English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Tools annual

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Tools monthly

Global: Zendy Plus monthly

Presents the access of premium content as premium feature

Premium Content

Global: Zendy Plus annual

Global: Zendy Free Plan

In this work we investigate the orbit-attitude perturbationsof a rigid spacecraft due to the effects of several forcesand torques. The spacecraft is assumed to be of a cylindricalshape and equipped with a charged screen with charge densitys. Clearly the main force affecting the motion of the spacecraftis the gravitational force of the Earth with uniform sphericalmass. The effect of oblate Earth up to J2 is considered asperturbation on both the orbit and attitude of the spacecraft,where the attitude of the spacecraft is acted upon by what iscalled gravity gradient torque. Another source of perturbationon the attitude of the spacecraft comes from the motion ofthe charged spacecraft in the geomagnetic field. This motiongenerates a force known as the Lorentz force which is the sourceof the Lorentz force torque influencing the rotational motion ofthe spacecraft. In this work we give an analytical treatment ofthe orbital-rotational dynamics of the spacecraft. We first usethe definitions of Delaunay and Andoyer variables in order toformulate the Hamiltonian of the orbit-attitude motion under theeffects of forces and torques of interest. Since the Lorentz forceis a non-conservative force, a potential like function is introducedand added to the Hamiltonian. We solve the canonical equationsof the Hamiltonian system by successive transformations using atechnique proposed by Lie and modified by Deprit and Kamelto solve the problem. In this technique we make two successivetransformations to eliminate the short and long periodic termsfrom the Hamiltonian.

Analytical Solution of the Perturbed Oribt-Attitude Motion of a Charged Spacecraft in the Geomagnetic Field