Sergey 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.

Guidance and robust gyromoment attitude control of agile flexible remote sensing spacecraft

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

Optimization of guidance and attitude control for 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 orbital altitude from 600 up to 800 km when their lifetime must be up to 10 years and economical control is actual problem. We also consider the optimization problems on attitude guidance of such spacecraft, discrete filtering of measured signals, economical control with respect to the onboard energy and fuel resources and present elaborated methods for their solving.

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.

Methods for nonlinear analysis, simulation and animation of land-survey spacecraft guidance

Obtained in the space photos a ground resolution depends on a spacecraft spatial angular motion during optoelectronic survey. The paper studies 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 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 also a brief description of developed software for designing the space telescope characteristics, simulation and animation of the land-survey spacecraft spatial motion and gives recommendations for its applications.

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.

Economical attitude and orbit control of information satellites by electromechanical, magnetic and plasma drivers

Methods for attitude & orbit control of the information satellites with economical expending of the onboard energy and fuel resources are presented. We consider small information spacecraft with an orbit altitude from 550 up to 1500 km when its lifetime must be up to 10 years and economical control is actual problem.

Pulse-width Attitude Control of Large-scale Information Satellite at Service Modes

Abstract Problems of nonlinear modeling, dynamic analysis and simulation of spatial motion by the large-scale information satellites with a flexible weak damping structure are considered. Obtained results on a multi-rate filtering of measurements and pulse-width control of the jet engines at the satellites’ service modes are presented. Results on analysis of the spacecraft nutation and flexible oscillations, and guidelines according to a logic in sequence of the gyrodines rotors spin-up, are also represented.

Simulation Technologies for Long-Term Target Planning and In-Flight Management of the Spacecraft Control Systems

Abstract Obtained in the space radio- and optic-photos a ground resolution depends on a spacecraft (SC) spatial angular motion during radio- and optic-electronic survey. The paper examines case of optimal equalization of an image longitudinal velocity and tackles the problem of defining initial azimuth of the scanning survey under the condition of minimizing quadratic functional of radio- or optic-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, simulation and animation of the land-survey SC spatial motion and gives recommendations for its applications.

Methods for attitude guidance and precise robust gyromoment control of large-scale agile observation spacecraft

Problems on guidance and robust gyromoment attitude control of agile information satellite 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 excessive gyrodine schemes, are presented.