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

A new, second-order solution in curvilinear coordinates is introduced for therelative motion of two spacecraft on eccentric orbits. The second-orderequations for unperturbed orbits are derived in spherical coordinates with trueanomaly as the independent variable, and solved by the method of successiveapproximations. A comparison of error trends against eccentricity andinter-spacecraft separation is presented between the new solution and prominentCartesian, curvilinear, and orbital element based solutions from theliterature. The second-order curvilinear solution offers a thousand-foldimprovement in accuracy over the first-order curvilinear solution, and stillgreater improvement over first- and second-order rectilinear solutions whenlarge along-track separations are present.

Second-Order Solution for Relative Motion on Eccentric Orbits in Curvilinear Coordinates