Many low-Earth-orbit constellations consist of multiple small satellites that are launched together in batches, and which make use of differential atmospheric drag for subsequent deployment and phasing. Depending on the initial altitude, this process can potentially take many months, or even years, to complete, and satellite altitudes can only ever be decreased, potentially affecting mission lifetimes. Miniaturized low-thrust propulsion systems are one option to achieve faster phasing and can additionally increase the constellation lifetime through drag compensation. Here, an analytical and numerical study comparing differential drag and low-thrust propulsion for constellation phasing is performed. Satellite electrical constraints associated with power generation and battery cycling life represent important factors that can decrease the performance of an onboard propulsion system. Despite these constraints, low-thrust propulsion can reduce total phasing times by an order of magnitude, or more, for altitudes in the range 300–700 km, while also increasing satellite flexibility and introducing a number of operational advantages. Remaining propellant can be used for drag compensation and collision avoidance maneuvers, while also reducing deorbiting times by many years.

许多低地球轨道星座是由多个小卫星组成的，这些小卫星分批发射，并利用差分大气阻力进行后续部署和定相。根据初始高度，此过程可能需要数月甚至数年才能完成，并且只能降低卫星高度，这可能会影响任务寿命。小型化的低推力推进系统是实现更快定相的一种选择，并且可以通过阻力补偿来延长星座寿命。在这里，进行了分析和数值研究，比较了差分拖曳力和低推力推进对星座相位的影响。与发电和电池循环寿命相关的卫星电气限制是可能降低机载推进系统性能的重要因素。尽管有这些限制，对于300-700 km范围内的高度，低推力推进仍可以将总定相时间减少一个数量级或更多，同时还可以提高卫星的灵活性并带来许多运行优势。剩余的推进剂可用于阻力补偿和避免碰撞的演习，同时还可将脱轨时间减少很多年。同时也增加了卫星的灵活性并带来了许多运营优势。剩余的推进剂可用于阻力补偿和避免碰撞的演习，同时还可将脱轨时间减少很多年。同时也增加了卫星的灵活性并带来了许多运营优势。剩余的推进剂可用于阻力补偿和避免碰撞的演习，同时还可将脱轨时间减少很多年。