Position-Attitude Coupling Guidance and Control for a Flexible Lander

Asteroid landing is of considerable scientific and economic value while accompanied by enormous difficulties. The flexible lander has advantages in the touching phase of an asteroid landing. This paper focuses on the descent phase and proposes a feasible trajectory planning algorithm for the asteroid landing with the flexible lander. The guidance analysis model suitable for trajectory planning is established, which includes the position and attitude models. The parametric trajectory is adopted to obtain the position and attitude trajectory for the flexible lander. The Compass Search technique is applied to optimize the trajectory under constraints. The Monte Carlo simulation is carried out to verify the feasibility and computational efficiency of the proposed trajectory planning algorithm. It's concluded that the trajectory planning algorithm does have high efficiency and can guide the flexible lander to the target with small errors.