Characterizing space debris longitude-dependent distribution based on RAAN perturbation rate

Pang, Baojun; Wang, Dongfang; Xiao, Weike; Lu, Bin-Bin

doi:10.1016/j.asr.2019.12.026

Cited by 3 publications

(2 citation statements)

References 6 publications

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“…Table 3. the value of the coefficient in RKF7 (8). The reference orbit dynamical model used in analyzing the impact of LEO satellite orbit prediction accuracy is constructed as depicted in Table 4.…”

Section: Experimental Designs On the Impact Of Orbit Prediction Accuracymentioning

confidence: 99%

“…Concurrently, several such LEO giant constellations may simultaneously exist in the future LEO space environment. The sustained normal operation of these large-scale LEO satellites in orbit imposes heightened demands on LEO space situational awareness, space debris environment analysis, and the accuracy and real-time performance of collision warning systems [8,9]. Whether for LEO satellite information support applications or collision warning analysis, precise orbit determination and rapid forecasting of LEO satellites are imperative [10].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Analysis of the Influence of Typical Perturbation Forces on LEO Satellites Orbit Prediction at Different Altitudes

Zhang,

He,

Peng

et al. 2024

Preprint

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Aiming at the development of the application of massive and heterogeneous LEO constellations, the influence of typical perturbation forces on the orbit prediction of LEO satellites at different altitudes is analyzed. Firstly, the main perturbation force model of LEO satellites is introduced. Then experiments for analyzing the influence of orbit prediction on LEO satellites at different altitudes are designed. Finally, the influence of typical perturbation forces on the orbit prediction under different prediction durations by numerical analysis is assessed systematically, and the orbit prediction of LEO satellites with different non-spherical gravitational field orders, ocean tide orders and atmospheric density models were compared and calculated. The research results show that different orders of non-spherical gravitational fields should be considered when the altitude of satellites is different, the reasonable gravitational field orders for LEO satellites at 500km, 1000km, 1500km and 2000km under 1-hour forecast time are 140x140, 80x80, 60x60 and 40x40 orders, the reasonable orders of ocean tide perturbation for 1500km and 2000km satellites are 20x20 orders. Under the 24-hour forecast time, atmospheric resistance has a great influence on the precision of LEO satellites at orbit altitude below 1,000km. The forecast deviation of the LEO satellites orbit at 500km reaches 8751.576m. The difference of orbit precision between different atmospheric density models is in the meter level. The orbit deviation by the Standard Atmosphere 1976 and NRLMSISE 2000 atmospheric models respectively reaches 25.494m. Relevant conclusions provide support for the optimization and selection of dynamical models in high precision orbit determination and fast orbit prediction of LEO satellites.

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Section: Experimental Designs On the Impact Of Orbit Prediction Accuracymentioning

confidence: 99%