Perturbation Effects in Orbital elements of CubeSats

被引：0

作者：

Hanafi, Ahmed ^{[1
]}

Karim, Mohammed ^{[1
]}

Hachem, El-Kaber ^{[2
]}

Rachidi, Tajjeeddine ^{[3
]}

Sahmoudi, Mohamed ^{[4
]}

机构：

[1] FSDM, LISTA Lab, Fes, Morocco

[2] UMI, Dept Phys, Fac Sci, Meknes, Morocco

[3] Al Akhawayn Univ, Dept Comp Sci, Ifrane, Morocco

[4] Higher Inst Aeronaut & Space, Toulouse, France

来源：

2017 3RD INTERNATIONAL CONFERENCE ON ADVANCED TECHNOLOGIES FOR SIGNAL AND IMAGE PROCESSING (ATSIP) | 2017年

关键词：

Orbit perturbations; CubeSat; Keplerian Orbital elements;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

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.

引用

页码：397 / 402

页数：6

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