The three Laser Interferometer Space Antenna (LISA) spacecraft are going to be placed in a triangular formation in an Earth-trailing or Earth-leading orbit. They will be launched together on a single rocket and transferred to that science orbit using Solar Electric Propulsion. Since the transfer Δv depends on the chosen science orbit, both transfer and science orbit have been optimised together. For a thrust level of 90 mN, an allocation of 1092 m/s per spacecraft is sufficient for an all-year launch in 2034. For every launch month a dedicated science orbit is designed with a corner angle variation of 60^° ± 1.0^° and an arm length rate of maximum 10 m/s. Moreover, a detailed navigation analysis of the science orbit insertion and the impact on insertion errors on the constellation stability has been conducted. The analysis shows that Range/Doppler measurements together with a series of correction manoeuvres at the beginning of the science orbit phase can reduce insertion dispersions to a level where corner angle variations remain at about 60^° ± 1.1^° at 99% C.L. However, the situation can become significantly worse if the self-gravity accelerations acting during the science orbit phase are not sufficiently characterised prior to science orbit insertion.

三个激光干涉仪空间天线 (LISA) 航天器将被放置在地球尾随或地球前导轨道上的三角形编队中。它们将在单个火箭上一起发射，并使用太阳能电力推进系统转移到科学轨道。由于转移 Δ v取决于选择的科学轨道，转移和科学轨道都已一起优化。对于 90 mN 的推力水平，每艘航天器分配 1092 m/s 就足以在 2034 年全年发射。每个发射月设计一个专用科学轨道，角角变化为 60 ^°  ±1.0 ^°和最大 10 m/s 的臂长速率。此外，还对科学入轨以及入轨误差对星座稳定性的影响进行了详细的导航分析。分析表明，距离/多普勒测量与科学轨道阶段开始时的一系列校正机动相结合，可以将插入色散降低到在 99% CL 时角角变化保持在大约 60 ^°  ±1.1 ^{° 的水平}。如果在科学轨道插入之前没有充分表征在科学轨道阶段起作用的自重力加速度，则可能会变得更糟。