SGP是第一个轨道传播器。它是由希尔顿和库尔曼于1966年开发的，这要归功于Kozai在1959年所做的一项研究工作。它是为绕地球轨道运行的卫星制造的，其中包括轨道周期小于225分钟的卫星。该模型假定偏心率低，并且近地点的高度恒定。
SGP4由肯·克兰福德（Ken Cranford）于1970年开发。它是对之前的传播器的改进，目的是跟踪此时轨道上不断增长的卫星数量。它也用于近地卫星。
SGP8也用于近地卫星，几乎类似于SGP4传播器，但计算方法不同。但是，对于大气和重力效应，它遵循相同的模型。
SDP8是适用于深空效果的SGP8传播器。此外，SGP8和SDP8更好地管理了轨道衰减(SGP is the first orbital propagator. It was developed by Hilton and kurman in 1966, thanks to a study by Kozai in 1959. It is made for satellites orbiting the earth, including those with an orbital period of less than 225 minutes. The model assumes low eccentricity and constant perigee height.
SDP4, developed by hujsak in 1979, is a SGP4 propagator for deep space objects. This includes satellites with orbital periods greater than 225 minutes. For a time period higher than this value, the orbit of the satellite will be interfered by the moon and the sun, as well as by some resonance effects in the 12 and 24-hour orbital periods.
Sgp8 is also used in near earth satellites, almost similar to SGP4 propagator, but the calculation method is different. However, it follows the same model for atmospheric and gravitational effects.
Sdp8 is a sgp8 propagator for deep space effects. In addition, sgp8 and sdp8 better manage orbital attenuation)