D.S. Roldugin

Investigation of the effectiveness of an algorithm of active magnetic damping

We consider the rapid rotation of a satellite equipped with an active magnetic attitude control system with the -Bdot algorithm designed to damp the initial angular velocity. The time-response of the algorithm is analytically studied as a function of orbit inclination.

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.

Six-impulse maneuvers for rendezvous of spacecraft in near-circular noncoplanar orbits

The problem of a rendezvous of two spacecraft in close near-circular noncoplanar orbits is considered. The angles of applying velocity impulses and their orientation are determined from necessary conditions of optimality derived using the basis vector theory. For non-degenerate six-impulse solutions the analytical formulas are found that approximate the dependence of moments of applying velocity impulses and angles determining their orientation on the rendezvous duration. The total characteristic velocity of six-impulse solutions (or five-impulse solutions derived from them) is compared to the total characteristic velocity obtained when solving the Lambert problem.

Motion of a satellite equipped with a pitch flywheel and magnetic coils in gravitational field

A satellite equipped with a magnetic attitude control system and a pitch flywheel has been considered. The system performance in the transient mode has been investigated. The characteristic exponent of the system have been approximated for a satellite on a circumpolar orbit. In the steady-state mode of gravitational attitude, small motions are considered in the vicinity of equilibrium. The attitude accuracy has been analyzed. The algorithm of an arbitrary but given attitude of the satellite in the orbital plane has been investigated. A numerical simulation has been performed.

One-axis attitude of arbitrary satellite using magnetorquers only

AbstarctAn active magnetic control synthesis for attitude guidance of “Chibis-M” microsatellite is considered. The only information required is the data from the sun sensor. Applicability of a control to achieve solar panels sun-pointing is studied. Equations of motions are analytically solved using averaging technique. The behavior of a system with respect to initial conditions and orbit parameters is studied.

Study of a bunch of three algorithms for magnetic control of attitude and spin rate of a spin-stabilized satellite

We consider the angular motion of an axi-symmetrical satellite equipped with an active magnetic attitude control system. Dynamics of the satellite is studied on the entire control loop, consisting of a bunch of three successively used algorithms. The control cycle includes the stages of nutation damping, spinning up the satellite about its symmetry axis, and reorienting the symmetry axis into a preset direction in the inertial space. The results are confirmed by numerical simulations.

Erratum to: “Motion of a satellite equipped with a pitch flywheel and magnetic coils in gravitational field”

M. Yu. Ovchinnikova, D. S. Roldugina, *, V. I. Penkova, R. Varatharajoob, and V. S. Ryabikovc aKeldysh Institute of Applied Mathematics, Russian Academy of Sciences, Moscow, 125047 Russia bUniversity of Putra, Serdang, Selangor, Malaysia 43400 cResearch Institute for Electromechanics, Istra, 143502 Russia *e-mail: rolduginds@gmail.com Submitted June 22, 2017; accepted for publication June 23, 2017

The results of flight tests of an attitude control system for the Chibis-M microsatellite

The attitude control system of the Chibis-M microsatellite is described. Results of flight experiments on damping the initial angular velocity (made using magnetorquers) are considered, as well as stabilization in the orbital referece frame, and orientation of solar arrays toward the Sun using reaction wheels. The operation of algorithms of satellite attitude determination on sunlit and shadow segments of the orbit is also under study. The general logic of operation of the attitude control system in automatic mode is presented and discussed.