Transfer trajectory design using direct method in photo-gravitational Sun–Earth system.

This study employs a direct approach to construct transfer trajectories within photo-gravitational Sun–Earth system and by considering the Earth as an oblate primary in circular-restricted three-body problem (CRTBP). Specifically, it explores transfer trajectories of a spacecraft from an Earth-centred parking orbit to a halo orbit near Lagrangian point in photo-gravitational CRTBP framework. In this work, the Chebyshev collocation method (CCM) is used in combination with differential correction (DC) method to construct transfer trajectories. To compensate for the absence of a general analytical solution in the photo-gravitational CRTBP, this method uses the CCM to produce a trustworthy starting approximation. The DC method is then used to improve the approximation to the required precision for the trajectories. For a comprehensive analysis, we consider six times-of-flight (TOF) durations ranging from 100 to 200 days, with increments of 20 days (i.e., 100, 120, 140, 160, 180 and 200 days). For each TOF, we compute the departure velocities required from the Earth-centred parking orbit and the insertion velocities at the halo orbits. These computations enable us to generate detailed velocity profiles and assess the propulsive demands of different transfer durations. Additionally, we investigate the influence of out-of-plane amplitude A z of the halo orbits on maneuver costs. We consider five halo orbits with varying values of A z (1.1 × 10 5 , 2.0 × 10 5 , 3.0 × 10 5 , 4.0 × 10 5 and 5.0 × 10 5 km) to analyse how the size and shape of halo orbit affect the required velocity changes (ΔV). The study quantifies the total velocity magnitude necessary for the spacecraft's insertion onto the transfer path. We also implement the coordinate transformation of the state vector of spacecraft from the Sun–Earth barycentric rotating frame to the Earth-centred inertial J2000 frame. [ABSTRACT FROM AUTHOR]