High-Robustness Rocket Landing Control Based on f-Shrink and V-Space

This paper presents a novel rocket landing control method based on the f-Shrink operator and V-space dynamics. The f-Shrink operator originates from the balance equation ln f + (π/2)f = 0 and its derived iterative systems, with rigorous proofs of global convergence established in previous work. By introducing V-space (defined as v = e^(πz/2)) and leveraging its unique expansive dynamics, the proposed controller achieves a 100% landing success rate under extreme conditions including wind disturbances, engine failures, and combined disturbances. In a benchmark scenario with initial altitude of 5000m, velocity of 850m/s, and fuel of 3500kg, the V-space controller with optimal parameter β = 0.035 attains perfect success across all test phases, significantly outperforming traditional PID controllers and Z/U-space variants. The experimental results establish the superiority of V-space in controlling strongly nonlinear, large-perturbation systems, providing a new theoretical tool for reusable launch vehicle guidance and control.