Question

Difficulty: Very hardGravitational Field and Orbits

A satellite of mass 500 kg500\text{ kg} orbits a spherical planet of radius R=6.0×106 mR = 6.0 \times 10^6\text{ m} with surface gravitational acceleration g=10 m/s2g = 10\text{ m/s}^2. The satellite is transferred from an initial circular orbit of radius 2R2R to a higher circular orbit of radius 3R3R. What is the minimum energy required, in megajoules (MJ\text{MJ}), to perform this transfer?

Answer: 2500 MJ

Answer

The minimum energy required to perform the orbital transfer is 2500 MJ2500\text{ MJ}.
The minimum energy needed to move a satellite between circular orbits is equal to the change in its total mechanical energy (E=GMm2rE = -\frac{GMm}{2r}). Expressing GMGM as gR2gR^2, the energy difference between radii 2R2R and 3R3R simplifies to ΔE=gRm12\Delta E = \frac{gRm}{12}, which evaluates to 2500 MJ2500\text{ MJ}.

Step-by-Step Solution

1
Relate surface acceleration due to gravity to planet mass and radius.
GM=gR2GM = gR^2
At the planet's surface (r=Rr = R), gravitational acceleration is g=GMR2g = \frac{GM}{R^2}.
2
Formulate the total mechanical energy equation for a circular orbit.
E=GMm2r=gR2m2rE = -\frac{GMm}{2r} = -\frac{gR^2 m}{2r}
Total energy is kinetic energy GMm2r\frac{GMm}{2r} plus gravitational potential energy GMmr-\frac{GMm}{r}.
3
Calculate initial and final total energies.
E1=gRm4E_1 = -\frac{gRm}{4} and E2=gRm6E_2 = -\frac{gRm}{6}
Substitute the orbit radii r1=2Rr_1 = 2R and r2=3Rr_2 = 3R into the total energy equation.
4
Determine the net work required for the transfer.
ΔE=E2E1=gRm12\Delta E = E_2 - E_1 = \frac{gRm}{12}
The energy required equals the difference in total mechanical energy between the final and initial orbits.
5
Substitute given numerical values and convert joules to megajoules.
ΔE=10×(6.0×106)×50012=2.5×109 J=2500 MJ\Delta E = \frac{10 \times (6.0 \times 10^6) \times 500}{12} = 2.5 \times 10^9\text{ J} = 2500\text{ MJ}
Dividing 2.5×109 J2.5 \times 10^9\text{ J} by 10610^6 converts the value to megajoules.

Key Concept

Total Mechanical Energy of a Satellite in Circular Orbit and Orbital Transfer Energy
Estimated Time:3m 0s
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