ADAPTATIVE, MULTIPLE SHOOTING OPTIMIZATION METHOD FOR DETERMINING OPTIMAL SPACECRAFT TRAJECTORIES

摘要

1. A method for determining a path for moving the spacecraft from the initial to the target space body outer body relative to a given central space body, the optimal trajectory is determined in relation to the movement of the spacecraft met the requirement of the space mission, the method comprising the steps of: kotoryhpredostavlyayut, according to the principle Pontrjagin maximum physical-mathematical model relating the model values ​​and INDIVIDUALS Kie quantities representing the movement of the spacecraft relative to a given central space body, the model values ​​comprise a first vector value () of the model and a second vector value () of the model, the first vector value () of the model has a first module, a time-varying, and a first orientation in space, which varies in time and is given by a first angle () longitude, time-varying, and a first angle () elevation varying in time, wherein the first vector quantity () model is, moment by moment, the corresponding optimal direction of propulsion of the spacecraft with respect to the requirements of the space mission, the second vector quantity () model has a second module, time-varying, and a second orientation in space, which varies in time and is given by a second angle ( ) longitude, time-varying, and a second angle () elevation varying in time, wherein the second vector quantity () represents the model, moment by moment, the time development of the first