地球同步转移轨道(geostationary transfer orbit，GTO)为霍曼转移轨道的运用之一，为椭圆形轨道，经加速后可达地球静止轨道(GEO)。近地点多在1000公里以下，远地点则为地球静止轨道高度35786公里。一般而言，地球同步转移轨道的近地点并无特别限制，但通常距地球表面数百公里，以降低ΔV(方向及速度改变量)的需求。

同步卫星的运作轨道为地球静止轨道，由地球同步转移轨道至地球静止轨道转换工作多由卫星自身动力进行，卫星在地球同步转移轨道的远地点附近变轨时，需要增加速度及改变速度的方向。在火箭性能方面，常以地球同步转移轨道酬载能力作为指标，该酬载能力较直接运送至地球静止轨道的数值为大。以三角洲四号重型运载火箭为例，其GTO运载能力为12,757公斤，而GEO运载能力仅为6,276公斤。

A geosynchronous transfer orbit or geostationary transfer orbit (GTO) is a Hohmann transfer orbit used to reach geosynchronous or geostationary orbit using high thrust chemical engines. It is a highly elliptical Earth orbit with an apogee of 42,164 km (26,199 mi), or 35,786 km (22,236 mi) above sea level, which corresponds to the geostationary (GEO) altitude. The argument of perigee is such that apogee occurs on or near the equator. Perigee can be anywhere above the atmosphere, but is usually restricted to a few hundred kilometers above the Earth's surface to reduce launcher delta-V (V) requirements and to limit the orbital lifetime of the spent booster so as to curtail space junk. If using low-thrust engines such as electrical propulsion to get from the transfer orbit to geostationary orbit, the transfer orbit can be supersynchronous (having an apogee above the final geosynchronous orbit). This method however takes much longer to achieve due to the low thrust injected into the orbit. The typical launch vehicle injects the satellite to a supersynchronous orbit having the apogee above 42,164 km. The satellite's low thrust engines are thrusted continuously around the geostationary transfer orbits in an inertial direction. This inertial direction is set to be in the velocity vector at apogee but with an outer plane direction. The outer plane direction removes the initial inclination set by the initial transfer orbit while the inner plane direction raises simultaneously the perigee and lowers the apogee of the intermediate geostationary transfer orbit. In case of using the Hohmann transfer orbit, only a few days are required to reach the geosynchronous orbit. By using low thrust engines or electrical propulsion, months are required until the satellite reaches its final orbit.