Developing a New Explicit Guidance Method for the Trajectory Correction of Sub-Orbital Modules

This paper presents an explicit guidance method which could be used in the problems of orbit correction for sub-orbital modules. This method is based on solving the Lambert problem. Two efficient methods of solving the Lambert problem are introduced and compared. Using of the selected method a guidance scenario is developed which is capable of solving the problem under investigation. All of the methods of solving the Lambert problem, are based on spherical gravitational field and aerodynamic forces are not considered by them. In order to consider those important factors, a method is presented which increases the accuracy of guidance block computations. Finally using of developed method, two sample problems are investigated. Applying the developed method, a guidance block is prepared which performs the required maneuvers in a mission. Monte Carlo simulation confirms the ability of developed method in different conditions.