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

This paper presents a convex programming approach to the optimization of amultistage launch vehicle ascent trajectory, from the liftoff to the payloadinjection into the target orbit, taking into account multiple nonconvexconstraints, such as the maximum heat flux after fairing jettisoning and thesplash-down of the burned-out stages. Lossless and successive convexificationare employed to convert the problem into a sequence of convex subproblems.Virtual controls and buffer zones are included to ensure the recursivefeasibility of the process and a state-of-the-art method for updating thereference solution is implemented to filter out undesired phenomena that mayhinder convergence. A hp pseudospectral discretization scheme is used toaccurately capture the complex ascent and return dynamics with a limitedcomputational effort. The convergence properties, computational efficiency, androbustness of the algorithm are discussed on the basis of numerical results.The ascent of the VEGA launch vehicle toward a polar orbit is used as casestudy to discuss the interaction between the heat flux and splash-downconstraints. Finally, a sensitivity analysis of the launch vehicle carryingcapacity to different splash-down locations is presented.

Convex Optimization of Launch Vehicle Ascent Trajectory with Heat-Flux and Splash-Down Constraints