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What is the tangential velocity of a satellite moving in a circular orbit at a height of 5250 km above the surface of Earth? The standard gravitational parameter of Earth is 398,600 km3/s2. The radius of Earth is 6378 km.

Correct Answer: 5.85 km/s
Given, Distance between Earth and satellite (r) = 5250 + 6378 = 11,628 km Standard gravitational parameter of Earth (μ) = 398,600 km3/s2 Since, gravitational attraction between Earth and satellite = centrifugal force of the satellite, we can derive, Tangential velocity of satellite (V) = (μ/r)1/2 = (398,600/11,628)1/2 = 5.85 km/s

If the standard gravitational parameter of earth, μ is 398,600 km3/s2 and the radius of earth is 6378 km, what is the period of a satellite revolving around earth in a circular orbit 500 kms above the surface of the earth?

Consider the following statements.
1. The time period of satellite does not depend on the radius of the orbit.
2. The orbital velocity is inversely proportional to the square root of the radius of the orbit.
3. The orbital velocity of a satellite increases with the radius of the orbit.
Which of the statement(s) given above is/are correct?

What is the specific energy of a spacecraft in an elliptical orbit around earth? Given, apogee and perigee distance from the surface of earth are 6250 km and 525 km respectively. The radius and standard gravitational parameter of earth are 6378 km and 398,600 km3/s2.

How long does it take for a satellite to travel between perigee and apogee? Apogee and perigee altitude from surface of the earth is 900 km and 400 km respectively. Earth’s radius and standard gravitational parameter is 6378 km and 398,600 km3/s2 respectively.

The standard parameter of Earth is 398,600 km3/s2, distance between Earth and Mars is 225 x 106 km, force of gravitational attraction between Earth and Mars is 6.39 x 1023 N. What is the standard gravitational parameter of Mars? Given, universal gravitational constant is 6.67408 × 10-11 m3 kg-1 s-2.

A lunar lander is leaving earth on a hyperbolic trajectory with a perigee altitude of 900 km from earth’s surface. The perigee velocity of the trajectory is 14.3 km/s. What is the hyperbolic excess speed? The radius of earth is 6378 km and its gravitational parameter is 398,600 km3/s2.

What is the tangential velocity of a spacecraft around earth. Given, the orbit is circular, and the specific angular momentum of spacecraft is 57,112 km2/s. Standard gravitational parameter of earth is 398,600 km3/s2?

What is the velocity of a satellite orbiting around moon in a circular orbit of altitude 100 km from moon’s surface. Given, standard gravitational parameter of moon is 4903 km3/s2 and radius of moon is 1738 km.

How much is the delta-v required to put a satellite in circular orbit of altitude 3,000 km over Mars surface. The satellite is travelling initially at 27 km/s. Radius and gravitational parameter of Mars are 3,389.5 km and 42,828 km3/s2.

What is the radial velocity of a spacecraft travelling in a parabolic orbit with a true anomaly of 0.52 rad? Given, the orbit is circular, and the specific angular momentum of spacecraft is 57,112 km2/s. Standard gravitational parameter of earth is 398,600 km3/s2?