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  • Deorbitation of small CNES satellites

    Paper number

    IAC-05-B6.3.02

    Author

    Mr. Pierre W. Bousquet, Centre National d'Etudes Spatiales (CNES), France

    Year

    2005

    Abstract
    P. W. BOUSQUET, G. BLANC, D. DILHAN, Ch. DUPUY, J. FOLIARD, Ph. GAMET, P. PELIPENKO, N. PILLET, B. POUILLOUX, P. PRIEUR   All co-authors from CNES
    
    CNES decided formally in October 2004 to apply a Code of Conduct originally drawn up by the main European space agencies earlier that year. It contains basic rules to be applied in space in order to limit the increase of orbital debris. In low earth orbit, the rule is to limit in-orbit lifetime to 25 years after the end of the operational mission, or else to transfer to a graveyard orbit above 2000 Km.
    In order to follow these instructions, we are currently investigating how to implement them on our MYRIADE family of micro-spacecrafts, which are commonly launched in circular orbits between 600 and 800 Km altitude. At those altitudes, the most efficient approach is to aim for time constrained re-entry. Mono-hydrazine propulsion is available as an option on Myriade, and is implemented if required by the mission. In that situation, fuel reserves may (on a case by case basis) be adequate to lower the orbit appropriately. In other cases, the design of the spacecraft must somehow be adapted.
    A task force has been set-up, and this article will present the outcome of its research. The mass range of the satellites investigated goes from 120 Kg (standard Myriad platform) to 200 Kg (Microscope mission for 2008). After a preliminary assessment of the requirements, two strategies have been short-listed:
    
    - propulsive manoeuvre at the end of the mission, to decrease the orbit. Various technologies are considered (chemical propulsion, cold gas, solid propulsion, electrical propulsion),
    
    - deployment of large - lightweight - surfaces to increase dramatically the ballistic coefficient of the spacecraft and enable a “fast” re-entry through high drag forces. The most promising technology here is based on inflatable structures.
    
    After a presentation of the mission analysis results that will establish the Delta V requirement for the propulsive solutions, and the surface requirements for the high drag option, we will present the main characteristics of the candidate systems and the criteria that were used to establish the trade-off. The system impact and the generic potential are significant considerations. At the time of writing, the choice is still being debated. The outcome is planned for April 2005 and the selected system will be presented in detail at the conference.
    
    The contents of this paper correspond to an activity currently running at CNES. The solution elaborated through this work should be implemented in the near future on our micro-satellites. These results have not previously been presented at a conference. 
    The participation of the main author in the 2005 IAC has been budgeted by CNES.
    
    Abstract document

    IAC-05-B6.3.02.pdf

    Manuscript document

    IAC-05-B6.3.02.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.