## 1 Introduction  
Missions to Lagrange points have been effective because they provide opportunities for flexible, low-energy trajectories. Lagrange points are equilibrium points in the space between two celestial bodies where the net gravitational force on an object at that point is zero. The five stable Lagrange points are L1, L2, L3, L4, and L5. In particular, L1 and L2 points are of interest because they offer a unique location in space where a spacecraft can maintain a stable position relative to the two celestial bodies. These points can be used for a variety of scientific and practical applications, such as satellite constellations, thermal observation, and studying the environment of celestial bodies. Halo orbits and Near Rectilinear Halo Orbits (NRHO) are types of orbits that are related to Lagrange points. Halo orbits are defined by their proximity to a Lagrange point and their ability to remain in the vicinity of that point for an extended period of time, allowing for a broad range of scientific observations and technological applications. NRHO orbits are a specific type of Halo orbits that do not coincide with resonance with the motions of celestial bodies. These orbits are called \"near-rectilinear\" because they are close to being a straight line. NRHO orbits have the advantage of being less affected by the perturbations caused by other celestial bodies, making them useful for long-term missions. One example of the application of this type of orbit is the James Webb Space Telescope (JWST or Webb), a joint NASA/ESA/CSA mission that launched an infrared-optimized 6.5 m space telescope in December 2021. The JWST will allow for a range of astronomical and cosmological studies, such as the observation of the first stars, the creation of the first galaxies, and a detailed analysis of potentially habitable exoplanets [1]. Another example is the Near-Earth Object Surveillance Mission (NEOSM), which is scheduled to be launchedby NASA in 2025. The NEOSM will use an infrared telescope to survey the solar system for potentially hazardous asteroids and will be conducted by the NEO Surveyor spacecraft, which will be stationed at the Sun-Earth L1 Lagrange point. This location allows it to look close to the Sun and detect objects inside Earth's orbit that would otherwise be difficult to spot from Earth or low Earth orbit [2]. Moreover, in recent years, several proposals have been made for using libration point orbits in the Earth-Moon system for communication and navigation services, particularly around the collinear L1 and L2 points. For example, [PERSON] et al. [3] have investigated the use of libration points for lunar South Pole coverage. [PERSON] et al. [4] analyzed the feasibility of using small satellites on Halo orbits for a lunar constellation. A lunar positioning system has also been designed using Lissajous [5] or Halo orbits [6] around both L1 and L2 points. Last, but not least, a future mission will deploy in a Moon Halo orbit, the Lunar Gateway: a space station that is a key part of NASA's Artemis program. The Lunar Gateway will serve as a science laboratory, a testing ground for new technologies, and a stepping stone for deep space exploration, including toward Mars. For all these missions, and for future ones, Orbit Determination (OD) is a crucial element in order to meet the requirements and the goals of the missions. Conventionally, Earth-based tracking stations, such as the Deep Space Network (DSN), are used for tracking spacecraft. However, this practice has several limitations, especially if the number of simultaneous missions to be tracked increases. In fact, it has a capacity limit in terms of spacecraft that can be served simultaneously; it is costly and cannot support direct full coverage of a celestial object (for example, the case of spacecraft on the dark side of the Moon).