This paper examines the ability of a bilinear tangent guidance law to perform continuous-thrust, single-burn orbital maneuvers in the small-body orbital environment (solar radiation pressure, etc.) and the capability of a Newton–Raphson predictor–corrector algorithm to perform free-time, state-to-state spacecraft guidance on initial state perturbations. This paper shows that low-thrust bilinear tangent is able to perform a wide variety of maneuvers with a wide variety of thrust levels around asteroid Bennu. Additionally, this paper shows that even with a high control authority, the size of initial state perturbations that can be corrected depends on the size of the target state’s complex backward-reachable subspace and the location of the initial state of the maneuver in that subspace. For example, a 5 mN thruster on a 1000 kg spacecraft performed an aggressive shape and plane change maneuver for less than 3.5 g of fuel. The derived guidance algorithm then corrected 100% of initial state perturbations drawn from δ r N ( 33 , 17.5 )    m and δ v N ( 3 , 1.7 )    mm / s distributions. Ultimately, this paper shows that Newton–Raphson predictor–corrector bilinear tangent guidance is a capable guidance scheme when used on perturbations that lie within the reachable subspace of the target state.


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    Titel :

    Low-Thrust Maneuverability Using Bilinear Tangent Guidance near Small Bodies


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.08.2021




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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