Abstract
Active Debris Removal (ADR) aims at removing large sized intact objects ― defunct satellites, rocket upper-stages ― from space crowded regions. Why? Because they constitute the main source of the long-term debris environment deterioration caused by possible future collisions with fragments and worse still with other intact but uncontrolled objects. In order to limit the growth of the orbital debris population in the future (referred to as the Kessler syndrome), it is now highly recommended to carry out such ADR missions, together with the mitigation measures already adopted by national agencies (such as postmission disposal). At the French Space Agency, CNES, and in the frame of advanced studies, the design of such an ADR mission in Low Earth Orbit (LEO) is under evaluation. A two-step preliminary approach has been envisaged. First, a reconnaissance mission based on a small demonstrator (∼500 kg) rendezvousing with several targets (observation and in-flight qualification testing). Secondly, an ADR mission based on a larger vehicle (inherited from the Orbital Transfer Vehicle (OTV) concept) being able to capture and deorbit several preselected targets by attaching a propulsive kit to these targets. This paper presents a flight dynamics level tradeoff analysis between different vehicle and mission concepts as well as target disposal options. The delta-velocity, times, and masses required to transfer, rendezvous with targets and deorbit are assessed for some propelled systems and propellant less options. Total mass budgets are then derived for two end-to-end study cases corresponding to the reconnaissance and ADR missions mentioned above.
Highlights
1.1 Study ContextThis paper presents a §ight dynamics study which has been carried out in the frame of the OTV study at CNES
The task is not fully completed but some results are presented in order to illustrate how the ADR mission design is linked to the vehicle design showing, for example, the dependence between vehicle propulsion system and removal mission strategy
As the con¦dence grew on the prediction models and more simulation were performed taken into account re¦ned assumptions, it became even clearer that the adopted mitigation measures will not be su©cient to stabilize the debris population and the need for ADR emerged as the only way to answer to this issue
Summary
This paper presents a §ight dynamics study which has been carried out in the frame of the OTV study at CNES. The Automated Transfer Vehicle ¤Jules Verne¥ March 9, 2008, launch demonstrated the ability of Ariane to place 20 t in LEO. This was the starting point for the general study to list the dierent missions that an OTV may accomplish. The task is not fully completed but some results are presented in order to illustrate how the ADR mission design is linked to the vehicle design showing, for example, the dependence between vehicle propulsion system and removal mission strategy
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