The emergence of microsatellite missions leaving low Earth orbits to pursue the exploration of the solar system is currently leading the development of new techniques of mission analysis. In fact, the small size of these satellites affects the performance of the propulsion systems, in particular because of the limited mass budget available for propellant stowage. This work focuses on the analysis of lunar microsatellite missions, proposing a method to design fuel-saving lunar captures. The solution is aimed at establishing the capture conditions taking advantage of the gravity-braking effect of the Moon, before injecting the spacecraft into a lunar capture orbit. The maneuvers are developed in the form of guidance laws, implemented based on primer vector theory and on the definition of a quasi-integral of motion for the elliptic restricted 4-body problem. The method is verified, by means of numerical analysis, on a 6U CubeSat equipped with a monopropellant thruster and considering deployment conditions compatible with microsatellite lunar missions. The achievement of lunar capture in a few days from the deployment, with propellant usage on the order of tenths of grams, corresponding to $\Delta V$ on the order of some meters per second, indicates the suitability of the method to expand the possible profiles of microsatellite missions to the Moon.

离开低地球轨道以探索太阳系的微卫星任务的出现，目前正在引领任务分析新技术的发展。实际上，这些卫星的小尺寸会影响推进系统的性能，特别是因为可用于推进剂积载的预算有限。这项工作着重于对月球微卫星任务的分析，提出了一种设计节油月球捕获方法。该解决方案旨在在将航天器注入月球捕获轨道之前，利用月球的重力制动作用建立捕获条件。演习是以指导法的形式制定的，基于引物矢量理论和椭圆受限4体问题的准运动积分定义实现。该方法已通过数值分析在配备单推进器的6U CubeSat上进行了验证，并考虑了与微卫星月球飞行任务兼容的部署条件。部署后几天内就完成了月球捕获，推进剂的使用量约为十分之一克，相当于$\Delta V$ 每秒几米的量级，表明该方法适用于扩展微卫星向月球飞行任务的可能分布。