Methods of changing the halo orbit of the spacecraft in order to approach asteroids

Мұқаба

Дәйексөз келтіру

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Ашық рұқсат Ашық рұқсат
Рұқсат жабық Рұқсат берілді
Рұқсат жабық Рұқсат ақылы немесе тек жазылушылар үшін

Аннотация

The paper presents possible options for changing the orbit of the spacecraft operating near the Sun-Earth libration point for the purpose of the close passage of asteroids approaching the Earth. Two methods of constructing transfer trajectories to one or more celestial bodies are proposed: transferring the spacecraft from the initial bounded orbit in the vicinity of the L2 Sun – Earth libration point to the required one in the same vicinity and taking it to the Earth along the trajectory of an unstable manifold. Examples are provided in which the asteroids Apophis and 1997 XF11 are chosen as targets, whose trajectories will pass near the spacecraft in 2029 and 2028, respectively. It is shown that under the existing fuel cost restrictions, the spacecraft can be redirected to the targeted asteroids by the proposed methods. According to the calculations, in all cases the spacecraft does not leave the near-Earth space and therefore, during or after the passage of the asteroid, it can be used in solving other scientific problems.

Толық мәтін

Рұқсат жабық

Авторлар туралы

M. Pupkov

Space Research Institute; Samara University

Хат алмасуға жауапты Автор.
Email: m.pupkov@iki.rssi.ru
Ресей, Moscow; Samara

N. Eismont

Space Research Institute

Email: m.pupkov@iki.rssi.ru
Ресей, Moscow

O. Starinova

Samara University

Email: m.pupkov@iki.rssi.ru
Ресей, Samara

K. Fedyaev

Space Research Institute

Email: m.pupkov@iki.rssi.ru
Ресей, Moscow

Әдебиет тізімі

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Әрекет
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2. Fig. 1. Simulated trajectory of the SRG observatory

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3. Fig. 2. Trajectories of the SRG observatory and the Apophis asteroid

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4. Fig. 3. Scheme of the flight of the SRG spacecraft to the asteroid Apophis: a) movement before the moment of meeting the asteroid, b) movement before and after the flyby of the asteroid

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5. Fig. 4. Trajectories of the SRG observatory and the asteroid 1997 XF11

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6. Fig. 5. Scheme of the flight of the SRG spacecraft to the asteroid 1997 XF11: a) movement before the moment of meeting with the asteroid, b) movement before and after the flyby of the asteroid

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7. Fig. 6. Example of trajectories of unstable manifold

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8. Fig. 7. Scheme of the multi-impulse flight of the SRG spacecraft to the asteroid Apophis

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9. Fig. 8. Flight diagram of the SRG observatory to Apophis after the flyby of asteroid 1997 XF11

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