Nebula Public Library

The knowledge bank of ESA’s R&D programmes

Format: 2023
Format: 2023
Format: 2023

83 results found
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ESA's Space Safety Programme contains a cornerstone quot;Collision Risk Estimation and Automated Mitigation (CREAM)quot;. CREAM addresses the development of technologies for automating collision avoidance.
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Germany

GSTP

GT17-413SD

Airbus Defence and Space GmbH

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Environment prediction models (like MASTER) are by no means static and require continuous improvements to keep the pace with an ever-changing highly dynamic space debris environment. New types of measurements (as, e.g., from potential in-situ sensors), newly discovered debris sources (as the release of MLI foils), and additional severe debris generating events (like the Chinese ASAT test of January 2007 and the Iridium-33/Cosmos-2251 collision in 2009) need to be reflected.

Germany

GSTP

G61C-025GR

TECHN UNIV BRAUNSCHWEIG

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Uncertainties on atmospheric densities and temperatures are major risk drivers for atmospheric entry and orbital maneuvers such as aerobraking or aerocapture. The EnVision mission scenario foresees orbit perigee lowering down to about 140km using aerobraking. Europe has gained a good expertise during the Venus Express mission, however there is no easily accessible model not to say engineering model to rely on for mission design at Venus.

France

TDE

T204-129EP

CNRS

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All missions in Earth-bound orbits rely on space debris and meteoroid flux models. These models are used to assess the mission risk and design shielding concepts (for manned modules). The flux predictions have been found to have a remarkable sizing effect. Collision break-ups are the major source of debris >1mm and are poorly understood. This needs to be improved significantly.
On Agency level, collision break-up modelling is decisive to define the Agency's position towards international agreements on space debris mitigation. Current models will be misleading.

Italy

TDE

T711-603SD

SPACEDYS S.R.L. SPACE DYNAMICS SERVICES S.R.L.

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Space Based Solar Power concepts promise the generation of large amounts of renewable power by launching vast Solar Power Satellites (SPS) into space and beaming the power back to rectennas on Earth. Due to diffraction physics, large scale arrays delivering 2GW of power to the ground will be of the order of a kilometre in length and have masses of between 2,000 and 10,000 tonnes.

United Kingdom

Discovery

21-D-S-TEC-01-b

FRAZER NASH CONSULTANCY LTD

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The activity investigated a novel hybrid magnetic shielding system that uses both passive and active cancelation. The design and simulations used, along with the characterisation and measurements taken on the optimised system, are summarised in the executive summary report, and described in more detail in the Final Report. This activity was divided in two main work packages: study of optimisation and magnetic shield prototype.

United Kingdom

Discovery

S 2021-05-b

RAL (Rutherford Appleton Laboratory)

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Ireland

GSTP

GT17-137TIaw

Xerotech Ltd

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This activity shall develop a Payload Interface Data Handling Unit (PIDHU) for SWE hosted payloads which shall provide power supplies at various voltages required by space weather/environment instruments limiting the mass required for individual instrument voltage transformers. The PIDHU shall receive data streams from instruments through various protocols including UART (RS-422/485), SpaceWire, MIL-STD-1553 and CAN Bus and provide data though a single data interface adaptable to hosting spacecraft requirements.

Finland

GSTP

GT18-001ED

RUAG SPACE FINLAND OY AB

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France

TDE

T711-604SY

THALES ALENIA SPACE FRANCE

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When Europe still had no access to clarify the attitude of lost spacecrafts in order to optimize recovery attempts and improve re-entry predictions, the precursor GSTP study on ?Attitude Motion Measurements and Modelling? activity paved the way for an independent European capacity in this field. In fact, for the first time in Europe, it was possible to join measurements of SLR, passive telescope and synthetic aperture radar to fit a dynamic attitude model of the given spacecraft.

Switzerland

GSTP

GT17-152GR

University of Bern

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