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Simplified models for spacecraft vulnerability assessments in early design phase

All spacecraft in Earth orbit are exposed to the risk of impact with Micrometeoroids and Orbital Debris (M/OD). Because of the large collision velocities, Hypervelocity Impacts (HVI) with M/OD may cause significant damage to various subsystems and components up to mission failure.

France

12-601-A

Airbus Defence &...
Assessment of Satellite Constellations for Monitoring the Variations in Earth Gravity Field “SC4MGV”

The overall objective of this study is to assess constellations of two pairs of satellites for the retrieval of time-variable gravity field information for best quality scientific monitoring of mass distribution and transport in the Earth system. Before embarking on this study the geodetic community and space agencies have come to realize that weaknesses in current single-pair gravimetric satellite missions such as GRACE or GRACE-FO (to be launched in 2017) would significantly be alleviated by having a second GRACE-type pair in space simultaneously.

Germany

12.708

UNIV STUTTGART
Weak GNSS Signal Navigation on the Moon

Global Navigation Satellite Systems (GNSS) are already used in space missions (e.g. GOCE, Swarm, Sentinel, and MetOp, among others), not only as a navigation sensor (either for autonomous orbit and attitude determination or for relative navigation) but also as a science instrument (e.g. for altimetry, global geodesy, Radio Occultation and GNSS Reflectometry applications). However, its use is usually limited to orbits or mission phases below the orbits of GNSS satellites, since GNSS satellite antennas transmit mainly in the Earth's direction.

Portugal

13-071

Deimos
Simplified models for spacecraft vulnerability assessments in early design phase

The space debris environment poses an ever-increasing risk to spacecraft particularly in low Earth orbits (LEO). Due to limitations of existing vulnerability models, increasing the overall survivability of a spacecraft by enhancing the protection of sensitive parts was not possible in the past. The aim of this study was to adopt and develop methodologies that allow increasing the survivability of a spacecraft by varying individual parameters, e.g. the position of sensitive components or the thickness of component casings.

Germany

30

Fraunhofer Gesellschaft

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