## 5 Juno Trajectory Geometry  
The Juno expedition to Jupiter has been separated into a total of 13 stages, each of which will last for a varying amount of time. As the lengthy Juno mission continues, each phase will reach unique milestones and experience exceptional occurrences. The Juno mission was scheduled to begin in August 2011 and was anticipated to continue for six and a half years, concluding in February 2018. The launch of Juno occurred on 5 August 2011. A two-part maneuver in deep space was performed by the spacecraft on the 30 August and 14 September 2012, subsequently assisted by an Earth gravity maneuver on 9 October 2013, at an altitude of 559 km. This trajectory is known as a deltaV-EGA trajectory [19; 20]. After reaching its nearest approach to Jupiter, known as perjove, during orbit 36, Juno performed a deorbit burn to be ready for its mission's end, which will include a devastating impact on the gas giant. After the conclusion of the mission, the scientists will conduct data analysis for two years [21]. The Juno spacecraft is a spinning orbiter that revolves along its +Z axis, which is the axis that is perpendicular to the plane in which the solar arrays are positioned. The mission phase determines whether the spacecraft spins at an average speed of 1, 2, or 5 revolutions per minute (RPM). For an interplanetary cruise, the spin rate is typically 1 RPM, 2 RPM during the orbit around Jupiter, and 5 RPM during propulsion system maneuvers after processing to the burn position. Instrument inspection and calibration are exempt from the spacecraft spinning at 1 RPM during interplanetary flight, as are the post-cleaning maneuvers [16]. The Launch phase begins at L \(-\) 40 min (also written as Launch \(-\) 40 min), and it lasts until the satellite has established a Sun-pointed attitude that is pre-defined, steady, and slowly changing. At this point, the cruise attitude control schemes and ephemerides can be used. Post-launch safety and health examinations decide whether the Launch phase continues or comes to a conclusion [20; 22]. In the system of differential equations that characterize the planetary, solar, and lunar movements, the independent variable is the uniform time scale known as Barycentric Dynamical Time (TDB). Table 1 presents a breakdown of the various stages of the Juno mission expressed in TBD, as seen below. It provides the phase's name, commencement date, and end date. The Juno spacecraft, which NASA operates, left Earth in 2011 to begin its trip to Jupiter, the giant planet in our solar system. It is possible to use cruise orientation control algorithms and ephemerides during the Inner Cruise 1 phase, which began after the post-launch establishment of a pre-defined and stable Sun-pointed orientation was achieved, when the orbiter moves far enough away from the Sun to allow for Earth-pointing instead of Sun-pointing. It was decided that TCM 1 (the earliest scheduled trajectory correction maneuver) was not required; hence, it was not carried out [8; 23]. Launch plus 66 days and continuing until Launch plus 663 days constituted the duration of the Inner Cruise 2 phase. During this phase, around the aphelion of Juno's first orbit around the Sun, the deep space maneuvers (DSMs) took place. After the Earth Flyby (EFB), Juno continued to Jupiter [20; 24; 25]. The duration of the Inner Cruise 3 phase was between L + 663 and L + 823 days. This portion of the voyage lasted 160 days. This phase included the Earthflyby, which provided Juno with a gravitational assist (7.3 km/s of velocity difference, \(\Delta\)v) on its journey to Jupiter. It had perihelion and happened when the spacecraft completed one elliptical revolution around the Sun [8; 26]. Three TCMs were scheduled before EFB, with the final judged unnecessary and one following EFB. As a result of the four maneuvers and EFB, there was greater DSN coverage. Subject to flight system restrictions, the Inner Cruise 3 phase focused on conducting the appropriate maneuvers and an integrated missions exercise around Earth Flyby.