Integrated Analysis of J₂-Perturbed Impulsive Orbital Maneuvers with Propulsion Mass Assessment

Accurate modeling of orbital maneuvers is crucial for spacecraft mission design, trajectory optimization, and efficient propellant management. This study introduces a comprehensive framework for simulating and analyzing orbital maneuvers, validated against FreeFlyer. The framework accommodates multiple maneuver types, including coplanar transfers, inclination adjustments, and combined angular maneuvers. For each scenario, it performs trajectory propagation, computes maneuvers, and analyzes orbital elements, providing visual outputs. High fidelity numerical propagators and force models are integrated to account for perturbations such as Earth’s oblateness, while thrust-based calculations ensure realistic mission representation. The framework consists of modular algorithms, each addressing a specific function within maneuver planning, which are systematically combined to form a flexible simulation environment. It enables the computation of Δ𝑣, transfer durations, and propellant requirements using the Tsiolkovsky rocket equation, linking kinematic modeling with propulsion analysis. The study integrates established analytical relations with numerical propagation into a unified tool suitable for preliminary maneuver design. By connecting classical impulsive dynamics with propulsion sizing, it provides consistent estimates of Δv, transfer time, and propellant mass under J₂ perturbation. Numerical comparisons with FreeFlyer show that relative Δv errors range from 10⁻⁹ to 10⁻⁸ for LEO-to-LEO transfers, remain below 10⁻³ for inclination-only maneuvers, and reach a few percent for combined LEO-to-GEO transfers. The framework was applied to a case study of a satellite transfer from Low Earth Orbit to Geostationary Orbit. Various propulsion options were evaluated to identify the optimal propellant type that minimizes transfer time, demonstrating the framework’s practical utility in mission planning and propulsion selection.