The orbit of a certain satellite has a semi-major axis of m and an eccentricity of 0.20

MATHEMATICS · Single correct · AP · AP Precalculus · Functions with Parameters, Vectors, and Matrices · Functions with Parameters, Vectors, and Matrices

Problem

The orbit of a certain satellite has a semi-major axis of 1.5×1071.5 \times 10^7 m and an eccentricity of 0.20. Its perigee (minimum distance) and apogee (maximum distance) are respectively: (A) 1.2×1071.2 \times 10^7 m, 1.8×1071.8 \times 10^7 m (B) 3.0×1063.0 \times 10^6 m, 1.2×1071.2 \times 10^7 m (C) 9.6×1069.6 \times 10^6 m, 1.0×1071.0 \times 10^7 m (D) 1.0×1071.0 \times 10^7 m, 1.2×1071.2 \times 10^7 m

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