Design and Operations of a Multi-Satellite System for the Cross-Scale Mission Concept
- Paper number
IAC-07-C1.5.05
- Author
Ms. Stefania Cornara, DEIMOS Space S.L., Spain
- Coauthor
Mr. Juan-Carlos Bastante, DEIMOS Space, Spain
- Coauthor
Mr. Franck Jubineau, Thales Alenia Space, France
- Year
2007
- Abstract
The Technology Reference Studies have been introduced in the ESA Science Directorate to focus on the development of strategically important technologies that are of likely relevance to potential future science missions. This is accomplished through the study of technologically demanding and scientifically meaningful mission concepts. In this context, the “ Cross-Scale Technology Reference Study (CS TRS)” has the primary aim to identify and analyse a mission concept for the investigation of fundamental space plasma processes that involve dynamical non-linear coupling across multiple length scales.
To fulfil the CS scientific objectives, a constellation of spacecraft is required, flying in loose formation around the Earth and sampling three characteristic plasma scale distances simultaneously: electron kinetic ( 10 km), ion kinetic ( 1000 km), magnetospheric fluid ( 6000 km). A constellation configuration with 10 spacecraft has been designed and analysed in details: this configuration comprises a mother-daughter system on the small scale located in the centre of two nested tetrahedrons on the medium and large scales.
This multi-satellite system shall be built-up and maintained with respect to a reference mission orbit. Near-equatorial highly elliptical orbits with apogee of 25 Earth radii and a range of perigees between low altitudes and 10 Earth radii have been analysed, since they cross the bow-shock region, the magnetosheath and visit the magnetotail each year. Periodic reconfiguration manoeuvres are envisaged during the operational lifetime to modify the spacecraft scale distances at intervals of few months up to one year.
The key CS mission drivers identified are the transfer and deployment strategy, the number of S/C, the S/C and payload design philosophy, as well as the mission operations.
The transfer and deployment scenario is based on a single launch with a Soyuz-Fregat 2-1b by means of a dispenser-like transfer vehicle that brings 10 S/C to the operational orbit where they will be deployed. A common transfer of the satellites optimises the overall S/C mass and volume, and allows reduced mission operations complexity compared to individual transfer to the target orbit. The mass and number of science spacecraft can be traded against the propellant mass for operational orbit acquisition and for formation deployment, reconfiguration and maintenance.
For cost-efficiency, simple identical spinning S/C have been baselined with a platform dry mass of 100 kg, which can accommodate 10–40 kg of payload.
Last but not least, operational streamlining and effective communications architecture are paramount to handle such a considerable number of spacecraft and instruments. In particular, the volume of data collected and the ground delivery intervals are driving factors to determine the S/C on-board mass memory and to define the necessary data transmission rate. Inter-spacecraft localization/synchronization is another key element to achieve the required timing and distance accuracy.
This paper presents a comprehensive overview of the system design and mission operations for the CS concept, and outlines a technically feasible mission architecture for a multi-dimensional investigation of space plasma phenomena.
- Abstract document
- Manuscript document
IAC-07-C1.5.05.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.