Non-coplanar orbit rendezvous control algorithm based on fixed-impulse single-pulse

To address the challenge of precise rendezvous in non-coplanar orbits, this study proposes an orbital maneuver method based on solid propulsion. The relationship between transfer duration and impulse magnitude is analyzed, and under the constraint of fixed impulse magnitude, the correlation between transfer duration and minimum rendezvous error is investigated. The transfer trajectory design problem is ultimately transformed into finding the minimum point of a single-valley function. A control solution framework for non-coplanar orbit rendezvous using fixed-impulse single-pulse propulsion is developed. The proposed workflow involves three key steps: first, calculating the time required for the target to coast inertially to a virtual intersection point; second, employing Lambert's algorithm to determine the minimum velocity increment; and third, integrating the golden section method with an optimal impulse guidance algorithm to precisely solve for transfer duration and impulse direction when the chaser's impulse exceeds the minimum increment. Simulation results demonstrate that the algorithm achieves high computational efficiency and rapid convergence, with a final rendezvous accuracy of 0.6 meters. This approach provides an effective solution for precision rendezvous tasks in non-coplanar orbit scenarios.