Äîêóìåíò âçÿò èç êýøà ïîèñêîâîé ìàøèíû. Àäðåñ îðèãèíàëüíîãî äîêóìåíòà : http://www.kiam1.rssi.ru/pubs/prep_2013_006.pdf Äàòà èçìåíåíèÿ: Tue Oct 8 14:40:35 2013 Äàòà èíäåêñèðîâàíèÿ: Thu Feb 27 19:55:36 2014 Êîäèðîâêà:

. ..

.. , .. , .. , .. , .. , .. , .. , ..

- L2 -

-- 2013


L2 -. ­ - . ­ - ( ) . . . , -. - , , . -. «-» «». : -, L2, , -, . ABSTRACT This work covers ballistic design of the spacecraft transfer to the vicinity of the Sun-Earth system L2 point and halo orbit motion in this area. The following methods and calculation algorithms are described: the algorithm building one impulse transfer trajectories starting at the LEO and ending at the halo orbit implying a swing by maneuver or not. the algorithm calculating the stationkeeping impulses, needed for the transfer to the halo orbit and the for the long term halo orbit motion. For calculation of one impulse flights from the Earth to the halo orbit (with the help of a swing by maneuver or without it) the initial approximation construction algorithm has been implemented. These approximations are calculated by means of two variables' function isolines construction and analysis. The transfer trajectory pericentre height above the Earth surface is considered to be such a function. The arguments of this function are the special parameters describing the halo orbit. The described algorithm provides halo orbits with the given geometrical dimensions in the ecliptics plane and in plane orthogonal to it. The characteristic velocity costs needed for the stationkeeping have been evaluated. These methods were used for construction of the nominal orbits for the "Spectr -RG" and "Millimetron" spacecrafts. Key words: halo orbits, L2 point, isoline method, Spectr-RG, Millimetron.


3

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17

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18




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19

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20

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21

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22

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23

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24

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25



B

A

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, 2014 . 7. 30.09.2014. , , /c , . , . , . , . , . , , X Y Z VX VY VZ 2 3 6 0 4 6 0 1 2 1 014/09/30 04:22:30.000 .265 86.911532 .990397 7.633 5.576533 .218384 360.848407 8.837 92.803

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26

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27

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-, , «». 13. ( 5, ). , 2018/09/15 16:08:31.749 , . 6.587983 0.002851 , . 51.609 , . 88.692813 , . 0.191067 , . 0.228626 , 198.683 , 84.178 14. . , , /c , . , . , . , . , . , , 2 3 7 0 5 6 0 1 1 3 018/09/15 17:05:00.000 .202 12.251380 .990733 1.472 9.238427 .222093 411.524394 98.883 12.243


28

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29



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30

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31

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32

«» , - 800 . . - , , L2. , - L2 600 . . 1. .., .., .. L2 ­ // . .. , 2012, 65. URL: http://keldysh.ru/papers/2012/prep2012_65.pdf 2. .., .., .. L2 ­ // . .. , 2012, 66. URL: http://keldysh.ru/papers/2012/prep2012_66.pdf 3. .., .., .. ­ ­ - L2 ­ // ­ 1992. ­ . 30. 4. ­ .435­454. 4. .. . ­ .: , 1978. ­ 312 . 5. .., .., .. - L2 ­ // . . 1987. . XXV. 2. . 163­185. 6. Eismont N., Dunham D., Jen S.-C., Farquhar R. Lunar Swingby as a Tool for Halo-Orbit Optimization in Relict-2 Project // Proceeding of the ESA Symposium on Spacecraft Flight Dynamic, Germany, 30-4 October, 1991 (ESA SP-326, December 1991), pp.435-439. 7. .., .., .. L2 ­ ( «-2») // . . 1993, . 31, 5. .3­20. 8. .. . . ­ : , 1978. ­ 456 . 9. . . . ­ : , 1982. ­ 656 . 10. .. «» . // ­ 2011. ­ . 48. 3. ­ . 271-278. 11. ., ., . . ­ .: , 1985.