A satellite is orbiting a circular orbit at an altitude of 900 ??, at which atmosphere density is5.46 × 10−13??/?3. The satellite has mass 150??, cross sectional area 1.50?2, and drag coefficient 2.a) Calculate the rate of change of orbit radius ??/?? in units of ?/?.b) Make an estimate of the time (in years) that will take the satellite to reach the Earth.You can also find the question in the image below Example 4. A satellite is orbiting a circular orbit at an altitude of 900 km, at which atmosphere density is5.46 x 10-13 kg/m³. The satellite has mass 150kg, cross sectional area 1.50m², and drag coefficient 2.a) Calculate the rate of change of orbit radius da/dt in units of m/s.b)Make an estimate of the time (in years) that will take the satellite to reach the Earth.

Answered: Image /qna-images/answer/2ae01402-ccf8-46cb-bbc8-1f6a4f7caa12.jpg

Example 4. A satellite is orbiting a circular orbit at an altitude of 900 km, at which atmosphere density is 5.46 x 10-13kg/m³. The satellite has mass 150kg, cross sectional area 1.50m², and drag coefficient 2. a) Calculate the rate of change of orbit radius da/dt in units of m/s. b) Make an estimate of the time (in years) that will take the satellite to reach the Earth.

Example 4. A satellite is orbiting a circular orbit at an altitude of 900 km, at which atmosphere density is 5.46 x 10-13kg/m³. The satellite has mass 150kg, cross sectional area 1.50m², and drag coefficient 2. a) Calculate the rate of change of orbit radius da/dt in units of m/s. b) Make an estimate of the time (in years) that will take the satellite to reach the Earth.

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