Trajectory optimization for solar sail in cislunar navigation constellation with minimal lightness number

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

“…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].…”

“…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]. In terms of attitude control, although there exists a variety of conventional attitude control methods such as reaction wheels, control moment gyroscopes (CMGs) and thrusters, these methods cannot effectively control the attitude of solar sails due to the mass limitation and the required long mission lifetime [1,3,11]. Currently, several methods for attitude control for solar sails exist [17], including the control vane method [18], gimbaled masses method [19,20], sliding masses method, shifted wings method, tilted wings method and billowed wings method for rigid solar sail and sail film with controllable reflectivity method for non-rigid solar sail [3,[21][22][23].…”

Shape-based approach for solar sail trajectory optimization

“…Solar sailing is an innovative and fascinating form of propulsion that requires no propellant consumption to produce thrust, which, instead, is generated exploiting the solar radiation pressure [1]. Due to its propellantless nature, a solar sail-based spacecraft can be used to perform advanced space missions that would be difficult to carry out with traditional chemical thrusters, such as maintenance of artificial equilibrium points [2,3], generation of (non-Keplerian) displaced orbits [4], and asteroid tour [5,6].…”

“…2 . A simplified analysis has been carried out, in which each Orbital parameters of asteroid 1219 Britta, 1831 Nicholson and 4 Vesta.…”

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

“…The features of the circular restricted three-body problem (CR3BP) [1,2] allow transfer trajectories with small propellant consumption to be designed by exploiting the existence of invariant manifolds, as is discussed in Refs. [3,4,5,6] in the case of the Earth-Moon CR3BP. A potential application of the results of the CR3BP analysis is constituted by space missions orbiting around equilibrium points.…”