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A satellite is in an elliptical orbit around the Earth with aphelion of 6R and perihelion of 2R where R = 6400 Km is the radius of the Earth. Find eccentricity of the orbit. Find the velocity of the satellite at apogee and perigee. What should be done if this satellite has to be transferred to a circular orbit of Radius 6R ?
[ G = 6.67 × 10⁻¹¹ SI units and M = 6 × 10²⁴ Kg ]
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❏ Physics Newton
❏ Other best users
A satellite is in an elliptical orbit around the Earth with aphelion of 6R and perihelion of 2R where R = 6400 Km is the radius of the Earth. Find eccentricity of the orbit. Find the velocity of the satellite at apogee and perigee. What should be done if this satellite has to be transferred to a circular orbit of Radius 6R ?
[ G = 6.67 × 10⁻¹¹ SI units and M = 6 × 10²⁴ Kg ]
◆Only hand typed answers
◆No spams
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