Entity

Time filter

Source Type

Russia

Ovchinnikov M.Yu.,RAS Keldysh Institute of Applied Mathematics | Roldugin D.,RAS Keldysh Institute of Applied Mathematics | Tkachev S.,RAS Keldysh Institute of Applied Mathematics | Karpenko S.,Sputnix Ltd.
Proceedings of the International Astronautical Congress, IAC | Year: 2014

Active magnetic control synthesis and analysis for attitude guidance of "Chibis-M" microsatellite are considered. Completely new magnetic control scheme based on the well-know "Bdot" reasoning is proposed. Satellite achieves one-axis inertial space attitude and maintains spinning around this axis. Control scheme utilizes Sun sensors or other possible sensors readings and orbital position data, magnetometer is not used or is unavailable. This control can therefore be used a backup system in case magnetometer fails. Averaging technique is used to assess equilibrium positions stability. The behavior of a system with respect to initial conditions and orbit parameters is studied. Evolutionary equations of motion for the axisymmetrical satellite are obtained, full set of autonomous first integrals is present. These integrals bring terminal spinning value. Equilibrium positions are found that bring inertial attitude. Slightly non-symmetrical satellite evolutionary equations are obtained also, stable equilibrium positions depending on the inertia tensor are shown. As a result simple formulae allow fast assessment on satellite attitude and spinning rate. Algorithm functioning onboard "Chibis-M" satellite is used to verify analytical results. The algorithm ensures solar panels attitude with respect to the Sun. Different stable attitude configurations are achieved in flight. Source


Ovchinnikov M.Yu.,RAS Keldysh Institute of Applied Mathematics | Roldugin D.S.,RAS Keldysh Institute of Applied Mathematics | Tkachev S.S.,RAS Keldysh Institute of Applied Mathematics | Karpenko S.O.,Sputnix Ltd.
Acta Astronautica | Year: 2014

New one-axis magnetic attitude control is proposed. Only one attitude sensor providing any inertial direction measurements is necessary, magnetometer is not used. The control may be used as a backup capability in case main actuators or some attitude sensors fail. Sun pointing is achievable using only three-axis Sun sensor, so the control may be used to lower the power consumption during battery charging. Asymptotic stability of different equilibria depending on the satellite inertia tensor is summarized. In-flight results from "Chibis-M" microsatellite are provided proving general control performance. © 2014 Published by Elsevier Ltd. on behalf of IAA. Source


Ivanov D.,RAS Keldysh Institute of Applied Mathematics | Ivlev N.,Sputnix Ltd. | Karpenko S.,Sputnix Ltd. | Ovchinnikov M.,RAS Keldysh Institute of Applied Mathematics
Advances in the Astronautical Sciences | Year: 2015

In the paper we introduce the analytical approach that allows us to study the filter performance and it can be applied for quasi-stationary motion determination. The approach based on a computation of filter covariance matrix after convergence, and it allows us to estimate the influence of unaccounted perturbations on motion determination accuracy. Accuracy dependence on filter parameters and perturbation is analytically derived. The proposed advanced method for Kalman filter performance adjustment and study is applied for a set of the algorithms of "TabletSat" microsatellites series. Source


Ivanov D.,RAS Keldysh Institute of Applied Mathematics | Ovchinnikov M.,RAS Keldysh Institute of Applied Mathematics | Ivlev N.,Russian Academy of Sciences | Ivlev N.,Sputnix Ltd. | Karpenko S.,Sputnix Ltd.
Acta Astronautica | Year: 2015

An analytical approach to study of attitude determination algorithms is considered. The approach is applicable for quasi-stationary motion determination. It is based on filter post-convergence computation of the Kalman filter covariance matrix and allows one to estimate the influence of unaccounted perturbations on motion determination accuracy. The dependence of attitude determination accuracy on filter parameters and perturbations is obtained. The proposed method of improving the Kalman filter performance is applied on board a microsatellite of the TabletSat series. © 2015 IAA. Source


Ovchinnikov M.Yu.,RAS Keldysh Institute of Applied Mathematics | Ivanov D.,RAS Keldysh Institute of Applied Mathematics | Ivlev N.,Sputnix Ltd. | Karpenko S.,Sputnix Ltd. | And 2 more authors.
Proceedings of the International Astronautical Congress, IAC | Year: 2012

The key-problems of design, examination, laboratory' and flight testing of the attitude determination and control system (ADCS) dedicated for a microsatellite arc considered. The system consists of three pairs of the reaction wheels, three magnetorquers, set of Sun sensors, three-axis magnetometer and a control unit. ADCS, on one hand, is subjected to the high accuracy and reliability requirements, and, on the other hand, power consumption, total mass and volume limitations. It is meant for the LEO satellite with mass between 10 and 50 kg. The problems are solved within several steps, i.e. preliminary study of the satellite dynamics using asymptotical and numerical techniques, hardware and software design, testing of each actuator and sensor and the whole ACS on the test-bench dedicated specially for such a laboratory simulation. Finally flight testing has been carried out to validate ADCS functioning. In this paper both dynamics of the microsatellite with ADCS and mock-up of ADCS operation are studied. Reaction wheels control law parameters are chosen to provide the maximum degree of stability. The evolution of the reaction wheels angular momentum is also studied and the problem of the desaturation with use of the magnetorquers is solved. Attitude accuracy is estimated in terms of closed-form formulae. Some aspects of in-flight ADCS exploitation onboard the Russian microsatellite "Chibis-M" developed, designed and fabricated by the Institute of Space Research of RAS and orbited from SC "Progress" on 25th of January, 2012 are presented. Flight showed a good correspondence between analytical, numerical and laboratory' study with in-flight testing. Copyright © (2012) by the International Astronautical Federation. Source

Discover hidden collaborations