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13 results found
OMAR – On orbit manufactured spacecraft

The objective of this activity is to assess the system level and design impacts of optimising a satellite design for on-orbit manufacturing and assembly, as well as preparing it to be refurbished, reused or recycled on orbit afterwards, and to identify the technologies needed.

Italy

19-D-S-TEC-05

Thales Alenia Space
Mars Surface Platform Capabilities

The objective of this study was to help define how to maintain and further develop European access to the surface of Mars, the major destination for European exploration, following the most recent approved and developed (or currently in development) missions (ExoMars 2016, ExoMars RSP).

Italy

20-P-M-HRE-01-a

Thales Alenia Space
Small Satellite Missions to Mars – S2M2

The focus of this study was the system-level assessment of potential small mission architectures that could operate at Mars in the 2030s, after or potentially in parallel with MSR mission.

In particular two cases were evaluated:

  • Mission 1: Mars Communications Constellation (MCC), for supporting assets on the surface and providing science
  • Mission 2: Mars Science Orbiter (MSO), a science-driven mission, remote sensing
Italy

20-P-M-HRE-02-b

Thales Alenia Space
Lunar ISRU Demonstration Mission Definition Study Segment 2

The study and exploitation of In Situ Resource Utilisation (ISRU) technologies (with an initial focus on the Moon) are stimulating an increasing interest in the international community, both at Agency and industry levels, in view of and in preparation for future crewed exploration missions and in terms of scientific and societal long-term benefits.

Italy

18_M-HRE-1E

Thales Alenia Space
Clean Sat technology assessment and concurrent engineering in support of LEO platform evolutions

In this activity, LSI's Airbus, OHB and Thales Alenia Space evaluated CleanSat technologies.

Italy

15/M61-c

Thales Alenia Space
M4 Phase A/B1 XIPE PHASE A

XIPE is designed to be launched with a VEGA-C vehicle into an orbit of 550 km and <6° inclination. With this orbit, eclipses last about 35 minutes. Due to remaining spacecraft fragments the mission is planned to end by controlled re-entry. The baseline ground station is Kourou either for S/S or S/X telemetry band, albeit Malindi (or Singapore) is additionally available, if necessary, for additional downloading capability in case of particularly bright sources. The mission duration is 3+2 years.

Italy

15/M23-a-2

Thales Alenia Space
Design for Removal: How to design S/C to support active debris removal if uncontrolled

In the future, satellites will have to demonstrate compliance with debris mitigation requirements, covering re-entry or parking graveyard orbits and passivation. Nevertheless, during the mission, a failure could occur without any possibility to manoeuvre the satellite and achieving its compliance to the Space Debris Mitigation requirements. Therefore to anticipate the need to use ADR for deorbiting (or reorbiting) the satellite, it is interesting to evaluate the implication of adapting the satellites and launcher upper stage to support a future ADR mission.

Italy

15/705-b

Thales Alenia Space
Atom Interferometry Test of the Weak Equivalence Principle in Space parallel studies

The purpose of the “Atom Interferometry Test of the Weak Equivalence Principle in Space” study was to conceive and specify an instrument for an atom interferometry test of the Weak Equivalence Principle (Quantum WEP test, QWEP), focusing on the International Space Station (ISS) as space platform.

Italy

2012-16

Thales Alenia Space
Universal parts Fabricator-Replicator for Space Applications
Italy

2010-19

Thales Alenia Space
Universal parts Fabricator-Replicator for Space Applications
Italy

2010-45

Thales Alenia Space

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