Families of halo orbits in the elliptic restricted three-body problem for a solar sail with reflectivity control devices

Orbital perturbation analysis and generation of nominal near rectilinear halo orbits using low-thrust propulsion

“…; ω x , ω y , and ω z are the partial derivatives of ω with respect to the position variables. 38,40 Note that the time variable is converted from t to θ. The existence of lunar angular velocity and angular acceleration, results in additional perturbation terms V × ρ, ΔV × (ΔV × ρ), and 2ΔV × v. Among them, ΔV × (ΔV × ρ) is about the order of 10 À19 km/s 2 and 2ΔV × v is of 10 À13 km/s 2 .…”

“…For the Earth–Moon ERTBP without perturbation, the nondimensional equations of motion are similar to equation (3) 38,39 where the pseudo-potential ω is defined as ω=U∗/(1+e⁡cos⁡θ), U∗=12(x2+y2−z2e⁡cos⁡f)+1−μr1+μr2; ω x , ω y , and ω z are the partial derivatives of ω with respect to the position variables. 38,40 Note that the time variable is converted from t to θ .…”

Integrated guidance and control for solar sail station-keeping with optical degradation

“…A solar sail using only the sail angles as the control variables for stationkeeping cannot adequately compensate for the errors in the optical properties (Huang et al, 2019). Moreover, the errors in the optical properties mainly affect the magnitude of the SRP acceleration, while this cannot be controlled effectively by varying the sail angles only.…”