The orbit of a certain a satellite has a semimajor axis of 1.5 * 10⁷ m and an eccentricity of 0.20.Its perigee (minimum distance)and apogee (maximum distance)are respectively: A)1.2 x 10⁷ m, 1.8 x10⁷ m B)3.0 x 10⁶ m, 1.2 x10⁷ m C)6.0 x10⁶ m, 9.0 x 10⁶ m D)1.0x 10⁷ m, 1.2 x10⁷ m E)9.6 x10⁶ m, 1.8x10⁷ m

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Quizplus · Accepted Answer

The perigee and apogee distances can be calculated using the semi-major axis (a) and the eccentricity (e) with the formulas: perigee = a(1 - e) and apogee = a(1 + e). Substituting the given values, a = 1.5 x 10^7 m and e = 0.20, we get perigee = 1.5 x 10^7 x (1 - 0.20) = 1.2 x 10^7 m and apogee = 1.5 x 10^7 x (1 + 0.20) = 1.8 x 10^7 m.

The Orbit of a Certain a Satellite Has a Semimajor