This paper presents a convex programming approach to the optimization of a multistage launch vehicle ascent trajectory, from the liftoff to the payload injection into the target orbit, taking into account multiple nonconvex constraints, such as the maximum heat flux after fairing jettisoning and the splash-down of the burned-out stages. Lossless and successive convexification are employed to convert the problem into a sequence of convex subproblems. Virtual controls and buffer zones are included to ensure the recursive feasibility of the process and a state-of-the-art method for updating the reference solution is implemented to filter out undesired phenomena that may hinder convergence. A hp pseudospectral discretization scheme is used to accurately capture the complex ascent and return dynamics with a limited computational effort. The convergence properties, computational efficiency, and robustness 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 case study to discuss the interaction between the heat flux and splash-down constraints. Finally, a sensitivity analysis of the launch vehicle carrying capacity to different splash-down locations is presented.

Convex optimization of launch vehicle ascent trajectory with heat-flux and splash-down constraints / Benedikter, Boris; Zavoli, Alessandro; Colasurdo, Guido; Pizzurro, Simone; Cavallini, Enrico. - 175:(2020), pp. 2773-2792. (Intervento presentato al convegno AAS/AIAA Astrodynamics specialist conference tenutosi a Virtual Event).

Convex optimization of launch vehicle ascent trajectory with heat-flux and splash-down constraints

Boris Benedikter
;
Alessandro Zavoli;Guido Colasurdo;Simone Pizzurro;Enrico Cavallini
2020

Abstract

This paper presents a convex programming approach to the optimization of a multistage launch vehicle ascent trajectory, from the liftoff to the payload injection into the target orbit, taking into account multiple nonconvex constraints, such as the maximum heat flux after fairing jettisoning and the splash-down of the burned-out stages. Lossless and successive convexification are employed to convert the problem into a sequence of convex subproblems. Virtual controls and buffer zones are included to ensure the recursive feasibility of the process and a state-of-the-art method for updating the reference solution is implemented to filter out undesired phenomena that may hinder convergence. A hp pseudospectral discretization scheme is used to accurately capture the complex ascent and return dynamics with a limited computational effort. The convergence properties, computational efficiency, and robustness 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 case study to discuss the interaction between the heat flux and splash-down constraints. Finally, a sensitivity analysis of the launch vehicle carrying capacity to different splash-down locations is presented.
2020
AAS/AIAA Astrodynamics specialist conference
convex optimization; ascent trajectory; launch vehicle; optimal control
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Convex optimization of launch vehicle ascent trajectory with heat-flux and splash-down constraints / Benedikter, Boris; Zavoli, Alessandro; Colasurdo, Guido; Pizzurro, Simone; Cavallini, Enrico. - 175:(2020), pp. 2773-2792. (Intervento presentato al convegno AAS/AIAA Astrodynamics specialist conference tenutosi a Virtual Event).
File allegati a questo prodotto
File Dimensione Formato  
benedikter_convex_optimization.pdf

solo gestori archivio

Tipologia: Versione editoriale (versione pubblicata con il layout dell'editore)
Licenza: Tutti i diritti riservati (All rights reserved)
Dimensione 366.75 kB
Formato Adobe PDF
366.75 kB Adobe PDF   Contatta l'autore

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1452829
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 0
  • ???jsp.display-item.citation.isi??? 11
social impact