A new approach to derive a formation flying model in the presence of a perturbing body in inclined elliptical orbit: relative hovering analysis

Bakhtiari, Majid; Daneshjou, K.; Abbasali, Ehsan

doi:10.1007/s10509-016-2968-9

Cited by 13 publications

(3 citation statements)

References 40 publications

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“…The secondary-body motion is described by hybrid orbital elements (r, v x , i, h, θ, Ω) (Bakhtiari et al 2017c) Also, the third-body is in an inclined orbit with semimajor axis a 3 , eccentricity e 3 , argument of perigee ω 3 , argument of latitude θ 3 , and RAAN Ω 3 (Xu et al 2012). Also, the potential function of the system is stated as (Bakhtiari et al 2017a)…”

Section: The Dynamic Modelmentioning

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.

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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.

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Section: The Dynamic Modelmentioning

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.

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“…PSO algorithm requires only a set of elementary arithmetic operators, so the implementation of this algorithm is simple and economical. 41,42…”

Section: Psomentioning

confidence: 99%

“…PSO algorithm requires only a set of elementary arithmetic operators, so the implementation of this algorithm is simple and economical. 41,42 In the PSO algorithm, there are creatures which are named particle. The particles are distributed in the search space.…”

Section: Psomentioning

confidence: 99%

The effects of parking orbit elements on designing of on-orbit servicing missions

Bakhtiari

Daneshjou

Mohammadi-Dehabadi

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Nowadays on-orbit servicing operations such as satellite refuelling, debris removal and visual inspection are considered as the most important issues in the space missions. Mission planning has a key role on the designation of such missions and it is strongly dependent on the required fuel. In this study, a new approach is proposed for the designing of the on-orbit operations with considering the parking orbit elements and location of the servicing satellites. The proposed method improves the previous mission planning process of the multiple servicing satellites in the terms of the reduction in the mission fuel consumption. Furthermore, a special rendezvous maneuver is considered for meeting the servicing satellites and the targets. Also, the transfer orbits are obtained through Lambert targeting. The optimisation of the problem is carried out by particle swarm optimisation algorithm and Taguchi technique is employed for the robust design of the control parameters of the optimisation algorithm. The results reveal that the proposed approach is an efficient way in the reduction of the fuel consumption in the on-orbit servicing missions rather than the conventional methods.

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An optimal deployment strategy for multi-plane satellite constellation using a generalized non-planar maneuver

Bakhtiari,

Abbasali

2024

Astrophys Space Sci

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A new approach to derive a formation flying model in the presence of a perturbing body in inclined elliptical orbit: relative hovering analysis

Cited by 13 publications

References 40 publications

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

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

The effects of parking orbit elements on designing of on-orbit servicing missions

An optimal deployment strategy for multi-plane satellite constellation using a generalized non-planar maneuver

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