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 Plus annual

Presents the access of premium content as premium feature

Premium Content

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 Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

Performing orbital insertion around Mars using aerocapture instead of apropulsive orbit insertion manoeuvre allows to save resources and/or increasethe payload mass fraction. Aerocapture has never been employed to date becauseof the high uncertainties in the parameters from which it depends, mainlyrelated to atmospheric density modeling and navigation errors. The purpose ofthis work is to investigate the feasibility of aerocapture at Mars with aninnovative deployable drag device, whose aperture can be modulated in flight,and assess the effects of the main uncertainties on the success of themanoeuvre. This paper starts with the presentation of a parametricbi-dimensional analysis of the effectiveness of aerocapture, for which a widerange of uncertainty levels in the atmospheric density and the ballisticcoefficient are considered. Then, an application to a real mission scenario iscarried out including the error of the targeting manoeuvre performed at thelimit of the sphere of influence of the planet. The analyses show the stronginfluence of the uncertainties in the atmospheric density and the ballisticcoefficient, which significantly narrow the solution space and limit itscontinuity. However, viable solutions for aerocapture can still be identifiedeven in the worst conditions.

Feasibility Study of Aerocapture at Mars with an Innovative Deployable Heat Shield