ENERGY of AN ORBITING SATELLITEMatch the Column I with Column II- For a satellite in circular orbit-Column IColumn IIA Kinetic energyp -GMEm-2rB Potential energyq -GME-rC Total energyr -GME-rD Orbital velocitys GMEm-2rwhere ME is the mass of the earth- m is mass of the satellite and r is the radius of the orbit

The correct option is D A s, B r, C p, D qKinetic energy = GM_Em2r ; #160; A→ s Potential energy = GM_Er ; B→ r Total energy = GM_Em ...

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Standard XII

Physics

Satellites

ENERGY of AN ...

Question

ENERGY of AN ORBITING SATELLITE
Match the Column I with Column II. For a satellite in circular orbit,
Column I Column II
(A) Kinetic energy (p) $- \frac{G M_{E} m}{2 r}$
(B) Potential energy (q) $\sqrt{\frac{G M_{E}}{r}}$
(C) Total energy (r) $- \frac{G M_{E}}{r}$
(D) Orbital velocity (s) $\frac{G M_{E} m}{2 r}$
(where $M_{E}$ is the mass of the earth, m is mass of the satellite and r is the radius of the orbit)

A-r, B-s, C-q, D-p

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A-q, B-p, C-r, D-s

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A-p, B-q, C-s, D-r

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A-s, B-r, C-p, D-q

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Solution

The correct option is D A-s, B-r, C-p, D-q
Kinetic energy = $\frac{G M_{E} m}{2 r}$ ;
$A \to s$
Potential energy = $- \frac{G M_{E}}{r}$ ;
$B \to r$
Total energy = $- \frac{G M_{E} m}{2 r}$ ;
$C \to p$
Orbital velocity= $\sqrt{\frac{G M_{E}}{r}}$ ;
$D \to q$

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Q. Match the following (for a satellite in circular orbit)

\begin{matrix} C o l u m n - I & C o l u m n - I I (a) & Kinetic energy & (p) & - \frac{G M m}{2 r} (b) & Potential energy & (q) & \sqrt{\frac{G M}{r}} (c) & Total energy & (r) & - \frac{G M m}{r} (d) & Orbital velocity & (s) & \frac{G M m}{2 r} \end{matrix}

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Column I	Column II
(A) Kinetic energy	(p) $- \frac{G M_{E} m}{2 r}$
(B) Potential energy	(q) $\sqrt{\frac{G M_{E}}{r}}$
(C) Total energy	(r) $- \frac{G M_{E}}{r}$
(D) Orbital velocity	(s) $\frac{G M_{E} m}{2 r}$

The correct option is D A-s, B-r, C-p, D-qKinetic energy = GMEm2r; A→sPotential energy = −GMEr;B→rTotal energy = −GMEm2r; C→pOrbital velocity=√GMEr;D→q

The correct option is D A-s, B-r, C-p, D-q
Kinetic energy = $\frac{G M_{E} m}{2 r}$ ;
$A \to s$
Potential energy = $- \frac{G M_{E}}{r}$ ;
$B \to r$
Total energy = $- \frac{G M_{E} m}{2 r}$ ;
$C \to p$
Orbital velocity= $\sqrt{\frac{G M_{E}}{r}}$ ;
$D \to q$