Next year the Hyabusa spacecraft will return to Earth from the asteroid Itokawa. Inspired by this, you are required to report on your individual study of the following: The free trajectory options, associated Δv requirements and mission times to take a spacecraft from a low Earth orbit (LEO) to a low orbit around Itokawa, if Itokawa is at: a. perihelion, (147,098,074 Km) b. apohelion. (152,097,701 Km) What are the pros and cons of each mission? LEO is at 8378 Km, How ever I have no idea how to caluclate the oribit of Itokawa, to get the distance between it and LEO. Also having problem geting the change in v. About Itokawa : http://en.wikipedia.org/wiki/25143_Itokawa Hope some one can help. Thanks in advance.