Question

A satellite in a circular orbit experiences a centripetal acceleration of (8.62 m/s²). The tangential speed of the satellite is (7.65 times 10³ m/s). What is the altitude of the satellite? ((r = 6.38 times 10⁶ m))

A. (6.38 times 10⁶ m)
B. (8.62 times 10³ m)
C. (7.65 times 10³ m)
D. (1.24 times 10⁷ m)

Answer 1

To find the altitude of a satellite in a circular orbit, we can use the centripetal acceleration and the tangential speed of the satellite. Using the formula altitude = (v² / a) - radius of the Earth, we can calculate the altitude by substituting the given values.

Step-by-step explanation:

In order to find the altitude of a satellite in a circular orbit, we need to use the centripetal acceleration and the tangential speed of the satellite. The centripetal acceleration is given as 8.62 m/s² and the tangential speed is given as 7.65 × 10³ m/s. To find the altitude, we can use the following formula:

r = v² / a

Where r is the radius of the orbit (altitude + radius of the Earth), v is the tangential speed, and a is the centripetal acceleration. Rearranging the formula, we get:

altitude = r - radius of the Earth

Substituting the known values, we have:

altitude = (v² / a) - radius of the Earth

Plugging in the values of v (7.65 × 10³ m/s), a (8.62 m/s²), and the radius of the Earth (6.38 × 10⁶ m), we can calculate the altitude of the satellite.