spacecraft 
This collection can be used to test spacecraft production materials, in order to determine their resistance to biodegradation.


Studying Stability of the Flexible Spacecraft with a Discrete Control System


Stability of the spacecraft was considered with regard for its elastic structural oscillations arising under discrete control.


Consideration was given to the possibility of estimating jointly the motion coordinates and parameters of the elastic spacecraft using algorithms based on the discrete Kalman filtering and the theory of testing statistical hypotheses.


Design of the Suboptimal Profiled Relay Control of Orientation of the Spacecraft Having Elastic Structural Elements with Regard


A speedoptimal formulation of the control of angular spacecraft motion with regard for two tones of oscillations of its elastic structural elements was considered.


Methods of Estimating the Envelope of Elastic Oscillations of the Flexible Spacecraft


A problem concerned with studying of dynamics of angular motion of large space structures and flexible spacecraft was considered.


Consideration was given to the Mayer variational problem of determining the optimal spacecraft trajectories.


The spacecraft center of mass was assumed to move in a thin spherical layer in the neighborhood of a certain reference orbit with a limited mass flow rate and constant jetpipe gas velocity.


Fuzzy logicbased design of the generalized adaptation algorithm for the discrete control system of flexible spacecraft


Results of modeling a flexible spacecraft with adaptive control system were presented.


A modalphysical representation of the mathematical model of flexible spacecraft enabling one to specify a diversity of the distinctions of the dynamics of controllable motion of the flexible objects was determined.


Consideration was given to some important questions concerning the impact of structural flexibility on stability and performance of the control system of orientation of flexible spacecraft.


The variational problem to determine the optimal trajectories of the center of mass of a spacecraft moving in the central Newtonian field with limited power and specific momentum was considered.


Parametric control in the problem of spacecraft stabilization in the geomagnetic field


The spacecraft interacting with the geomagnetic field in electrodynamic mode is subject to parametric perturbations; parameters of the spacecraft are controlled quasiperiodic functions.


Under some conditions, there exist control algorithms for spacecraft electrodynamic parameters that allow realizing systems of spacecraft angular position stabilization.


Stability of the spacecraft stabilized orientation is proved both analytically and by PC computations.


Optimization of interorbital threedimensional transfer trajectories for stage spacecraft

