As control precision for Earth-orbiting formations increases, the required Δ V can quickly become infeasible. Missions have demonstrated approximately 5    m / s / yr for 10-m control (TanDEM-X), but that quickly grows to approximately 90    m / s / yr for 1.5-m control (CanX-4/5). Previous research has shown that formation reference trajectories must use high-fidelity relative orbital dynamics; otherwise, Δ V is spent rejecting modeling errors. However, even with a perfect reference trajectory, feeding back relative state estimation errors can drive Δ V . This paper presents a linear time-invariant analysis approach that quantifies the three-way trade-off between mission Δ V , control precision, and estimation error for approximately circular orbits and verifies the approach through high-fidelity simulations, including tracking an ideal reference trajectory that eliminates the Δ V cost of modeling errors. Because Linear Quadratic Regulator control is used, the resulting Δ V can be considered a lower bound on the required Δ V , assuming linear control and quadratic cost. Using reference trajectories based on simplified dynamics, such as without differential J2, would only increase Δ V . Using this analysis approach, for example, the minimum required capability of a relative sensing and estimation system could be determined given a mission concept’s Δ V capability and control requirements for science.


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    Title :

    Relative Sensing, Control Precision, and Mission Delta- V Trade-Offs for Precision Formation Flying in Planetary Orbit


    Contributors:

    Published in:

    Publication date :

    2019-02-21


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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