Stepan Sergeevich Tkachev

Testing of attitude control algorithms for microsatellite Chibis-M at laboratory facility

A laboratory facility developed at the Engineering Technological Center “Scan Ex” for testing algorithms for determination of attitude and stabilization of the attitude system of the satellite “Chibis-M” is described. The results of experiments on damping initial angular rotation, using magnetorquers, stabilization of the mock-up using flywheels, and flywheel unloading are analyzed. The operation of the algorithm for determination of the mock-up attitude is studied; the main characteristics of this algorithm are the accuracy of the state vector estimation and the time of convergence.

Attitude control of a rigid body suspended by string with the use of ventilator engines

Axial motion of a balloon payload with respect to the center of mass under action of ventilator engines is studied. An implementation of a control algorithm is suggested. The possibility of using ventilator engines for trajectory tracking is examined. A technique for determining engine parameters and results of laboratory tests of a system mock-up are presented.

Laboratory Facility for Microsatellite Mock-up Motion Simulation

A description of a COSMOS laboratory facility for the controlled motion simulation of microsatellites created in Keldysh Institute of Applied Mathematics of the Russian Academy of Sciences and the results of its application to the simulation of the control algorithms are presented. The laboratory facility consists of an aerodynamic table and microsatellite mock-ups. Due to the air cushion between the table surface and the disks on which the mock-ups are installed, free motion with three degrees of freedom becomes possible: two translational and one rotational. A review of the simulator’s international analogues has revealed its advantages and disadvantages. A motion determination algorithm based on video processing is described and its accuracy is studied. The results of the investigation of perturbations acting on the mock-ups on the aerodynamic table are presented. The performance of the control algorithms is demonstrated.

Orbital and angular motion construction for low thrust interplanetary flight

Low thrust interplanetary flight is considered. Firstly, the fuel-optimal control is found. Then the angular motion is synthesized. This motion provides the thruster tracking of the required by optimal control direction. And, finally, reaction wheel control law for tracking this angular motion is proposed and implemented. The numerical example is given and total operation time for thrusters is found. Disturbances from solar pressure, thrust eccentricity, inaccuracy of reaction wheels installation and errors of inertia tensor are taken into account.