The discussion revolves around determining the speed of a satellite in an elliptical orbit at varying altitudes, specifically comparing its speed at the high point and low point of the orbit. The context involves concepts from orbital mechanics and energy conservation.
Some participants have offered insights into the relationship between velocity and radius at different points in the orbit, while others express uncertainty about their calculations and the assumptions made. There is an ongoing exploration of different approaches to the problem without a clear consensus on the correct method.
Participants note the importance of accounting for the Earth's radius when calculating distances and speeds at different altitudes. There is also mention of varying interpretations of Kepler's Laws and their implications for the problem at hand.
hellothere123 said:Homework Statement
A satellite is in an elliptical orbit at altitudes ranging from 230 to 890 km. At the high point it's moving at 7.23 km/s. How fast is it moving at the low point?
I would think i would have to use some sort of energy conservation equations. but i really don't know where to begin or how to set this up. any help would be greatly appreciated!. i would like to learn how to do this.
hellothere123 said:kepler's law says they sweep out equal area in equal times. but i do not know how much area they are sweeping and how long it takes to sweep the equal area.
hellothere123 said:well i did some crazy stuff and got it to work :P
but i tried with the v1r1 = v2r2, doesn't give me the right answer. i did 1/2 mv^2 + mgh where i found g at that height and it magically gave me the answer. so, did i get lucky? or did i do it right?