G.P. Titov

Computer aided design and flight support of spacecraft control systems

Abstract We present results on creation and employment of the software system DYNAMICS for research of dynamic processes in complex control systems. The software tool supports functions modelling and simulation for spacecraft, control systems design, as well as solving any user problems in special problem areas which are described by differential and difference equations, also by transfer functions and logic conditions including a logic automata for real time. We present also the decision support system, which is based on the DYNAMICS and is used by the flight controller at the spacecraft Flight Control Center in the process of state diagnostics and decision-making on contradictory failures in the onboard spacecrafts motion control system.

Fault-Tolerant Attitude Control Systems of the Communication and Navigation Spacecraft*

Abstract We present new results on creation and employment of nonlinear methods, algorithms and software for dynamic research of the precision faulttolerant gyromoment attitude control systems of the Russian spacecrafts for communication, navigation and geodetic purposes.

Robust gyromoment spacecraft attitude control with precise pointing a flexible antenna

Abstract New approach for modeling a physical hysteresis damping the flexible spacecraft structure oscillations, is developed. New results on spacecraft attitude guidance and digital robust control with precise pointing the large-scale flexible antennas, are presented.

Nonlinear Dynamics of a Spacecraft Respinup by a Weak Internal Control

Abstract Recently, space science and engineering advanced new problem before theoretical mechanics and motion control theory: a spacecraft directed respinup by the weak restricted control internal forces. The paper presents some results on this problem, which is very actual for energy supply of the communication mini-satellites with plasma thrusters at initial mission modes.

Attitude & Orbit Digital and Pulse-Width Control of Large-Scale Communication Spacecraft

Abstract New results on both the attitude gyromoment digital control and the orbit electro-reaction pulse-width control of the large-scale communication satellites with precise pointing the large-scale flexible antennas, are presented.

Guidance and Robust Gyromoment Attitude Control of a Large-scale Communication Satellite

Abstract New approach for modelling a physical hysteresis damping the flexible spacecraft structure oscillations, is developed. New results on communication satellite attitude guidance and digital robust control with precise pointing the large-scale flexible antennas, are presented.

ROBUST CONTROL OF A SPACECRAFT RESPINUP BY WEAK INTERNAL FORCES

Abstract Recently, space science and engineering advanced new problem before theoretical mechanics and motion control theory: a spacecraft directed respinup by the weak restricted control internal forces. The paper presents some results on this problem, which is very actual for energy supply of the communication mini-satellites with plasma thrusters at initial mission modes.

Nonlinear Dynamics of Gyromoment Attitude Control System at Communication Satellite Sesat

Abstract New research and developments on attitude determination, nonlinear dynamics of precise gyromoment control and antenna pointing by the GEO communication spacecraft Sesat developed by Russian State Space Research & Production Association Applied Mechanics (NPO PM) in cooperation with Alcatel Space Industries (ASI, France) on the order of Eutelsat, are presented.

Nonlinear Dynamics of Gyromoment Attitude Control and Precise Antenna Pointing by the Sesat Spacecraft

Abstract New research and developments on attitude determination, nonlinear dynamics of precise gyromoment control and antenna pointing by the GEO communication spacecraft Sesat developed by Russian State Space Research & Production Association Applied Mechanics (NPO PM) in cooperation with Alcatel Space Industries ( ASI , France) on the order of Eutelsat , are presented.

Guidance and adaptive-robust attitude & orbit control of a small information satellite

We consider a small information satellite which may be placed on an orbit with altitude from 600 up to 1000 km. The satellite attitude and orbit control system contains a strap-down inertial navigation system, cluster of four reaction wheels, magnetic driver and a correcting engine unit with eight electro-reaction engines. We study problems on design of algorithms for spatial guidance, in-flight identification and adaptive-robust control of the satellite motion on sun-synchronous orbit.