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<p>In this paper, a high-fidelity satellite precise orbit propagator (SPOP) is described for the spacecraft orbiting in the halo orbit around the Lagrangian point of the Sun-planet system. The propagator integrates the perturbed two-body differential equations of motion in the heliocentric <i>J</i>2000 inertial reference frame using Cowell’s method and explicit Runge–Kutta integrator with fixed time step size. The dominant perturbing forces are included while modeling the numerical propagator. Further, we describe the computational procedure for calculating the orbit to and from <i>J</i>2000 inertial frame and the Rotating Lagrangian Point (RLP) frame for visualizing the orbit. The SOHO and Aditya-<InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(L_1\)</EquationSource> <EquationSource Format="MATHML"><math> <msub> <mi>L</mi> <mn>1</mn> </msub> </math></EquationSource> </InlineEquation> missions are used to validate the results obtained from the precise orbit propagator.</p>

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Lagrange point orbit prediction using high-fidelity orbit propagator and orbit representation in rotating reference frame

  • 期刊论文

  • 发表日期：

    2026年1月21日

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  • AMIT K. SINGH,
  • VINEET K. SRIVASTAVA,
  • SONALI AGARWAL

摘要

In this paper, a high-fidelity satellite precise orbit propagator (SPOP) is described for the spacecraft orbiting in the halo orbit around the Lagrangian point of the Sun-planet system. The propagator integrates the perturbed two-body differential equations of motion in the heliocentric J2000 inertial reference frame using Cowell’s method and explicit Runge–Kutta integrator with fixed time step size. The dominant perturbing forces are included while modeling the numerical propagator. Further, we describe the computational procedure for calculating the orbit to and from J2000 inertial frame and the Rotating Lagrangian Point (RLP) frame for visualizing the orbit. The SOHO and Aditya- \(L_1\) L 1 missions are used to validate the results obtained from the precise orbit propagator.