Long-term evolution of orbital inclination due to third-body inclination

Nie, Tao; Gurfil, Pini

doi:10.1007/s10569-020-09997-x

Cited by 9 publications

(3 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Up to now, many valuable studies have been published, especially for GEO satellites [37]. In the present work, a double‐average technique is used to derive the differential disturbance effects caused by the third‐body perturbations [43].…”

Section: Extended Relative Motion Model Based On Mean Roesmentioning

confidence: 99%

Analytical propagation on relative motion of geostationary earth orbit satellites with orbital perturbations

Zhang

et al. 2023

IET Control Theory & Appl

View full text Add to dashboard Cite

An accurate description of the relative motion of satellites is critical for space missions in the complex geostationary earth orbit space environment. Here, a new relative motion model is established considering major perturbations. To avoid the singularity of the classical orbital elements, a set of quasi‐non‐singular orbital elements are used to represent the relative motion states, which is further extended by considering the SRP coefficient difference. On the basis of existing classical model, an analytical model is derived by taking the Taylor expansion of the time derivative of the perturbation functions to the first order in the neighbourhood of the reference satellite, which contains the earth's oblateness perturbation, the third‐body perturbations and the solar radiation pressure perturbation. This method avoids solving the complex differential equations of relative motion directly and provides a general framework for including arbitrary perturbations into the model. The new model is verified in uncontrolled natural relative motion scenarios and position‐keeping control scenario, respectively. The results show that the proposed model has high accuracy and strong competitiveness.

show abstract

Section: Extended Relative Motion Model Based On Mean Roesmentioning

confidence: 99%

Analytical propagation on relative motion of geostationary earth orbit satellites with orbital perturbations

Zhang

et al. 2023

IET Control Theory & Appl

View full text Add to dashboard Cite

show abstract

“…The disturbing effect of a third-body on a secondary-body's motion in a hierarchical triple system is a crucial problem in astrophysics. It has wide applications in star systems and exoplanets (Han et al 2014;Ricker et al 2015), and has been extensively studied in the literature (Domingos et al 2014(Domingos et al , 2015Nie & Gurfil 2021). There are evaluations of the orbital elements of a secondary-body that orbits around a primary-body on a timescale of thousands of days; hence, it would be impossible to plan such evaluations without addressing third-body orbit characteristics (Bakhtiari et al 2017b).…”

Section: Introductionmentioning

confidence: 99%

Effect of Orbital Characteristic of Inclined Third-body on Motion of Secondary-body for a Hierarchical Triple Systems

Bakhtiari

2023

Res. Astron. Astrophys.

View full text Add to dashboard Cite

The influence of a third-body's orbital elements on the second-body's motion in a hierarchical triple system is a crucial problem in astrophysics. Most prolonged evaluation studies have focused on a distant zero-inclined third-body. This study presents a new perspective on orbiter motion equations that addresses a perturbing body in an elliptic orbit derived with consideration of the axial-tilt (obliquity) of the primary. The proposed model is compared by the dual-averaged (DA) method and the N-body problem algorithm. After validation, a generalized three-body model is derived to investigate the effects of third-body's orbital elements on secondary-body motion behavior. The proposed model considers short-time oscillations that affect secular evaluation and applies to exoplanets with all the primary and third body's eccentricities, inclinations, and mass ratios. It is demonstrated that the obliquity of the primary (or the inclination of third-body) must be propunded for precise long-term assessment, even in high-hierarchy systems.

show abstract

“…[6][7][8][9]). However, around natural satellites that do not have an orbital plane coinciding with their equatorial plane, the effects of this non-co-planarity (obliquity and nodal phasing) on the dynamics of the probe become important [10,11].…”

Section: Introductionmentioning

confidence: 99%

Probe lifetime around natural satellites with obliquity

et al. 2022

View full text Add to dashboard Cite

The dynamics of a probe orbiting a moon can be significantly influenced by the non-coincidence between the moon’s equatorial and orbital planes. Thus, we performed a general analysis about the effects of the angle (obliquity) between the above-mentioned planes and of the angle (nodal phasing) between the nodal lines of the mother planet’s apparent orbit and the probe orbit on the lifetime of the probe. The lifetime, strictly correlated to the variations in eccentricity of the probe orbit, was evaluated starting from low values of the semi-major axis, moderate eccentricity, and high inclination to offer high ground spatial resolution and extend latitudinal coverage of the natural satellite. This investigation, carried out through numerical simulations, may be useful for identifying the optimal initial conditions of the probe’s orbit elements, leading to an important increase in the probe lifetime in missions devoted to the exploration of natural satellites.

show abstract

Long-term evolution of orbital inclination due to third-body inclination

Cited by 9 publications

References 23 publications

Analytical propagation on relative motion of geostationary earth orbit satellites with orbital perturbations

Analytical propagation on relative motion of geostationary earth orbit satellites with orbital perturbations

Effect of Orbital Characteristic of Inclined Third-body on Motion of Secondary-body for a Hierarchical Triple Systems

Probe lifetime around natural satellites with obliquity

Contact Info

Product

Resources

About