Mathematics

Problem

The orbit of a certain satellite has a semi-major axis of

1.5 \times 10^7

m and an eccentricity of 0.20. Its perigee (minimum distance) and apogee (maximum distance) are respectively: (A)

1.2 \times 10^7

1.8 \times 10^7

m (B)

3.0 \times 10^6

1.2 \times 10^7

m (C)

9.6 \times 10^6

1.0 \times 10^7

m (D)

1.0 \times 10^7

1.2 \times 10^7