 | | Mechanics of Solids
A Journal of Russian Academy of Sciences | | Founded
in January 1966
Issued 6 times a year
Print ISSN 0025-6544
Online ISSN 1934-7936 |
Archive of Issues
| Total articles in the database: | | 12804 |
| In Russian (Èçâ. ÐÀÍ. ÌÒÒ): | | 8044
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| In English (Mech. Solids): | | 4760 |
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| Ya.G. Sapunkov and Yu.N. Chelnokov, "Pulsed Optimal Spacecraft Orbit Reorientation by Means of Reactive Thrust Orthogonal to the Osculating Orbit. II," Mech. Solids. 54 (1), 1-18 (2019) |
| Year |
2019 |
Volume |
54 |
Number |
1 |
Pages |
1-18 |
| DOI |
10.3103/S0025654419010011 |
| Title |
Pulsed Optimal Spacecraft Orbit Reorientation by Means of Reactive Thrust Orthogonal to the Osculating Orbit. II |
| Author(s) |
Ya.G. Sapunkov (Institute of Precision Mechanics and Control Problems of the Russian Academy of Sciences, ul. Rabochaya 24, Saratov, 410028 Russia)
Yu.N. Chelnokov (Institute of Precision Mechanics and Control Problems of the Russian Academy of Sciences, ul. Rabochaya 24, Saratov, 410028 Russia; Chernyshevskii Saratov State University, ul. Astrakhanskaya 83, Saratov, 410012 Russia, chelnokovyun@gmail.com) |
| Abstract |
A new theory and a new algorithm for numerical solution of the problem of optimal spacecraft orbit reorientation by means of a pulsed (large) thrust, orthogonal to the osculating orbit plane, for a non-fixed number of thrust impulses are set out in a strict non-linear formulation. As a control, a vector of reactive acceleration from engine thrust is used. The combined functional is minimized, equal to the weighted sum of the reorientation time and the reactive acceleration impulse (characteristic speed) during the time of the spacecraft orbit reorientation (a special case of this functional is the case of minimization of the characteristic speed). To construct the theory, a solution for the problem of optimal spacecraft orbit reorientation in continuous formulation (using limited (low) thrust) is described in the first part of this article.
It is shown that the problem of optimal impulse spacecraft orbit reorientation in the case when optimal control consists of two reactive acceleration impulses, applied to the spacecraft at initial and final moments of time of motion, is solved analytically. Examples of numerical solution of the problem of optimal impulse spacecraft orbit reorientation are given, illustrating the capabilities of the proposed method. |
| Keywords |
spacecraft orbit, optimal orbit reorientation, reactive acceleration, orthogonal to the orbit plane, quaternion |
| Received |
09 February 2016 |
| Link to Fulltext |
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