A satellite in earth orbit has the altitude of its perigee at 400k and altitude of its apogee at ...
A satellite in earth orbit has the altitude of its perigee at 400k and altitude of its apogee at 800 km. u_E = 398,600km^3/s^2, R_E = 6371 km
a) Determine its orbital period
b) Determine its eccentricity
c) Determine the magnitude of its specific angular momentum
d) Determine the radius r_pi/2 when the true anomaly theta = pi/2 rad. Sketch an elliptical orbit and show where the point is.
e) Determine the orbital speed when the true anomaly theta = pi/2 rad. Give three sig digits after the decimal if you are providing your answer in km/s
f) What is the node DELTA N displacement of this satellite ground-track?
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A satellite in earth orbit has the altitude of its perigee at 400k and altitude of its apogee at ...
A satellite is in Earth orbit with an altitude at perigee of 500 km and an altitude at apogee of 700 km.
QUESTION 13 A satellite is in Earth orbit with an altitude at perigee of 500 km and an altitude at apogee of 700 km. What is the Eccentricity of the orbit?QUESTION 15 What is the radius of the moon's Sol relative to Earth? Assume: • The mass of the earth is 81.3 times the mass of the moon • The semi-major axis of the moon's orbit about the earth = 3.884 x 105km
A satellite is in Earth orbit with an altitude at perigee of 500 km and an altitude at apogee of 700 km.
A satellite is in Earth orbit with an altitude at perigee of 500 km and an altitude at apogee of 700 km. What is the semimajor axis of the orbit? Please only submit a number in the answer box (do not include units). I will assume the answer you submit is in kilometers.
5. A satellite is in earth orbit for which the perigee altitude is 100 km and...
5. A satellite is in earth orbit for which the perigee altitude is 100 km and the apogee altitude is 500 km. Find the time of flight from perigee to when the satellite reaches an altitude of 250 ks
#6. An earth-orbiting satellite has a perigee radius of 7000 km and an apogee radius of...
#6. An earth-orbiting satellite has a perigee radius of 7000 km and an apogee radius of 12,000 km. Determine the true anomaly 40 minutes after perigee passage.
Suppose a certain satellite has a highly eccentric orbit about Earth. At its greatest distance (apogee),...
Suppose a certain satellite has a highly eccentric orbit about Earth. At its greatest distance (apogee), it is 1487 km above the surface of Earth. At its closest approach (perigee), it is 737 km above Earth's surface. If it is moving at 7 km/s at apogee, what is its speed, in m/s, at perigee? Assume four sig figs.
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point t...
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 = 249.0 km, and it is moving with a speed of up = 7.950 km/s. The gravitational constant G equals 6.67 x 10-11 mº.kg-1.5-2 and the mass of Earth equals 5.972 x 1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what is...
A satellite is in an elliptic orbit around the Earth. Its speed at the perigee A...
A satellite is in an elliptic orbit around the Earth. Its speed
at the perigee A is 8500 m/s (Figure 1) .
A) Use conservation of energy to determine its speed at B. The
radius of the Earth is 6380 km.\
B) Use conservation of energy to determine the speed at the
apogee C.
B 13,900 km A с 16,460 km 8230 km 8230 km
A satellite is placed in an elliptic equatorial orbit and orbits Earth in the opposite direction ...
A satellite is placed in an elliptic equatorial orbit and orbits Earth in the opposite direction to Earth’s rotation. The altitude of perigee point is 2,000 km while the altitude of the apogee point is 30,000 km. Given that radius of Earth is 6378 km, find: The semi-major and semi-minor axis of the orbit. In one orbit, the satellite had its perigee over longitude 30° E, over which longitude will it have its next apogee? If the satellite transmits a...
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 closest approach to the Earth, its height above the ground is hp = 217.0 km and it is moving with a speed of vp = 8.850 km/s. When the satellite reaches its apogee, at its farthest point from the Earth, what is its height ha above the ground?
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 closest approach to the Earth, its height above the ground is h_p = 225.0 km and it is moving with a speed of v_p = 9.850 km/s. When the satellite reaches its apogee, at its farthest point from the Earth, what is its height ha above the ground?
5. A satellite is in earth orbit for which the perigee altitude is 100 km and the apogee altitude is 500 km. Find the time of flight from perigee to when the satellite reaches an altitude of 250 ks
#6. An earth-orbiting satellite has a perigee radius of 7000 km and an apogee radius of 12,000 km. Determine the true anomaly 40 minutes after perigee passage.
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 = 249.0 km, and it is moving with a speed of up = 7.950 km/s. The gravitational constant G equals 6.67 x 10-11 mº.kg-1.5-2 and the mass of Earth equals 5.972 x 1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what is...
A satellite is in an elliptic orbit around the Earth. Its speed
at the perigee A is 8500 m/s (Figure 1) .
A) Use conservation of energy to determine its speed at B. The
radius of the Earth is 6380 km.\
B) Use conservation of energy to determine the speed at the
apogee C.
B 13,900 km A с 16,460 km 8230 km 8230 km
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its closest approach to the Earth, its height above the ground is h_p = 225.0 km and it is moving with a speed of v_p = 9.850 km/s. When the satellite reaches its apogee, at its farthest point from the Earth, what is its height ha above the ground?
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