A new algorithm for minimum-fuel two-impulse orbit transfer

In this paper, the problem of two-impulse orbital transfer of spacecraft with the minimum fuel consumption is considered. The transfer orbit is parameterized in terms of the angular momentum. The total consumption, which is represented by the increment of the velocity, is expressed as a function of the angular momentum. The derivative of the fuel consumption is evaluated analytically. By solving the derivative equation, the minimum transfer orbit can be obtained. This method can be applied to both circle orbits and elliptic orbits. It accommodates for the transfers between coplanar orbits as well as the transfers between non-coplanar orbits. Numerical simulation example is given to show the effectiveness of the proposed method.