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Your search keyword '"Ishkov, Sergey A."' showing total 17 results
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17 results on '"Ishkov, Sergey A."'

2. Matrix method for the multi salesmen problem (TSP) with several vehicles

Author

Ishkov, Sergey and Ishkova, Elena

Subjects
Computer Science - Data Structures and Algorithms
Abstract

In this paper discussed procedure of separation of the original problem with several vehicles to a number of simpler problems with one vehicle which based on the matrix approach., Comment: 10 pages with 1 figure

Published
2011

14. Formation Algorithms of Sequential Control for Spacecraft Rendezvous with Low-Thrust.

Author

Ishkov, Sergey A., Khramov, Andrew A., and Filippov, Gregory A.

Subjects
*SEQUENTIAL analysis, *SPACE vehicles, *THRUST vector control, *EQUATIONS of motion, *ANALYTICAL solutions
Abstract

The problem of control program formation during orbital rendezvous maneuver at low Earth orbits is studied. Rendezvous of two spacecraft are considered. The first is an active spacecraft, equipped with low-trust engines and, the second, is passive spacecraft. Using the linearized equations of motion, the secular and periodic components of relative motion are explicitly allocated. The control program is a consistent correction of the relative motion parameters to the specified values with transversal and binormal trust direction. During formation of the control program, the analytical solutions and the iterative procedure are used. The numerical simulation of rendezvous maneuver is carried out. [ABSTRACT FROM AUTHOR]

Published
2018
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15. Nominal control program in problem of far rendezvous at geostationary orbit with low transversal thrust.

Author

Ishkov, Sergey A., Filippov, Gregory A., and Fadeenkov, Pavel V.

Subjects
*THRUST vector control, *PROBLEM solving, *GEOSTATIONARY satellites, *LINEAR systems, *OPTIMAL control theory
Abstract

The air of this research is obtaining of nominal control programs in problem of far rendezvous at geostationary orbit with low transversal thrust. The problem of control program designing in linear approximation divided to control in orbital plane and control in lateral direction. Motion in orbital plane is separate to secular and periodic. Using Pontriagins maximum principle, the structure of optimal control program with transversal thrust is determined. Base on optimal control program, the simple analytical control programs is obtained. Numeric simulation of rendezvous transfer with obtained control programs is carried out. [ABSTRACT FROM AUTHOR]

Published
2018
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16. Low thrust spacecraft motion control with simultaneous changes in main orbital elements.

Author

Fadeenkov, Pavel and Ishkov, Sergey

Subjects
*SPACE vehicles, *THRUST, *MOTION, *STRUCTURAL frames, *ORBITS (Astronomy)
Abstract

The problem of forming a nominal optimal program for controlling the direction of the low-thrust vector of a spacecraft for a significant change in the elements of the spatial orbit is considered. A scheme for the joint change of the elements of the orbit within the framework of a simple structure for controlling the thrust vector on the orbit is proposed. [ABSTRACT FROM AUTHOR]

Published
2019

17. A Disposal of the Space Debris with Special Spacecraft Debris Collector using Low Trust.

Author

Ishkov, Sergey A. and Filippov, Gregory A.

Subjects
*SPACE debris, *SPACE vehicles, *PROPULSION systems, *DRAG (Aerodynamics), *THRUST faults (Geology)
Abstract

the aim of this work is to study the possibility of the disposal of the space debris in the dense layers of the Earth's atmosphere. We use information about the fragments of the space debris location that stored in NORAD databases. There two types of the orbits of the space debris are explored: the high elliptical orbit and the circular orbits. The algorithm of the operation of the utilization of the fragments of the space debris in the dense layers of the Earth's atmosphere using the special spacecraft debris collector is composed. The spacecraft debris collector must be equipped with electro propulsion engines with low-thrust. The mathematical model of the plane motion of the spacecraft debris collector, in the form of the system of osculating elements, is composed. Problem of the descent of the fragments of the space debris reduced to the problem of the reducing of the height of the perigee of elliptical orbit. Obtained the locally - optimal control program of the orientation of the thrust vector. Using the L.S. Pontryagin's maximum principle, we solved the boundary value problem of the optimal control (decrease) of the perigee of the elliptical orbit. The results of the parametric study of the problem in the space of the initial orbits and the acceleration traction of the electro propulsion engines is shown. Numerical simulation of the space debris reduction from the low circular orbits is performed. Determined the number of revolutions passed a fragment of the space debris around the Earth during braking due to aerodynamic drag. Calculated the estimates of the gains of the characteristic velocity to perform the operation. [ABSTRACT FROM AUTHOR]

Published
2015

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