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EnglishAnalytic trajectories for a spacecraft subjected to a low, continuous, propulsive acceleration are available only for very special cases [1–3], even though these solutions find significant utility in preliminary mission design and optimization [4]. If a closed-form trajectory corresponding to a given thrust control law cannot be recovered, a possible option is to resort to a shape-based approach [5–7], or to suitably simplify the differential equations of motion [8–10]. Within the latter context, in this Note an analytical, albeit approximate, expression for the heliocentric trajectory of a spacecraft propelled by a low-performance electric sail [11, 12] is discussed. Using a two-dimensional model and under the assumptions of constant thrust angle and low propulsive acceleration modulus, the spacecraft heliocentric trajectory is obtained in a parametric way as a function of time. The effectiveness of the mathematical model is checked by comparing the analytic solution with a numeric integration of equations of motion.
| Autori interni: | QUARTA, ALESSANDRO ANTONIO (Primo) MENGALI, GIOVANNI (Secondo) |
| Autori: | Quarta, ALESSANDRO ANTONIO; Mengali, Giovanni |
| Titolo: | Trajectory Approximation for Low-Performance Electric Sail with Constant Thrust Angle |
| Anno del prodotto: | 2013 |
| Abstract: | Analytic trajectories for a spacecraft subjected to a low, continuous, propulsive acceleration are available only for very special cases [1–3], even though these solutions find significant utility in preliminary mission design and optimization [4]. If a closed-form trajectory corresponding to a given thrust control law cannot be recovered, a possible option is to resort to a shape-based approach [5–7], or to suitably simplify the differential equations of motion [8–10]. Within the latter context, in this Note an analytical, albeit approximate, expression for the heliocentric trajectory of a spacecraft propelled by a low-performance electric sail [11, 12] is discussed. Using a two-dimensional model and under the assumptions of constant thrust angle and low propulsive acceleration modulus, the spacecraft heliocentric trajectory is obtained in a parametric way as a function of time. The effectiveness of the mathematical model is checked by comparing the analytic solution with a numeric integration of equations of motion. |
| Digital Object Identifier (DOI): | 10.2514/1.59076 |
| Appare nelle tipologie: | 1.1 Articolo in rivista |
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