Fuel-Efficient Low-Thrust Transfer in Elliptic Orbits

Abstract

In this study, a fuel-efficient, low-thrust transfer problem is considered. The low-thrust transfer occurs continuously and its magnitude is constant through the transfer. Then, injection methods that enable spacecraft to transfer from any initial orbits to the geostationary orbit are proposed. The effectiveness of the proposed injection methods is evaluated via numerical simulations, with respect to velocity and fuel mass. Moreover, the dependence of the velocity increment on the initial argument of perigee is clarified through an analytic expression, which is useful in selecting a fuel-efficient initial orbit. T : orbital period (T = 2π/n) α : the maximum angle along the direction of move-ment ω : argument of perigee Ω : right ascension of the ascending node θ : argument of latitude (θ = ω + f) 6XEVFULSWV 0 : initial f : final h : direction normal to the orbital plane (rotation vector) r : radial direction s : direction along the cross product of the unit vector along h direction and that of r direction ,QWURGXFWLRQ Recently, satellites that use electricity as a primary propulsion sources have attracted much interest. Because electric propulsion has a high specific impulse, spacecraft using this propulsion system need less propellant compared to those using chemical propulsion systems. Though the actuator mass of the electric propulsion system is larger than that of the conventional chemical propulsion system, the overall mass for electric propulsion becomes smaller because the propellant mass is dominant in the overall mass.