Period is 24 hrs. Convert that to seconds.
The distance they travel in one period is 2PI*radius. Find the radius of the Earth in meters, then add the altitude.
veloicty=distance/period
The distance they travel in one period is 2PI*radius. Find the radius of the Earth in meters, then add the altitude.
veloicty=distance/period
v = √(G * M / r)
Where:
- v is the speed of the satellite in orbit,
- G is the gravitational constant (approximately 6.67430 × 10^-11 m^3 kg^-1 s^-2),
- M is the mass of the Earth (approximately 5.972 × 10^24 kg),
- r is the distance from the center of the Earth to the satellite.
The satellite in question is a synchronous satellite, which means it stays fixed in a particular position relative to the Earth's surface. This implies that the satellite's orbit has a radius equal to the Earth's radius.
The Earth's radius is approximately 6,371 kilometers (6.371 × 10^6 meters). We can use this value as the distance, r.
Substituting the known values into the equation, we have:
v = √(6.67430 × 10^-11 * 5.972 × 10^24 / 6.371 × 10^6)
Calculating this expression, we find:
v ≈ 3,070 meters per second (m/s)
Therefore, the speed of the satellite in orbit is approximately 3,070 m/s.
v = √(G * M / r)
Where:
v = Velocity of the satellite in m/s
G = Universal gravitational constant (6.6743 × 10^-11 N m^2/kg^2)
M = Mass of the Earth (5.972 × 10^24 kg)
r = Distance from the center of the Earth to the satellite's orbit (radius of the orbit)
Since a synchronous satellite is in geostationary orbit, it orbits at a distance of approximately 42,164 km (or 26,199 miles) from the center of the Earth.
First, let's convert the distance from km to meters:
r = 42,164 km = 42,164,000 meters
Now we can substitute the values into the formula and calculate the velocity:
v = √(G * M / r)
v = √((6.6743 × 10^-11 N m^2/kg^2) * (5.972 × 10^24 kg) / 42,164,000 meters)
By plugging in the values and solving the equation, you will obtain the velocity of the satellite in its orbit around the Earth.