  Journal of Applied Mathematics and Mechanics Russian Academy of Sciences   Founded
in January 1936
(Translated from 1958)
Issued 6 times a year
ISSN 00218928 (print version) 
Archive of Issues
Total articles in the database:   2048 
In Russian (ΟΜΜ):   1249

In English (J. Appl. Math. Mech.):   799 

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Yu.N. Chelnokov, "Optimal reorientation of a spacecraft's orbit using a jet thrust orthogonal to the orbital plane," J. Appl. Math. Mech. 76 (6), 646657 (2012) 
Year 
2012 
Volume 
76 
Issue 
6 
Pages 
646657 
Title 
Optimal reorientation of a spacecraft's orbit using a jet thrust orthogonal to the orbital plane 
Author(s) 
Yu.N. Chelnokov (Saratov, Russia, chelnokovyun@gmail.com) 
Abstract 
The problem of the optimal control of the orientation of a spacecraft's orbit using magnitudeconstrained control, i.e., the jet thrust vector perpendicular to the orbital plane, is considered. Under such control the spacecraft's orbit rotates in space as an unalterable (nondeformable) figure. A combined functional, equal to the weighted sum of the reorientation time and an integral quadratic (with respect to the control) quality functional, or equal to the weighted sum of the reorientation time and the control momentum (the characteristic velocity) during reorientation of the orbit serves as an optimality criterion. A quaternion differential equation of the orientation of the orbital system of coordinates and the maximum principle are used to solve the problem. A differential boundaryvalue problem with a dimension of ten is formulated to construct the optimal control and the optimal trajectory for reorientating the orbit. Control laws that satisfy the necessary optimality conditions are obtained (in the form of functions of conjugate variables). Quaternion and scalar first integrals of the equations of the problem are found, and transversality conditions that do not contain Lagrange undetermined multipliers are devised. It is shown that the original boundaryvalue problem reduces (with simultaneous simplification of the equations of the problem) to a new boundaryvalue problem of a smaller dimension equal the three, whose equations for a circular orbit in the case of maximum speed are integrated in trigonometric functions. Such a reduction is possible owing to the selfconjugation of the quaternion differential equation of the orientation of the orbital system of coordinates of the spacecraft and the use of a new quaternion variable that is related to the quaternion first integral by a rotational transformation. It is found that the switching function of the control is described by a system of three firstorder differential equations, which reduce to a linear inhomogeneous secondorder equation with constant coefficients for a circular orbit in the timeoptimal case and to the Duffing equation in the case of an integral quadratic quality functional. It is also shown that for a circular orbit in the timeoptimal case the problem reduces to solving a thirdorder nonlinear algebraic system. An example of a numerical solution of the problem is presented. 
Received 
26 November 2010 
Link to Fulltext 
http://www.sciencedirect.com/science/article/pii/S0021892813000245 
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