Analytical solution of the optimal steering law for non-ideal solar sail

Niccolai, Lorenzo; Quarta, Alessandro A.; Mengali, Giovanni

doi:10.1016/j.ast.2016.11.031

Cited by 40 publications

(24 citation statements)

References 28 publications

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“…The same bounds as those reported in Table 4 are used for the shape parameters. The flight time T is constrained to assume values within the interval [5,20] TU (or [10,30] TU) for the transfer toward 2002 DU3 (or 2007 MK13), whereas n rev ∈ [1, 3] (or n rev ∈ [4,7]). As in the orbit-to-orbit case, a comparison of the three previously described methods has been performed, and the solutions of the shapebased approach have been used as initial guesses for the direct multiple-shooting approach.…”

Section: Rendezvous Scenariosmentioning

confidence: 99%

“…Indirect methods use the analytical necessary conditions from the calculus of variation and Pontryagin's maximum principle to formulate a two-point boundary value problem, whose solution gives the optimal control law capable of transferring the spacecraft from a given initial condition toward a final target state [8]. This approach has the advantage that the optimal control law can be usually determined analytically [9,10], but the nonlinearity of the problem induces a high sensitivity to the initial guess of costates. Direct methods, instead, transcribe a continuous optimal control problem into a nonlinear programming problem by partitioning in time the state vector and the control law.…”

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confidence: 99%

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Shape-based approach for solar sail trajectory optimization

Caruso

Quarta

Mengali

et al. 2020

Aerospace Science and Technology

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Section: Rendezvous Scenariosmentioning

confidence: 99%

mentioning

confidence: 99%

Shape-based approach for solar sail trajectory optimization

Caruso

Quarta

Mengali

et al. 2020

Aerospace Science and Technology

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“…While the trajectory analysis has been widely discussed and several methods were proposed to design and optimize the trajectory for various mission requirements [3,[8][9][10][11][12][13][14][15], ranging from sail types and design, deployment, dynamics, to attitude dynamics and control, these aspects are all vital to a practical and reliable solar sail mission. For dynamics, Wang et al designed a distributed fault-tolerant control method for an E-sail system to enhance the reliability of using this new technology, and they also developed a control strategy for E-sail-based formation flight [16].…”

Section: Introductionmentioning

confidence: 99%

Design and Simulation of a Flexible Bending Actuator for Solar Sail Attitude Control

et al. 2021

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This paper presents the design of a flexible bending actuator using shape memory alloy (SMA) and its integration in attitude control for solar sailing. The SMA actuator has advantages in its power-to-weight ratio and light weight. The bending mechanism and models of the actuator were designed and developed. A neural network based adaptive controller was implemented to control the non-linear nature of the SMA actuator. The actuator control modules were integrated into the solar sail attitude model with a quaternion PD controller that formed a cascade control. The feasibility and performance of the proposed actuator for attitude control were investigated and evaluated, showing that the actuator could generate 1.5 × 10−3 Nm torque which maneuvered a 1600 m2 CubeSat based solar sail by 45° in 14 h. The results demonstrate that the proposed SMA bending actuator can be effectively integrated in attitude control for solar sailing under moderate external disturbances using an appropriate controller design, indicating the potential of a lighter solar sail for future missions.

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“…By utilizing the Gateway, NASA plans to land the first female astronaut on the Moon by 2024 and aims to establish a sustainable human presence on the Moon by 2028 [3]. As the paradigm for planetary exploration has shifted, many fascinating studies have been conducted on orbital stabilities and low-energy transfers [4][5][6][7][8][9][10][11][12]. Further details on the relevant literature are left for the readers to discover, as there exists a significant amount of research.…”

Section: Introductionmentioning

confidence: 99%

Potential Launch Opportunities for a SmallSat Mission around the Moon Injected during a Lunar Flyby En Route to Mars

Song

Lee

et al. 2019

Mathematical Problems in Engineering

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In this work, the concept of a multipurpose mission that can explore both the Moon and Mars with a single launch is proposed, and potential launch opportunities are analyzed to establish an early-phase trajectory concept. The proposed mission applies the concept of a piggyback ride to a small-sized lunar probe, i.e., the daughtership, of the main Mars orbiter, i.e., the mothership. For the trajectory design, the Earth-Moon-Mars gravity assist (EMMGA) trajectory is adopted for the mothership to reach Mars, and the daughtership is assumed to be released from the mothership during lunar flyby. To investigate the early-phase feasibility of the proposed mission, the launch windows have been analyzed and the associated delta-Vs have been directly compared with the solutions obtained for typical Earth-Mars direct (EMD) transfer options. The identified launch windows (in the years 2031 and 2045) could be the strongest candidates for the proposed conceptual mission. Under the current assumptions, up to approximately 15% (in 2031) and 9% (in 2045), more dry mass is expected to be delivered to Mars by appropriately selecting one of the currently available launch vehicles, regardless of whether the EMMGA transfer option is used. For missions around the Moon using a SmallSat in 2031, the feasibility of a lunar orbiter case and an impactor case is briefly analyzed based on the delta-Vs required to divert the SmallSat from the mothership. Although the current work is performed under numerous assumptions for a simplified problem, the narrowed candidate launch window from the current work represents a good starting point for more detailed trajectory design optimization and analysis to realize the proposed conceptual mission.

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Analytical solution of the optimal steering law for non-ideal solar sail

Cited by 40 publications

References 28 publications

Shape-based approach for solar sail trajectory optimization

Shape-based approach for solar sail trajectory optimization

Design and Simulation of a Flexible Bending Actuator for Solar Sail Attitude Control

Potential Launch Opportunities for a SmallSat Mission around the Moon Injected during a Lunar Flyby En Route to Mars

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