ISO/TR 19473:2015提供了有效载荷LV分离时轨道元件的最佳实践。包括各种有效载荷的轨道要素和计算条件、轨道要素的计算方法及其在椭圆轨道插入时的误差。轨道要素的实际值和预期值之间的拟合可作为商业发射的标准。 轨道元素有许多不同的集合。每一种都最适合于特定的应用。传统上使用的轨道元素集称为开普勒元素集。ISO/TR 19473:2015给出了开普勒元素的计算方法和所有其他轨道元素的转换方法，以满足不同用户的需要。 受地球引力摄动、日月引力摄动等因素影响，轨道注入后轨道要素变化缓慢。本技术报告不包括分离后的轨道元素计算方法。 通过应用ISO/TR 19473:2015，轨道元件的技术交流和具体进展相对容易达成一致，这有助于避免可能的争议。

ISO/TR 19473:2015 provides the best practices for orbit elements at payload-LV separation. It includes orbit elements and calculation conditions, calculation method of orbit elements and their errors at elliptical orbit insertion of various payloads. The fit between the actual and expected values of orbit elements can be used as a criterion of commercial launch. There are many different sets of orbit elements. Each is best suited for a particular application. The traditionally used set of orbital elements is called the set of Keplerian elements. ISO/TR 19473:2015 gives the calculation method of Keplerian elements and the transformation method of all the other orbit elements, in order to satisfy different user's need. Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors, orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation are not included in this Technical Report. The technical communication and specific progress for orbit elements is relatively easy to be agreed on by applying this ISO/TR 19473:2015, which can contribute to avoiding possible disputes.