Orbit design for the Spektr-R spacecraft of the ground-space interferometer |
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Authors: | N S Kardashev B B Kreisman A V Pogodin Yu N Ponomarev E N Filippova A I Sheikhet |
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Institution: | 1. Astrospace Center, Lebedev Physical Institute, Russian Academy of Sciences, Moscow, Russia 2. Lavochkin NPO (Science and Production Corporation), Khimki, Moscow oblast, Russia
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Abstract: | In order to carry out tasks of the RadioAstron mission, a high-apogee orbit was designed. On average, the period of its satellite’s orbit around the Earth is 8.5 days with evolution due to gravitational perturbations produced by the Moon and the Sun. The perigee and apogee of this orbit vary within the limits 7500–70000 km and 270000–333000 km, respectively. The basic evolution of the orbit represents a rotation of its plane around the line of apsides. Over 3 years, the plane normal to the orbit draws on the celestial sphere an oval with a semi-major axis of about 150° and semi-minor axis of about 45°. |
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