In this work, an efficient method with which to evaluate the high-degree-and-order gravitational harmonics of the non-sphericity of a central body is described and applied to state predictions of a lunar orbiter. Unlike the work of Song et al. (2010), which used a conventional computation method to process gravitational harmonic coefficients, the current work adapted a well-known recursion formula that directly uses fully normalized associated Legendre functions to compute the acceleration due to the non-sphericity of the moon. With the formulated algorithms, the states of a lunar orbiting satellite are predicted and its performance is validated in comparisons with solutions obtained from STK/Astrogator. The predicted differences in the orbital states between STK/Astrogator and the current work all remain at a position of less than 1 m with velocity accuracy levels of less than 1 mm/s, even with different orbital inclinations. The effectiveness of the current algorithm, in terms of both the computation time and the degree of accuracy degradation, is also shown in comparisons with results obtained from earlier work. It is expected that the proposed algorithm can be used as a foundation for the development of an operational flight dynamics subsystem for future lunar exploration missions by Korea. It can also be used to analyze missions which require very close operations to the moon.

1. INTRODUCTION
 2. PERTURBING ACCELERATIONS DUE TO NONSPHERICITY
 3.RESULTS ANALYSIS
  3.1 Simulation Setup
  3.2 Orbit Prediction Accuracy Validation
  3.3 Processing Time and Accuracy Comparisons
 4. CONCLUSIONS
 ACKNOWLEDGEMENTS
 REFERENCES

• Young-Joo Song(Korea Aerospace Research Institute) Corresponding Author
• Bang-Yeop Kim(Korea Aerospace Research Institute, Daejeon 34133, Korea)