z) UTC
Rocket Ariane 5ECA
Launch site Kourou ELA-3
Contractor Arianespace
Orbital parameters
Reference system Geocentric
Regime Geosynchronous transfer
Perigee 266 kilometres (165 mi)
Apogee 35,726 kilometres (22,199 mi)
Inclination 6.7 degrees
Period 631.19 minutes
Epoch 14 April 2005[2]

SLOSHSAT-FLEVO (Sloshsat Facility for Liquid Experimentation and Verification in Orbit) is a microsatellite launched to investigate the dynamics of fluids in microgravity. FLEVO stands for Facility for Liquid Experimentation and Verification in Orbit. Multiple sensors were used to monitor the behavior of water in an instrumented tank and how sloshing affects the attitude control of launchers and space vehicles.[1]

The project is a joint program between ESA, the Netherlands Agency for Aerospace Programmes, and the Israel Space Agency.[3] The primary contractor is the National Aerospace Laboratory providing the spacecraft structure and power systems. The ejection system and ground support equipment were contracted by NEWTEC. The ISA was responsible for supplying the sub-propulsion system which was built and assembled by Rafael.


The spacecraft itself is a 90-cm cube microsatellite covered by solar cells and fitted with 12 small thrusters.


Originally Sloshsat-FLEVO was to be launched from the Space Shuttle and use the shuttle as a data relay, but after the Space Shuttle Columbia disaster the satellite was modified to be launched on board the Ariene qualification flight.[4] The satellite was launched from the Guiana Space Centre launch site at Kourou, French Guiana on 12 February 2005.


The SLOSHSAT-FLEVO is the first satellite entirely dedicated to liquid research in space. The satellite was equipped with an 87-litre cylindrical tank containing 33.5 litres of de-ionised water. 270 sensors were placed on the tank's walls to measure the sloshing behavior by calculating the thickness of the water. Three accelerometers and a fibre-optic gyroscope were used to measure the motion of the spacecraft. An array of temperature, pressure and fluid velocity sensors were also installed on the craft.[1][3]

After depletion of the propellants and completion of the experiment, the satellite was turned off. ESA estimate that without active debris removal the orbit would decay by 2335.


  1. ^ a b c "Sloshsat FLEVO". ESA. Archived from the original on March 18, 2005. Retrieved 20 November 2013.
  2. ^ McDowell, Jonathan. "Satellite Catalog". Jonathan's Space Page. Retrieved 20 November 2013.
  3. ^ a b "SLOSHSAT". The Israel Space Agency. Retrieved 20 November 2013.
  4. ^ "Sloshsat-FLEVO".

External Links

  • Shimshon Adler, Abraham Warshavsky, and Arie Peretz. "Low-Cost Cold-Gas Reaction Control System for the Sloshsat FLEVO Small Satellite", Journal of Spacecraft and Rockets, Vol. 42, No. 2 (2005), pp. 345-351.

See also

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