Suppose that on a particular mission to Mars, a spacecraft is maneuvered to a circular parking orbit of 700 km around Earth. It is intended to carry out a heliocentric Hohmann transfer to Mars. Using patched conics determine: a) The eccentricity of the heliocentric transfer b) The angular momentum of the Hohmann transfer orbit c) The required hyperbolic excess velocity of earth escape, v∞/Earth. d) The required velocity increment of the impulse Dv to escape earth and complete the mission. e) The eccentricity of the hyperbolic escape f) The angular position of the impulse application θ∞/Earth g) The escape path displacement D.
The spacecraft mission needs to be designed so that it passes within 1900km of the surface of Mars. Using patched conics determine: h) The eccentricity of the Mars flyby i) The deflection d of the Mars flyby j) The heliocentric spacecraft speed before and after the flyby if the spacecraft approaches the sunny side of Mars and explain any differences. k) Repeat j) if the spacecraft approaches the dark side of Mars and explain any differences or similarities.
Please help with j) and k)