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Електронний архів Житомирського державного технологічного університету
View Archive Info| Field | Value | |
| Title |
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Method for orientation of artificial Earth satellites |
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| Creator |
?????????, ????? ?????????
????????, ?????? ??????????? |
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| Description |
?????? ?????????? ??????? ?????????? ????? ??????? ? ????, ?? ?????????? ???????????? ?????????? ????????? ?????? ?????????? ??????? ?? ????????????? ???? ? ??????? ???????? ??????. ????? ????? ????????? ?????????? ??????????? ?????????? ????????? ?????? ?????????? ???????. ???? ????????? ??????? ???????? ???????????? ????????????? ???? ?? ???? ?????????, ??? ?????????????? ??? ????????? ??????????? ?????????? ???????????? ??????????? ?????????? ?????? ????????????? ????. ????? ?? ???????????? ??????????? ?????????? ?????? ?????????? ??????? ??????????? ????????? ???????? ???????????? ??????????? ??????? ??? ???????? ??????????? ????????? ???? ????????? ????????? ?? ??????. ???? ?????????? ????????? ???????? ???????????? ??????????? ??????? ?????????? ?????? ??????????? ?????????? ????????, ?? ???????????? ?? ??????? ?????? ?????????, ?? ???? ??????????? ?????????? ?????? ??????? ??????? ? ??????????? ?????????????????. ????? ????, ?? ???????? ??????? ???? ??????? ??????, ????????? ???????? ???????????? ??????????? ???????. ??????? ?????????? ????????? ?????????? ?????????? ?? ?????????? ???????? ?????????? ??????? ?????????? ?????.
A method of orientation of artificial Earth satellites lies in that previously are calculated analytical predicted models of excitatory moment and geomagnetic field in given orbit sections. Then previously calculated analytical predicted model of excitatory moment are corrected. Then are measured current values of geomagnetic field strength along satellite axes that are used for current correction of previously calculated predicted model of geomagnetic field. Then according to corrected analytical predicted model of excitatory moment is calculated predicted value of accumulated kinetic moment for given future interval of time of revolution in orbit. If calculated predicted value of accumulated kinetic moment exceeds maximal allowable value, the calculation is made of this section of satellite orbit on which accumulated kinetic moment may be dropped with minimal energy consumption. When a satellite reaches this section of orbit, accumulated kinetic moment is dropped. Invention provides for reduction of energy consumption and increase precision of orientation of artificial satellites. |
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| Date |
2016-04-05T09:39:39Z
2016-04-05T09:39:39Z 2003 |
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| Type |
Other
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| Identifier |
http://eztuir.ztu.edu.ua/123456789/2530
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| Language |
uk
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| Relation |
56077;
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| Publisher |
????
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