Spacecraft Angular Reorientation Control By Means Of Flywheels

摘要

For the problem of spatial reorientation of spacecraft from the initial position to terminal one we determine preset trajectory and control, realizing it. Optimization of the preset trajectory according to the given criterion is done. Result of numerical modeling is stated. The suggested algorithms are realized in the control system of the "Egyptsat-1" spacecraft, designed by State Design Office "Yuzhnoe" within framework of the international contract between Ukraine and Egypt.