Earth Satellites
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PHXI08:GRAVITATION

359719 An artificial satellite moving in a circular orbit around the earth has a total energy \(E_{0}\). Its potential energy is

1 \(-2 E_{0}\)
2 \(E_{0}\)
3 \(-E_{0}\)
4 \(2 E_{0}\)
PHXI08:GRAVITATION

359720 Match Column I with Column II. For a satellite in circular orbit, (where \(M_{E}\) is the mass of the Earth, \(m\) is mass of the satellite and \(r\) is the radius of the orbit)
Column I
Column II
A
Kinetic energy
P
\( - \frac{{G{M_E}m}}{{2r}}\)
B
Potential energy
Q
\(\sqrt {\frac{{G{M_E}}}{r}} \)
C
Total energy
R
\( - \frac{{G{M_E}m}}{r}\)
D
Orbital velocity
S
\(\frac{{G{M_E}m}}{{2r}}\)

1 A - R, B - S, C - Q, D - P
2 A - Q, B - P, C - R, D - S
3 A - P, B - Q, C - S, D - R
4 A - S, B - R, C - P, D - Q
PHXI08:GRAVITATION

359721 The minimum energy required to launch a \(m \mathrm{~kg}\) satellite from earth's surface in a circular orbit at an altitude of \(2 R, R\) is the radius of earth, will be

1 \(3 \mathrm{mgR}\)
2 \(\dfrac{5}{6} m g R\)
3 \(2 m g R\)
4 \(\dfrac{1}{5} m g R\)
PHXI08:GRAVITATION

359722 In a satellite if the time of revolution is \(T\), then kinetic energy is proportional to

1 \(T^{-2 / 3}\)
2 \(\dfrac{1}{T}\)
3 \(\dfrac{1}{T^{2}}\)
4 \(\dfrac{1}{T^{3}}\)
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PHXI08:GRAVITATION

359719 An artificial satellite moving in a circular orbit around the earth has a total energy \(E_{0}\). Its potential energy is

1 \(-2 E_{0}\)
2 \(E_{0}\)
3 \(-E_{0}\)
4 \(2 E_{0}\)
PHXI08:GRAVITATION

359720 Match Column I with Column II. For a satellite in circular orbit, (where \(M_{E}\) is the mass of the Earth, \(m\) is mass of the satellite and \(r\) is the radius of the orbit)
Column I
Column II
A
Kinetic energy
P
\( - \frac{{G{M_E}m}}{{2r}}\)
B
Potential energy
Q
\(\sqrt {\frac{{G{M_E}}}{r}} \)
C
Total energy
R
\( - \frac{{G{M_E}m}}{r}\)
D
Orbital velocity
S
\(\frac{{G{M_E}m}}{{2r}}\)

1 A - R, B - S, C - Q, D - P
2 A - Q, B - P, C - R, D - S
3 A - P, B - Q, C - S, D - R
4 A - S, B - R, C - P, D - Q
PHXI08:GRAVITATION

359721 The minimum energy required to launch a \(m \mathrm{~kg}\) satellite from earth's surface in a circular orbit at an altitude of \(2 R, R\) is the radius of earth, will be

1 \(3 \mathrm{mgR}\)
2 \(\dfrac{5}{6} m g R\)
3 \(2 m g R\)
4 \(\dfrac{1}{5} m g R\)
PHXI08:GRAVITATION

359722 In a satellite if the time of revolution is \(T\), then kinetic energy is proportional to

1 \(T^{-2 / 3}\)
2 \(\dfrac{1}{T}\)
3 \(\dfrac{1}{T^{2}}\)
4 \(\dfrac{1}{T^{3}}\)
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PHXI08:GRAVITATION

359719 An artificial satellite moving in a circular orbit around the earth has a total energy \(E_{0}\). Its potential energy is

1 \(-2 E_{0}\)
2 \(E_{0}\)
3 \(-E_{0}\)
4 \(2 E_{0}\)
PHXI08:GRAVITATION

359720 Match Column I with Column II. For a satellite in circular orbit, (where \(M_{E}\) is the mass of the Earth, \(m\) is mass of the satellite and \(r\) is the radius of the orbit)
Column I
Column II
A
Kinetic energy
P
\( - \frac{{G{M_E}m}}{{2r}}\)
B
Potential energy
Q
\(\sqrt {\frac{{G{M_E}}}{r}} \)
C
Total energy
R
\( - \frac{{G{M_E}m}}{r}\)
D
Orbital velocity
S
\(\frac{{G{M_E}m}}{{2r}}\)

1 A - R, B - S, C - Q, D - P
2 A - Q, B - P, C - R, D - S
3 A - P, B - Q, C - S, D - R
4 A - S, B - R, C - P, D - Q
PHXI08:GRAVITATION

359721 The minimum energy required to launch a \(m \mathrm{~kg}\) satellite from earth's surface in a circular orbit at an altitude of \(2 R, R\) is the radius of earth, will be

1 \(3 \mathrm{mgR}\)
2 \(\dfrac{5}{6} m g R\)
3 \(2 m g R\)
4 \(\dfrac{1}{5} m g R\)
PHXI08:GRAVITATION

359722 In a satellite if the time of revolution is \(T\), then kinetic energy is proportional to

1 \(T^{-2 / 3}\)
2 \(\dfrac{1}{T}\)
3 \(\dfrac{1}{T^{2}}\)
4 \(\dfrac{1}{T^{3}}\)
NEET DIGITAL LIBRARY
PHXI08:GRAVITATION

359719 An artificial satellite moving in a circular orbit around the earth has a total energy \(E_{0}\). Its potential energy is

1 \(-2 E_{0}\)
2 \(E_{0}\)
3 \(-E_{0}\)
4 \(2 E_{0}\)
PHXI08:GRAVITATION

359720 Match Column I with Column II. For a satellite in circular orbit, (where \(M_{E}\) is the mass of the Earth, \(m\) is mass of the satellite and \(r\) is the radius of the orbit)
Column I
Column II
A
Kinetic energy
P
\( - \frac{{G{M_E}m}}{{2r}}\)
B
Potential energy
Q
\(\sqrt {\frac{{G{M_E}}}{r}} \)
C
Total energy
R
\( - \frac{{G{M_E}m}}{r}\)
D
Orbital velocity
S
\(\frac{{G{M_E}m}}{{2r}}\)

1 A - R, B - S, C - Q, D - P
2 A - Q, B - P, C - R, D - S
3 A - P, B - Q, C - S, D - R
4 A - S, B - R, C - P, D - Q
PHXI08:GRAVITATION

359721 The minimum energy required to launch a \(m \mathrm{~kg}\) satellite from earth's surface in a circular orbit at an altitude of \(2 R, R\) is the radius of earth, will be

1 \(3 \mathrm{mgR}\)
2 \(\dfrac{5}{6} m g R\)
3 \(2 m g R\)
4 \(\dfrac{1}{5} m g R\)
PHXI08:GRAVITATION

359722 In a satellite if the time of revolution is \(T\), then kinetic energy is proportional to

1 \(T^{-2 / 3}\)
2 \(\dfrac{1}{T}\)
3 \(\dfrac{1}{T^{2}}\)
4 \(\dfrac{1}{T^{3}}\)
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