Fast and Robust Computation of Low-Thrust Orbit-Raising Trajectories

Sreesawet, Suwat; Dutta, Atri

doi:10.2514/1.g003319

Cited by 24 publications

(18 citation statements)

References 29 publications

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“…These components of the thrust are functions of the magnitude of thrust F and the control angles α and β as shown in Figure 2. The first-order differential equations that describe the spacecraft translational dynamics are given by the following equations [39]:…”

Section: Spacecraft Dynamicsmentioning

confidence: 99%

“…This paper utilizes a novel dynamic model that has proven to be effective for solving orbit-raising optimal control problems [38,39]. This model uses dynamical parameters as the states of the spacecraft, instead of geometrical quantities.…”

Section: Introductionmentioning

confidence: 99%

“…Additionally, the current paper utilizes a novel optimization scheme introduced in Ref. [39]; this technique breaks the multi-revolution problem into a sequence of optimization sub-problems, computing the all-electric orbit-raising trajectory in the order of tens of seconds on a standard personal computer without the need of any user-provided initial guess. This optimization tool can be used to analyze various electric orbit-raising mission scenarios and also can compute the trajectories to the GEO due to the non-singularity of the formulation in the equatorial plane.…”

Section: Introductionmentioning

confidence: 99%

“…Recently, the work in Ref. [39] was extended in order to analyze a variety of different aspects of the orbit-raising problem: effect of J 2 perturbations and accurate shadow model [40], effects of using different types of electric thrusters [41], analysis of attitude control during the maneuver [42], effect of planning horizon length [43], effect of objective function weights [44], and their adaptive modification [45].…”

Section: Introductionmentioning

confidence: 99%

“…The contributions of the paper are two important enhancements of the optimization problem described in Ref. [39], in which the thrust magnitude was determined by a pre-set scheme (thrust in Sun-lit segments of trajectory and coast in eclipses) and power loss during transfer was not considered. First, we allow for coasting arcs within the Sun-lit portion of the orbit-raising trajectory.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Sequential Low-Thrust Orbit-Raising of All-Electric Satellites

2020

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In this paper, we consider a recently developed formulation of the electric orbit-raising problem that utilizes a novel dynamic model and a sequence of optimal control sub-problems to yield fast and robust computations of low-thrust trajectories. This paper proposes two enhancements of the computational framework. First, we use thruster efficiency in order to determine the trajectory segments over which the spacecraft coasts. Second, we propose the use of a neural network to compute the solar array degradation in the Van Allen radiation belts. The neural network is trained on AP-9 data and SPENVIS in order to compute the associated power loss. The proposed methodology is demonstrated by considering transfers from different geosynchronous transfer orbits. Numerical simulations analyzing the effect of thruster efficiency and average power degradation indicate the suitability of starting the maneuver from super-geosynchronous transfer orbits in order to limit fuel expenditure and radiation damage. Furthermore, numerical simulations demonstrate that proposed enhancements are achieved with only marginal increase in computational runtime, thereby still facilitating rapid exploration of all-electric mission scenarios.

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Section: Spacecraft Dynamicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Sequential Low-Thrust Orbit-Raising of All-Electric Satellites

2020

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Elliptical shape-based model for multi-revolution planeto-centric mission scenarios

Prinetto

Lavagna

2021

Celest Mech Dyn Astr

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The paper presents a novel 3-dimensional shape-based algorithm which extends the domain of analytical solutions to planeto-centric mission scenarios, which classically entail even thousands revolutions to transfer to the final orbit. Thanks to the strong physical meaning the proposed method keeps while shaping the trajectory, the method succeeds in outputting a solution close to the real optimum. The proposed approach allows to easily formalize practical mission constraints, such as maximum thrust threshold and eclipses; free and fixed time of flight are manageable as well. The approach is almost completely analytic, which is beneficial as it significantly decreases the computational load. It is well suited for complex mission scenarios and for fast detection near optimal solutions to support the whole mission design.

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Coplanar circular-to-circular orbit transfer guidance with constant-thrust acceleration

Kaki,

Akella

2023

Celest Mech Dyn Astron

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Fast and Robust Computation of Low-Thrust Orbit-Raising Trajectories

Cited by 24 publications

References 29 publications

Sequential Low-Thrust Orbit-Raising of All-Electric Satellites

Sequential Low-Thrust Orbit-Raising of All-Electric Satellites

Elliptical shape-based model for multi-revolution planeto-centric mission scenarios

Coplanar circular-to-circular orbit transfer guidance with constant-thrust acceleration

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