00:01
In this problem, we're thinking about how to get, um, produce a transfer orbit from the earth to mars.
00:10
So in this case, our, the sun is our central body, and it is here.
00:17
And then we have earth's orbit here, and mars is orbit here.
00:20
And we're assuming that they're, that they're circular and co -planar, which is not exactly the case.
00:28
And we know that the mean distances, which we'll use as a radius from the sun, are this much for earth and this much for mars.
00:41
So we need to, basically, we want to launch a spacecraft here that then intercepts mars at this point.
00:50
And we need to figure out how much energy we need to add because it's now, it's, this whatever body is here, is orbiting.
01:00
The sun in a circular orbit and we need to now make it orbit the sun in a polybine elliptic orbit so that it reaches out here and then we need to change the speed here so that it goes now into a circular orbit with mars or reduce the speed so that it matches that of mars.
01:21
So what we have as a kinetic energy at a and again it's just circumferential at both a and b so we don't have any radial components because these are the maximum or minimum of the or the maximum here and the minimum here of the elliptic orbit.
01:38
We have the potential energy at a, kinetic energy at b and the potential energy at b.
01:45
Again, we're not worried, we're not going to worry about the gravity of the planet in this case.
01:52
So we have our conservation of angle momentum.
01:58
So all the force on this body acts just through the, through the center of the sun at all points.
02:06
Obviously as it gets closer and closer to mars and farther and farther and and it's close to earth, that's not going to be a good assumption.
02:15
But again, we're just using a first approximation to try to figure out exact kind of orders of magnitude here...