Solar sail cooperative formation flying around <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" altimg="si1.svg"><mml:mrow><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>2</mml:mn></mml:mrow></mml:msub></mml:mrow></mml:math>-type artificial equilibrium points

Wang, Wei; Baoyin, Hexi; Mengali, Giovanni; Quarta, Alessandro A.

doi:10.1016/j.actaastro.2019.10.028

Cited by 34 publications

(4 citation statements)

References 68 publications

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“…As a result, the only effective control variable is δβ, whereas it is assumed that the sail is constantly in a Sun-facing attitude. It may be verified that the eigenvalues of matrix A are λ 1,2 = −3.507 ± 2.571j , λ 3,4 = −0.078 ± 1.332j , λ 5,6 = ±1.776j (49) showing that the dynamics along the k-direction is undamped due to the presence of two imaginary eigenvalues. The spacecraft oscillates about the ecliptic plane with an amplitude of about 1800 km, as is shown in Fig.…”

Section: Case Study and Numerical Simulationsmentioning

confidence: 99%

Feedback control law of solar sail with variable surface reflectivity at Sun-Earth collinear equilibrium points

Niccolai

Mengali

Quarta

et al. 2020

Aerospace Science and Technology

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Section: Case Study and Numerical Simulationsmentioning

confidence: 99%

Feedback control law of solar sail with variable surface reflectivity at Sun-Earth collinear equilibrium points

Niccolai

Mengali

Quarta

et al. 2020

Aerospace Science and Technology

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“…A square sail is employed as the solar polar orbiter for challenging science missions [8]. Solar sail cooperative formation around L 2 -type artificial equilibrium points provides a dramatic interplanetary observation point [9]. Wang et al [10] investigate the problem of multiple solar sail formation around heliocentric displaced orbit via consensus.…”

Section: Introductionmentioning

confidence: 99%

Intelligent Fuzzy Control in Stabilizing Solar Sail with Individually Controllable Elements

Chen

Santos

et al. 2022

Space Sci Technol

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Fuzzy logical control is a robust and effective control method in industrial fields, which renders it applicable to the attitude control of a solar sail. However, it is hard to apply in black-box and time-varying problem as real solar sail attitude control. Considering the lack of a priori knowledge and the unacceptable manual workload in the design of the fuzzy logical controller (FLC), an intelligent FLC designer (IFLCD) is developed by introducing neural network modelling and automatic design method. Besides, IFLCD also supports self-adaption for better control accuracy. By applying the proposed IFLCD in the attitude stabilization of a solar sail with individually controllable elements (SSICE), an effective solution of unmanned, time-varying, and complex system control method is offered without any mathematical model, which also overcomes the difficulties in FLC design Considering the performance degradation, accident, and distance problems faced by spacecraft, IFLCD can help with more practical problems that are hard be solved by traditional control theory.

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“…It is found that the initial spherical surface will become an ellipsoidal one, while it will become smaller as the distance from the Earth decreases. Several studies [10][11][12] are aimed at the design of formation flying to obtain the stable configuration in CRTBP or bicircular model (BCM). Meanwhile, the solar sail could be applied to achieve a synchronized formation tracking with a virtual leader.…”

Section: Introductionmentioning

confidence: 99%

Mission Design of an Aperture-Synthetic Interferometer System for Space-Based Exoplanet Exploration

Jia

Huo³

et al. 2022

Space Sci Technol

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In recent years, exoplanet detection has become the technological frontier in the field of astronomy, because it provides evidence of the origin of life and the future human habitable exoplanet. Deploying several satellites to form an aperture-synthetic interferometer system in space may help discover “another Earth” via interferometry and midinfrared broadband spectroscopy. This paper analyzes a space-based exoplanet exploration mission in terms of the scientific background, mission profile, trajectory design, and orbital maintenance. First, the system architecture and working principle of the interferometer system are briefly introduced. Secondly, the mission orbit and corresponding transfer trajectories are discussed. The halo orbit near the Sun-Earth L2 (SEL2) orbit is chosen as the candidate mission orbit. The low-energy transfer via stable invariant manifold with multiple perigees is designed, and the proper launch windows are presented. A speed increment less than 10 m/s is imposed for each transfer to achieve the insertion of the halo orbit. Finally, the tangent targeting method (TTM) is applied for high-precision formation maintenance with the whole velocity increments of less than 5×10−4 m/s for each spacecraft when the error bound is 0.1 m. The overall fuel budget during the mission period is evaluated and compared. The design in this paper will provide technical support and reliable reference for future exoplanet exploration missions.

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Solar sail cooperative formation flying around L2-type artificial equilibrium points

Cited by 34 publications

References 68 publications

Feedback control law of solar sail with variable surface reflectivity at Sun-Earth collinear equilibrium points

Feedback control law of solar sail with variable surface reflectivity at Sun-Earth collinear equilibrium points

Intelligent Fuzzy Control in Stabilizing Solar Sail with Individually Controllable Elements

Mission Design of an Aperture-Synthetic Interferometer System for Space-Based Exoplanet Exploration

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