Solar Sail Transfer Trajectory Design for Comet 29P/Schwassmann–Wachmann 1 Rendezvous

Quarta, Alessandro A.; Abu Salem, Karim; Palaia, Giuseppe

doi:10.3390/app13179590

Cited by 9 publications

(8 citation statements)

References 40 publications

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“…The value of n can be estimated using an analytical expression obtained through the combination of Equations ( 6), (25), and (28). Indeed, assuming ãp sin α ≃ ãm sign r f − 1 during the transfer, with the aid of Equation ( 28), the second and the last of Equation ( 6) give…”

Section: Maximum Value Of ãM Compatible With the Proposed Methodsmentioning

confidence: 99%

Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration

Quarta

2024

Applied Sciences

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The transfer between two circular, coplanar Keplerian orbits of a spacecraft equipped with a continuous thrust propulsion system is usually studied in an optimal framework by maximizing a given performance index. Using an indirect approach, the optimal trajectory and the maximum value of the performance index are obtained by numerically solving a two-point boundary value problem (TPBVP). In this context, the computation time required by the numerical solution of the TPBVP depends on the guess of unknown initial costates. The aim of this paper is to describe an analytical procedure to accurately approximate the initial costate variables in a coplanar, circle-to-circle, minimum-time transfer. In particular, this method considers a freely steerable propulsive acceleration vector, whose magnitude varies over a finite range with a sufficiently low maximum value. The effectiveness of the analytical method is tested in a set of both geocentric and heliocentric (simplified) mission scenarios, which model the classical LEO-GEO or interplanetary transfers toward Venus, Mars, Jupiter, and comet 29P/Schwassmann–Wachmann 1.

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Section: Maximum Value Of ãM Compatible With the Proposed Methodsmentioning

confidence: 99%

Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration

Quarta

2024

Applied Sciences

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“…The RTN reference frame is schematized in Figure 3, which is an adaptation of a similar figure that has recently appeared in Ref. [27]. Note that the plane ( îR , îT ) coincides with the plane of the spacecraft osculating orbit.…”

Section: Spacecraft Dynamics In the Interplanetary Spacementioning

confidence: 96%

“…The set of classical orbit elements can be recovered by inverting Equation (1), as described in Ref. [27], and the result is…”

Section: Spacecraft Dynamics In the Interplanetary Spacementioning

confidence: 99%

Rapid Orbit-to-Orbit Transfer to Asteroid 4660 Nereus Using Solar Electric Propulsion

Quarta,

Mengali,

Bassetto

2023

Universe

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This paper analyzes the rapid rendezvous trajectory of a spacecraft equipped with an advanced solar electric propulsion system towards asteroid 4660 Nereus. In this context, a set of possible minimum-time orbit-to-orbit transfer trajectories is calculated by modeling the propulsion system performance characteristics on those of NASA’s Evolutionary Xenon Thruster-Commercial (NEXT-C). In particular, the actual NEXT-C ion engine throttle table is used to calculate the optimal thrust control law that ensures the flight time is minimized for an assigned value for the spacecraft’s initial mass and the reference (electric) power at the beginning of the transfer. A baseline scenario that considers the actual inertial characteristics of the NASA’s DART spacecraft is analyzed in detail, and a parametric study is proposed to evaluate the transfer performance as a function of the main design parameters as, for example, the spacecraft’s initial mass and the reference power.

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“…The problem under consideration, that is, the calculation of the optimal control law (or, equivalently, the optimal transfer trajectory) that satisfies the final conditions of Equation ( 5) and minimizes the value of a c , is solved using an indirect approach based on the calculus of variations [36,37]. The mathematical model requiring the definition of the Hamiltonian function and the (numerical) integration of the Euler-Lagrange equations is similar to the model discussed by the authors in the recent paper [38], and is not reported here for the sake of conciseness. However, it is interesting to mention that the optimal sail pitch angle is determined, according to Sauer [35], using Pontryagin's maximum principle [39], while the boundary value problem associated with the optimization process is solved numerically by adapting the procedure described in [40].…”

Section: Mathematical Model Of the Solar Sail-based Transfermentioning

confidence: 99%

Solar Sail Optimal Performance in Heliocentric Nodal Flyby Missions

Mengali,

Bassetto,

Quarta

2024

Aerospace

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Solar sails are propellantless propulsion systems that extract momentum from solar radiation pressure. They consist of a large ultrathin membrane, typically aluminized, that reflects incident photons from the Sun to generate thrust for space navigation. The purpose of this study is to investigate the optimal performance of a solar sail-based spacecraft in performing two-dimensional heliocentric transfers to inertial points on the ecliptic that lie within an assigned annular region centered in the Sun. Similar to ESA’s Comet Interceptor mission, this type of transfer concept could prove useful for intercepting a potential celestial body, such as a long-period comet, that is passing close to Earth’s orbit. Specifically, it is assumed that the solar sail transfer occurs entirely in the ecliptic plane and, in analogy with recent studies, the flyby points explored are between 0.85au and 1.35au from the Sun. The heliocentric dynamics of the solar sail is described using the classical two-body model, assuming the spacecraft starts from Earth orbit (assumed circular), and an ideal force model to express the sail thrust vector. Finally, no constraint is imposed on the arrival velocity at flyby. Numerical simulation results show that solar sails are an attractive option to realize these specific heliocentric transfers.

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Solar Sail Transfer Trajectory Design for Comet 29P/Schwassmann–Wachmann 1 Rendezvous

Cited by 9 publications

References 40 publications

Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration

Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration

Rapid Orbit-to-Orbit Transfer to Asteroid 4660 Nereus Using Solar Electric Propulsion

Solar Sail Optimal Performance in Heliocentric Nodal Flyby Missions

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