India's Lunar Mission (Chandrayaan- 1) Orbit Determination System

Vighnesam, N. V.; Sonney, Anatta; Soni, Pramod Kumar

doi:10.2514/6.iac-06-c1.5.06

Cited by 2 publications

(1 citation statement)

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“…In fact, Lunar Operational Orbit Determination Program (ILOODP) of the Indian Space Research Organization (ISRO) was validated with LP mission ephemeris obtained from NASA's Goddard Space Flight Center (GSFC). These results were approximately 25 m and 4 cm/sec for the accuracy of the position and velocity, respectively, for a one-day prediction during the lunar mapping (LM) phase (Vighnesam et al 2006).…”

Section: Orbit Prediction Accuracy Validationmentioning

confidence: 85%

Evaluating High-Degree-and-Order Gravitational Harmonics and its Application to the State Predictions of a Lunar Orbiting Satellite

Song

Kim²

2015

Journal of Astronomy and Space Sciences

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In this work, an efficient method with which to evaluate the high-degree-and-order gravitational harmonics of the nonsphericity 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.

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Section: Orbit Prediction Accuracy Validationmentioning

confidence: 85%