Small celestial body attachment convex trajectory guidance method

The invention discloses a small celestial body attachment convex trajectory guidance method, relates to a small celestial body attachment guidance method, and belongs to the technical field of deep space exploration. The convex trajectory guidance law is composed of an energy optimal item and a sliding mode item, for small celestial body dynamics coupling, concave-convex parts of a three-dimensional space trajectory are defined on two mutually orthogonal planes of a landing point fixed connection coordinate system, and by changing an acceleration coefficient and the fixed constant accelerationtime of energy optimal guidance, the attachment track keeps convex or convex from concave; for the situation that the magnitude and direction of the small celestial body gravitation change along withthe position of a land device, the gravitation of the current period is predicted and counteracted when each guidance period starts. In order to cope with interference, the lander trajectory in the current period is predicted