Question
In: Physics
A satellite is put into an elliptical orbit around the Earth. When the satellite is at...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point to the Earth, its height above the ground is hp=215.0 km,hp=215.0 km, and it is moving with a speed of vp=8.450 km/s.vp=8.450 km/s. The gravitational constant GG equals 6.67×10−11 m3⋅kg−1⋅s−26.67×10−11 m3·kg−1·s−2 and the mass of Earth equals 5.972×1024 kg.5.972×1024 kg.
When the satellite reaches its apogee, at its farthest point from the Earth, what is its height haha above the ground?
For this problem, choose gravitational potential energy of the satellite to be 00 at an infinite distance from Earth.
Solutions
genius_generous answered 1 year agoRelated Solutions
A satellite is put into an elliptical orbit around the Earth. When the satellite is at...
A satellite is put into an elliptical orbit around the Earth.
When the satellite is at its perigee, its nearest point to the
Earth, its height above the ground is hp=215.0 km,hp=215.0 km, and
it is moving with a speed of vp=8.450 km/s.vp=8.450 km/s. The
gravitational constant GG equals 6.67×10−11 m3⋅kg−1⋅s−26.67×10−11
m3·kg−1·s−2 and the mass of Earth equals 5.972×1024 kg.5.972×1024
kg.
When the satellite reaches its apogee, at its farthest point
from the Earth, what is its height haha above...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at...
A satellite is put into an elliptical orbit around the Earth.
When the satellite is at its perigee, its nearest point to the
Earth, its height above the ground is ℎp=215.0 km, and it is moving
with a speed of ?p=8.850 km/s. The gravitational constant ? equals
6.67×10−11 m3·kg−1·s−2 and the mass of Earth equals 5.972×1024 kg.
When the satellite reaches its apogee, at its farthest point from
the Earth, what is its height ℎa above the ground? For this...
A satellite is in an elliptical orbit around the earth. The distance from the satellite to...
A satellite is in an elliptical orbit around the earth. The
distance from the satellite to the center of the earth ranges from
7.2 Mm at perigee (where the speed is 8.0 km/s) to 9.9 Mm at
apogee.
1. Assume the initial conditions are x = 0, y = 7.2 × 106 m, vx
= 8.0×103 m/s, and vy = 0. Use python program to print its speed,
distance from the earth, kinetic energy, potential energy, and
total mechanical energy...
A satellite is placed in an elongated elliptical (not circular) orbit around the Earth. At the...
A satellite is placed in an elongated elliptical (not circular)
orbit around the Earth. At the point in its orbit where it is
closest to the Earth, it is a distance of 1.00 × 10^6
m from the surface (not the center) of the Earth,
and is moving at a velocity of 5.14 km/s. At the
point in its orbit when it is furthest from the Earth it is a
distance of 2.00×10^6 m from the surface of the
Earth....
Consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee...
Consider a spacecraft in an elliptical orbit around the earth. At
the low point, or perigee of its orbit it is 500 km above the earth
surface at the high point or apogee it is 5000km above the earth
surface
A) what is the period of the spacecraft orbit!?
B) using conservation of angular momentum find the ratio of
the spacecraft speed at perigee to its speed apogee!?
C) using conservation of energy find the speed at perigee and
the...
Consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee,...
Consider a spacecraft in an elliptical orbit around the earth.
At the low point, or perigee, of its orbit, it is 300km above the
earth's surface; at the high point, or apogee, it is 2500km above
the earth's surface.
A) What is the period of the spacecraft's orbit?
B) Using conservation of angular momentum, find the ratio of the
spacecraft's speed at perigee to its speed at apogee.
C) Using conservation of energy, find the speed at perigee and
the...
consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee,...
consider a spacecraft in an elliptical orbit around the earth.
At the low point, or perigee, of its orbit, it is 300 km above the
earth's surface; at the high point or apogee, it is 2500 km above
the earth's surface.
Part A: find ratio of the spacecraft's speed at perigee to its
speed at apogee?
(Vperigee / Vapogee) = .....
Part B: find the speed at the apogee?
V apogee = ........ m/s
Part C: find speed at perigee?...
Two satellites are in circular orbits around the earth. The orbit for satellite A is at...
Two satellites are in circular orbits around the earth. The
orbit for satellite A is at a height of 555 km above the earth’s
surface, while that for satellite B is at a height of 778 km. Find
the orbital speed for (a) satellite A and (b) satellite B.
Two satellites are in circular orbits around the earth. The orbit for satellite A is at...
Two satellites are in circular orbits around the earth. The
orbit for satellite A is at a height of 458 km above the earth’s
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(b) satellite B.
The path of a very small satellite S in an elliptical orbit around a massive spherical...
The path of a very small satellite S in an
elliptical orbit around a massive spherical planet
P is shown in the figure. The distance from 3 to 4
is the same as from 4 to 5, 9 to 10, and 10 to 11.
True False Greater than Less than Equal to The KE of
S varies with position.
True False Greater than Less than Equal to The speed at
S at position '8' is ... at '2'.
True False Greater than...
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