Development of the algorithm of the spacecraft programmed yaw turns with the use of orbital gyrocompass

Abstract

Actual issues related to the quality of control of a spacecraft yaw (SC) involving an orbital gyrocompass (OGC), built on the basis of a block of gyroscopic meters of the angular velocity vector of a spacecraft and an Earth orientation device (horizon sensor), are considered. Upgraded version of OGC with the ability to perform accurate and unlimited programmed turns of the spacecraft along the yaw angle is considered. The definition of a programme coordinate system (PCS) is introduced and a mathematical description of the OGC in the yaw program turns is given. The problem of accelerated yaw reorientation of the body-fixed coordinate system (BFCS) of the spacecraft relative to the basic orbital coordinate system (BOCS) is raised. The goal is to develop an algorithm for program yaw turns and its synthesis into the angular motion control system (AMCS) of the spacecraft. A class of programmed trajectories of the yaw motion of the spacecraft is found, which minimize the time and overshoot of transition process (TP). When constructing an algorithm to obtain optimizing programme functions (OPF), numerical methods are used to solve systems of differential equations with known boundary conditions. In the process of synthesis of the algorithm in the AMCS, the method of variable research of OPF is used. Mathematical modelling of the algorithm is performed using the MATLAB Simulink application package. Based on the results of mathematical modelling – diagrams of changes in the motion parameters of the spacecraft - a comparative analysis of the impact of each OPF on the AMCS is carried out and an assessment of the quality of the TP by the direct method is formed. As a result, practically feasible trajectories that ensure the execution of yaw programmed turns of the spacecraft with the required quality of the TP are shown, which allows to speak about the expedient application of the algorithm in the system of orientation and stabilization of the spacecraft.Actual issues related to the quality of control of a spacecraft yaw (SC) involving an orbital gyrocompass (OGC), built on the basis of a block of gyroscopic meters of the angular velocity vector of a spacecraft and an Earth orientation device (horizon sensor), are considered. Upgraded version of OGC with the ability to perform accurate and unlimited programmed turns of the spacecraft along the yaw angle is considered. The definition of a programme coordinate system (PCS) is introduced and a mathematical description of the OGC in the yaw program turns is given. The problem of accelerated yaw reorientation of the body-fixed coordinate system (BFCS) of the spacecraft relative to the basic orbital coordinate system (BOCS) is raised. The goal is to develop an algorithm for program yaw turns and its synthesis into the angular motion control system (AMCS) of the spacecraft. A class of programmed trajectories of the yaw motion of the spacecraft is found, which minimize the time and overshoot of transition process...