The total energy of a satellite in orbit is given by the formula:

E = -GMm/2r

Where:
E is the total energy of the satellite,
G is the gravitational constant,
M is the mass of the Earth,
m is the mass of the satellite, and
r is the radius of the orbit.

The radius of the orbit for a geostationary satellite is given by:

r = (GMt^2/4π^2)^(1/3)

Where:
t is the period of the satellite (which is 24 hours for a geostationary satellite).

Substituting the second equation into the first gives the total energy of a geostationary satellite in terms of G, M, m, and t:

E = -GMm/2((GMt^2/4π^2)^(1/3))

This simplifies to:

E = -GMm/(2^(4/3)(GMt^2/4π^2)^(1/3))

This is the total energy of a geostationary satellite in orbit around the Earth.

Question

The total energy of a satellite in orbit is given by the formula:

E = -GMm/2r

Where:
E is the total energy of the satellite,
G is the gravitational constant,
M is the mass of the Earth,
m is the mass of the satellite, and
r is the radius of the orbit.

The radius of the orbit for a geostationary satellite is given by:

r = (GMt^2/4π^2)^(1/3)

Where:
t is the period of the satellite (which is 24 hours for a geostationary satellite).

Substituting the second equation into the first gives the total energy of a geostationary satellite in terms of G, M, m, and t:

E = -GMm/2((GMt^2/4π^2)^(1/3))

This simplifies to:

E = -GMm/(2^(4/3)(GMt^2/4π^2)^(1/3))

This is the total energy of a geostationary satellite in orbit around the Earth.

Knowee AI · Accepted Answer

The total energy of a satellite in orbit is given by the formula:

E = -GMm/2r

Where:
E is the total energy of the satellite,
G is the gravitational constant,
M is the mass of the Earth,
m is the mass of the satellite, and
r is the radius of the orbit.

The radius of the orbit for a geostationary satellite is given by:

r = (GMt^2/4π^2)^(1/3)

Where:
t is the period of the satellite (which is 24 hours for a geostationary satellite).

Substituting the second equation into the first gives the total energy of a geostationary satellite in terms of G, M, m, and t:

E = -GMm/2((GMt^2/4π^2)^(1/3))

This simplifies to:

E = -GMm/(2^(4/3)(GMt^2/4π^2)^(1/3))

This is the total energy of a geostationary satellite in orbit around the Earth.

Radius of the orbit of Geo statimary satellite of mass m is r, If mass of the earth is M and theradius is R, the total energy of the satellite at the orbit is,

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