- #1
AwesomeTrains
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Warning read on your own risk: This is my first post here. I'm new to english, sorry for my bad grammar.
A satellite is launched one time Earth radius straight above the northpole (two times radius from center), with an angle of 60° to vertical.
Find the launch velocity [itex]v_{0}[/itex] so that the satellite won't orbit further away than six times Earth radius from the center of the earth.
FG=G[itex]\frac{Mm}{r^{2}}[/itex]
FC=m[itex]\frac{v^{2}}{r}[/itex]
FNet=[itex]m[/itex][itex]\cdot[/itex][itex]a[/itex]
I tried solving it by finding the satellite's trajectory.
Initial velocity in x and y direction:
[itex]v_{x}=cos 60°[/itex][itex]\cdot[/itex][itex]v_{0}[/itex]
[itex]v_{y}=sin 60°[/itex][itex]\cdot[/itex][itex]v_{0}[/itex]
Velocity from gravitational force in x and y direction:
(Θ the angle the satellite makes with the vertical y-axis through the northpole, when it's in orbit)
[itex]v_{Gx}[/itex]=[itex]\frac{F_{G} \cdot cos Θ \cdot t}{m}[/itex]
[itex]v_{Gy}[/itex]=[itex]\frac{F_{G} \cdot sin Θ \cdot t}{m}[/itex]
Total velocity:
(Vector addition)
[itex]v_{Tot}[/itex]=[itex] (v_{x} - v_{Gx}) + (v_{y} - v_{Gy})[/itex]
I don't know if this approach makes sense/ is correct. If it is, how should I continue?
Feel free to ask if something is unclear. Any help or tips are much appreciated.
Homework Statement
A satellite is launched one time Earth radius straight above the northpole (two times radius from center), with an angle of 60° to vertical.
Find the launch velocity [itex]v_{0}[/itex] so that the satellite won't orbit further away than six times Earth radius from the center of the earth.
Homework Equations
FG=G[itex]\frac{Mm}{r^{2}}[/itex]
FC=m[itex]\frac{v^{2}}{r}[/itex]
FNet=[itex]m[/itex][itex]\cdot[/itex][itex]a[/itex]
The Attempt at a Solution
I tried solving it by finding the satellite's trajectory.
Initial velocity in x and y direction:
[itex]v_{x}=cos 60°[/itex][itex]\cdot[/itex][itex]v_{0}[/itex]
[itex]v_{y}=sin 60°[/itex][itex]\cdot[/itex][itex]v_{0}[/itex]
Velocity from gravitational force in x and y direction:
(Θ the angle the satellite makes with the vertical y-axis through the northpole, when it's in orbit)
[itex]v_{Gx}[/itex]=[itex]\frac{F_{G} \cdot cos Θ \cdot t}{m}[/itex]
[itex]v_{Gy}[/itex]=[itex]\frac{F_{G} \cdot sin Θ \cdot t}{m}[/itex]
Total velocity:
(Vector addition)
[itex]v_{Tot}[/itex]=[itex] (v_{x} - v_{Gx}) + (v_{y} - v_{Gy})[/itex]
I don't know if this approach makes sense/ is correct. If it is, how should I continue?
Feel free to ask if something is unclear. Any help or tips are much appreciated.