ZBO:
R&D challenge
for CNES space studies

ZBO:
CNES R&D challenge
for reuse of the upper stage

Development of a cryogenic propellant depot to improve the sustainability of space operations.

Development of a cryogenic propellant depot
to improve the sustainability
of space operations.

CNES R&D Challenge

CNES R&D Challenge

produits_ligne_30
produits_ligne_20

Over the past year, Absolut System has been working on the development of a cryogenic propellant depot, as part of the CNES R&D Challenge for the reuse of the upper stage.

The use of depots and on-orbit refueling are essential for long-term lunar and Mars missions, as they enable multiple launch missions and reusable tugs in space. The use of smaller depots and refueling missions targeting more specific orbits could also help improve the sustainability of space operations.

The objective: to design a system capable of storing and transferring cryogenic propellants in orbit, with a view to being launched (filled) as a payload on a possible evolution of the Ariane launcher.

This development included an in-depth analysis of mission scenarios. Our cryogenic expertise was used for thermal modeling to optimize the ZBO (zero-boil off) system and to model the cryogenic propellant transfer process in microgravity.

Cryogenic innovations have long been essential to the space industry for a variety of applications: imaging, propulsion, etc.

For missions in a geostationary orbit, following a rendezvous in a geostationary transfer orbit (GTO), the launcher can deliver cryogenic propellants to a reusable fuel tug, which will then transport them to GEO to refuel satellites.

The system has been designed for two configurations: LOX/LCH4 and LAr. These were chosen for their compatibility with future Mars missions and their likelihood of use in future systems. However, these cryogenic propellants present several additional challenges which Absolut System will address in further studies:

Detailed study

Detailed study

produits_ligne_10
produits_ligne_20

Two main scenarios were selected for this engineering study carried out by the space design office:

For the first scenario of SSO missions, Absolut System assumed that the debris collectors would refuel from a large SSO depot. Calculations showed that it was particularly advantageous to place small depots in specific orbits located close to the regions where debris is concentrated, in order to minimize the mass of propellant required for orbital maneuvering by the collectors.

CNES R&D Challenge

CNES R&D Challenge

produits_ligne_20
produits_ligne_30
produits_ligne_20

Over the past year, Absolut System has been working on the development of a cryogenic propellant depot, as part of the CNES R&D Challenge for the reuse of the upper stage.

The use of depots and on-orbit refueling are essential for long-term lunar and Mars missions, as they enable multiple launch missions and reusable tugs in space. The use of smaller depots and refueling missions targeting more specific orbits could also help improve the sustainability of space operations.

The objective: to design a system capable of storing and transferring cryogenic propellants in orbit, with a view to being launched (filled) as a payload on a possible evolution of the Ariane launcher.

This development included an in-depth analysis of mission scenarios. Our cryogenic expertise was used for thermal modeling to optimize the ZBO (zero-boil off) system and to model the cryogenic propellant transfer process in microgravity.

Cryogenic innovations have long been essential to the space industry for a wide range of applications: imaging, propulsion, etc.

Detailed study

Detailed study

produits_ligne_20
produits_ligne_10

Two main scenarios were selected for the engineering study carried out by the space design office:

For the first scenario of SSO missions, Absolut System assumed that the debris collectors would refuel from a large SSO depot. Calculations showed that it was particularly advantageous to place small depots in specific orbits located close to the regions where debris is concentrated, in order to minimize the mass of propellant required for orbital maneuvering by the collectors.

For missions in geostationary orbit, following a rendezvous in geostationary transfer orbit (GTO), the launcher can deliver cryogenic propellants to a reusable fuel tug, which will then transport them to GEO to refuel the satellites.

The system has been designed for two configurations: LOX/LCH4 and LAr. These were chosen for their compatibility with future Mars missions and their likelihood of use in future systems. However, these cryogenic propellants present several additional challenges which Absolut System will address in further studies:

Absolut System is working to meet the challenges posed by the use of cryogenic propellants in a microgravity environment, to achieve ZBO (zero boil-off) long-term storage and vent-free filling during the refueling process.

Absolut System is working to meet the challenges posed by the use of cryogenic propellants in a microgravity environment, to achieve ZBO (zero boil-off) long-term storage and vent-free filling during the refueling process.