- #1
jisbon
- 476
- 30
- Homework Statement
- A minimum-energy transfer orbit to an outer planet consists of putting a spacecraft on
an elliptical trajectory with the departure planet corresponding to the perihelion of the ellipse, or the closest point to the Sun, and the arrival planet at the aphelion, or the farthest point from the Sun. (Assume the orbital radius of the Earth is ##1.50*10^8## m, and the orbital radius of Mars is ##2.30*10^8## m, and mass of Sun to be ##2.00*10^30##kg. Calculate how long spacecraft will take to arrive at Mars.
- Relevant Equations
- NIL
So I've seen many similar questions like this on the internet, but they all involve using Kepler's law, which is not in my syllabus in my case. However, they do give me the mass of the Sun. which I assume involves gravitational force/field/circular motion?
The question also gave me a hint that I could work out the formula by assuming radius r and then replace with semi-major axis a. Not sure what it is talking about exactly.
Sorry, but I don't really know how to start this, but advice will be appreciated. Thanks!