Table of Contents
- 1 What is the orbital velocity of geostationary satellite?
- 2 What is the velocity of a satellite in orbit?
- 3 What is the orbital velocity of geostationary satellite class 11?
- 4 How is a satellite placed in a geostationary orbit?
- 5 What determines the apogee distance of an elliptical orbit?
- 6 What is the injection velocity at the perigee of the Earth?
What is the orbital velocity of geostationary satellite?
The aptly titled geosynchronous orbit is described in detail: “At an altitude of 124 miles (200 kilometers), the required orbital velocity is just over 17,000 mph (about 27,400 kph). To maintain an orbit that is 22,223 miles (35,786 km) above Earth, the satellite must orbit at a speed of about 7,000 mph (11,300 kph).
What is the velocity of a satellite in orbit?
Orbital velocity is the velocity needed to achieve balance between gravity’s pull on the satellite and the inertia of the satellite’s motion — the satellite’s tendency to keep going. This is approximately 17,000 mph (27,359 kph) at an altitude of 150 miles (242 kilometers).
What is the orbital velocity of geostationary satellite class 11?
About 3.08 km s-1 .
How do you get into a geostationary orbit?
To achieve a geostationary orbit, a geosynchronous orbit is chosen with an eccentricity of zero, and an inclination of either zero, right on the equator, or else low enough that the spacecraft can use propulsive means to constrain the spacecraft’s apparent position so it hangs seemingly motionless above a point on …
What is orbital velocity of a satellite?
The velocity which is required to keep the satellite revolves around its orbit is called orbital velocity of a satellite. It depends upon the radius of the orbit in which it revolves. Suppose a satellite of mass ‘m’ revolving around the earth at a height ‘h’ from the surface. Let v 0 be the orbital velocity of the satellite.
How is a satellite placed in a geostationary orbit?
In the second step, the satellite’s orbit is transformed from the low Earth orbit into an elliptical transfer orbit by maneuvers at perigee, in order to attain the apogee equal to geostationary (GEO) orbit’s radius. Finally, the satellite is placed from the elliptical transfer orbit to the final destination, as geostationary orbit [2,3].
What determines the apogee distance of an elliptical orbit?
The satellite injection point is at perigee, and the apogee distance attained in the elliptical orbit depends upon the injection velocity. The higher the injection velocity at perigee, the greater is the apogee distance, as schematically is presented in Figure 3.
What is the injection velocity at the perigee of the Earth?
For attitude of 600 km (perigee of 7000 km) the injection velocity at perigee point is 7.55 km/s and for attitude of 1200 km (perigee of 7600 km) the injection velocity at perigee is 7.24 km/s. As higher perigee (higher attitude) the lower injection velocity is required at perigee point. Obviously, for defined low Earth orbit the higher velocity