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Worked Examples · Example 7.8

Q.A 400 kg satellite is in a circular orbit of radius 2RE2R_E about the Earth. How much energy is required to transfer it to a circular orbit of radius 4RE4R_E? What are the changes in the kinetic and potential energies?

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For a circular orbit, total mechanical energy is E=−GMEm2rE=-\dfrac{GM_Em}{2r}. Moving the 400 kg satellite from 2RE2R_E to 4RE4R_E requires supplying energy ΔE=+3.14×109\Delta E=+3.14\times10^9 J; in doing so, its kinetic energy decreases by 3.14×1093.14\times10^9 J while its potential energy increases by 6.27×1096.27\times10^9 J.

Total energy in a circular orbit

For a satellite of mass mm orbiting at radius rr, gravity supplies the centripetal force, giving orbital speed v2=GME/rv^2=GM_E/r, so

K=12mv2=GMEm2r,U=−GMEmrK = \frac12mv^2 = \frac{GM_Em}{2r}, \qquad U = -\frac{GM_Em}{r}

E=K+U=GMEm2r−GMEmr=−GMEm2rE = K+U = \frac{GM_Em}{2r}-\frac{GM_Em}{r} = -\frac{GM_Em}{2r}

Energy at the two orbits

With r1=2REr_1=2R_E and r2=4REr_2=4R_E:

E1=−GMEm4RE,E2=−GMEm8REE_1 = -\frac{GM_Em}{4R_E}, \qquad E_2 = -\frac{GM_Em}{8R_E}

Energy that must be supplied

ΔE=E2−E1=−GMEm8RE+GMEm4RE=GMEm8RE\Delta E = E_2-E_1 = -\frac{GM_Em}{8R_E}+\frac{GM_Em}{4R_E} = \frac{GM_Em}{8R_E}

Using GME=gRE2GM_E=gR_E^2 with g=9.8 m/s2g=9.8\text{ m/s}^2, RE=6.4×106R_E=6.4\times10^6 m, and m=400m=400 kg:

GME=9.8×(6.4×106)2=4.01×1014 m3/s2GM_E = 9.8\times(6.4\times10^6)^2 = 4.01\times10^{14}\text{ m}^3/\text{s}^2

ΔE=4.01×1014×4008×6.4×106=1.606×10175.12×107≈3.14×109 J\Delta E = \frac{4.01\times10^{14}\times400}{8\times6.4\times10^6} = \frac{1.606\times10^{17}}{5.12\times10^7} \approx 3.14\times10^9\text{ J}

Since this is positive, energy must be added — thrusters must do work to raise the satellite to the higher orbit.

Changes in kinetic and potential energy

K1=GMEm4RE,K2=GMEm8RE  ⇒  ΔK=K2−K1=−GMEm8RE≈−3.14×109 JK_1 = \frac{GM_Em}{4R_E}, \quad K_2 = \frac{GM_Em}{8R_E} \;\Rightarrow\; \Delta K = K_2-K_1 = -\frac{GM_Em}{8R_E} \approx -3.14\times10^9\text{ J} …

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