The formula to calculate the Time Period of Satellite is:
\[ T = \frac{(2 \pi)}{R_{Earth}} \sqrt{\frac{(R_{Earth} + h)^3}{g}} \]
Time period of Satellite is the time taken by the satellite to make one full orbit around any object. Satellite Altitude is the perpendicular distance from the vertex of the triangle to the opposite side.
Let's assume the following values:
Using the formula:
\[ T = \frac{(2 \pi)}{R_{Earth}} \sqrt{\frac{(R_{Earth} + 18900000)^3}{g}} = 40007.8482338525 \]
| Satellite Altitude (h) | Time Period of Satellite (T) |
|---|---|
| 18000000 | 24,063,046.869549654424191 |
| 18100000 | 24,263,779.363665804266930 |
| 18200000 | 24,465,066.940504126250744 |
| 18300000 | 24,666,908.073535136878490 |
| 18400000 | 24,869,301.248754832893610 |
| 18500000 | 25,072,244.964514348655939 |
| 18600000 | 25,275,737.731352798640728 |
| 18700000 | 25,479,778.071833301335573 |
| 18800000 | 25,684,364.520382076501846 |
| 18900000 | 25,889,495.623130518943071 |
| 19000000 | 26,095,169.937760218977928 |
