Yevgeny Somov

Guidance and Robust Gyromoment Precise Attitude Control of Agile Observation Spacecraft

Some problems on guidance and robust gyromoment attitude control of agile spacecraft for remote sensing the Earth surface are considered. Elaborated methods for dynamic research of the spacecraft programmed angular motion at principle modes under external and parametric disturbances, partial discrete measurement of the state and digital control of the gyro moment cluster by the few-excessive gyrodine schemes, are presented.

An expert system for design of spacecraft attitude control systems

In the aspect of further development of investigations in automatic theorem proving, complicated systems modeling and analysis of their control systems and making such systems more intelligent, we consider problems of elaboration of a hybrid expert system (ES) for design of gyromoment system of attitude control for spacecraft.

Nonlinear dynamics and control of a wind-milling gyroplane rotor

Mathematical models of auto-rotation and flapping the wind-milling rotor have been carried out. Their approximate analytical solutions have been obtained. Software allowing one to simulate and study a rotor dynamics have been created. Major physical features on the forced flexible oscillations of the wind-milling rotor in the flapping plane have been investigated. Results obtained have successfully been applied to designing the Irkutsk A-002 gyroplane main rotor.

In-flight Calibration of Attitude Determination Systems for Information Mini-satellites

Abstract Contemporary information mini-satellites have general mass up to 500 kg and are placed onto the orbit altitudes from 500 up to 1500 km. For such spacecraft some principle problems on precise attitude determination and in-flight calibration are considered and elaborated methods are presented for their solving. Original multiple discrete algorithms for filtering, integration and calibration of a strapped-down inertial navigation system for precise determining the spacecraft attitude, are presented. This system contains electrostatic micro-accelerometer, an inertial measurement unit based on the gyro sensors, an astronomical system based on star trackers, multi-head Sun sensor and magnetic sensor, the that are fixed to the spacecraft body.

Optimizing the Guidance and Control Laws at the Space Optoelectronic Observation

Abstract Obtained in the space photos a ground resolution depends on a spacecraft (SC) spatial angular motion during optoelectronic survey. The paper examines case of optimal equalization of an image longitudinal velocity in the focal plane of telescope and tackles the problem of defining initial azimuth of the scanning survey under the condition of minimizing quadratic functional of image cross velocity values on the left and right edges of the CCD linear array. Results of a simulated survey of random surface object are presented, and the change of initial azimuth value for various survey angles within the swath is examined. The paper presents a brief description of developed software for designing the space telescope characteristics and gives recommendations for its application.

In-orbit Calibration of Attitude Determination Systems for Land-survey Micro-satellites

Abstract Contemporary land-survey micro-satellites have general mass up to 100 kg and are placed on the orbit altitudes from 600 up to 800 km. For such spacecraft some principle problems on attitude determination, in-flight calibration and alignment are considered and elaborated methods are presented for their solving. We present discrete algorithms for calibration and alignment of the low cost strap-down inertial navigation systems with correction by signals from multi-head Sun sensor, magnetic sensor and the GPS/GLONASS satellites.

Postgraduate Education and New Challenges on Stability and Adaptive-Robust Control in Aerospace

Abstract Traditions on postgraduate education in Russia and France are considered. New challenges on stability and adaptive-robust control in aerospace engineering are presented.

Nonius Guidance and Robust Image Motion Stabilization of a Large Space Astronomical Telescope

Abstract Some problems on a nonius guidance, robust attitude control and long-time image motion stabilization of a large space astronomical telescope are considered. Elaborated methods for dynamic research under external and parametric disturbances, partial discrete measurement of the state, digital control of the gyro moment cluster and a fine piezo-driver, are presented.

NONLINEAR DYNAMICS AND ROBUST CONTROL OF A GYROPLANE ROTOR

Abstract Mathematical models of a gyroplane rotor have been carried out. Their approximate analytical solutions have been obtained. Software allowing one to simulate and study a rotor dynamics has been created. Major physical features on the forced flexible oscillations of the rotor have been investigated. The results obtained have successfully been applied to design the A-002 gyroplane rotor.

Economical digital and pulse-width control of land-survey mini-satellites

Methods for attitude & orbit control of the information satellites with economical expending of the energy and fuel onboard resources are presented. We consider the land-survey mini-satellites with an orbit altitude from 600 up to 800 km when their lifetime must be up to 10 years and economical control is actual problem.