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In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the\udexecution of the 1st lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During\udthe early design phase of the system, associate analysis is an essential design factor as the 1st LOI maneuver is the largest\udburn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance\udachieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival\udtrajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such\udas varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the 1st LOI\udmaneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted\udto simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis\udto analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major\udrequirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for\udthe burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn\udperformances were simultaneously estimated and analyzed to maintain the 1st elliptical orbit achieved around the moon\udwithin the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the\udtarget insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC)\udmaneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus\uditself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based\udon the current results, including a contingency trajectory design plan

Uncertainty Requirement Analysis for the Orbit, Attitude, and Burn Performance of the 1stLunar Orbit Insertion Maneuver