ScholarLens Back to search
2017•Unpublished venueRequires access

Perturbation effects in orbital elements of CubeSats

Ahmed Hanafi, Mohammed Karim, El-Kaber Hachem, Tajjeeddine Rachidi, M. Sahmoudi

Open publisher page 6 citations

Abstract

The main objective of this paper is to evaluate the perturbations in CubeSat's orbital elements in low Earth orbits (LEO) using the Cowell's method. The disturbing forces are driving the satellite (the satellite's trajectory) away from Keplerian orbit, therefore produce a change in Keplerian orbital elements over time. In this paper, after introducing the perturbing forces acting on a satellite in LEO, the methods of converting the orbital elements into state vector and the opposite are being presented, and in the end, the perturbations in orbital elements of CubeSats in LEO are evaluated.

About this research paper

What this paper is about

The main objective of this paper is to evaluate the perturbations in CubeSat's orbital elements in low Earth orbits (LEO) using the Cowell's method. The disturbing forces are driving the satellite (the satellite's trajectory) away from Keplerian orbit, therefore produce a change in Keplerian orbital elements over time. In this paper, after introducing the perturbing forces acting on a satellite in LEO, the methods of converting the orbital elements into state vector and the opposite are being presented, and in the end, the perturbations in orbital elements of CubeSats in LEO are evaluated.

Why it matters

OpenAlex reports 6 citations for this work. Citation counts describe recorded attention and do not establish research quality.

Key contribution

A contribution statement is not available in the OpenAlex record.

Method / approach

Method details are not available in the OpenAlex metadata.

Main findings

Findings are not separately available in the OpenAlex metadata.

Limitations

Limitations are not available in the OpenAlex metadata.

Applications

Application details are not available in the OpenAlex metadata.

Available abstract

The main objective of this paper is to evaluate the perturbations in CubeSat's orbital elements in low Earth orbits (LEO) using the Cowell's method. The disturbing forces are driving the satellite (the satellite's trajectory) away from Keplerian orbit, therefore produce a change in Keplerian orbital elements over time. In this paper, after introducing the perturbing forces acting on a satellite in LEO, the methods of converting the orbital elements into state vector and the opposite are being presented, and in the end, the perturbations in orbital elements of CubeSats in LEO are evaluated.

Key concepts: Orbital maneuver, Perturbation (astronomy), CubeSat, Orbital mechanics, Orbital elements, Frozen orbit, Satellite, Orbital speed

Related papers

Related paper 1Related paper 2Related paper 3
Back to paper searchBrowse research topicsOriginal source
Perturbation effects in orbital elements of CubeSats — Research Paper | ScholarLens