Parametric analysis of a two-stage small launcher using a MDO approach
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Published:2022-03-07
Issue:1
Volume:14
Page:79-96
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ISSN:2247-4528
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Container-title:INCAS BULLETIN
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language:en
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Short-container-title:INCAS BULLETIN
Author:
ONEL Alexandru-Iulian1, CHELARU Teodor-Viorel2
Affiliation:
1. INCAS – National Institute for Aerospace Research “Elie Carafoli”, B-dul Iuliu Maniu 220, 061126, Bucharest, Romania, onel.alexandru@incas.ro and “POLITEHNICA” University of Bucharest, Faculty of Aerospace Engineering, Str. Gheorghe Polizu 1-7, 011061, Bucharest, Romania 2. “POLITEHNICA” University of Bucharest, Faculty of Aerospace Engineering, Str. Gheorghe Polizu 1-7, 011061, Bucharest, Romania, teodor.chelaru@upb.ro
Abstract
The paper presents the influence of the main design requirements on the optimal two-stage small launcher configuration. The influence of target orbit altitude, payload mass, typical missions, and the type of liquid propellant (oxidizer - fuel pair) used on the launcher characteristics is quantified. The launchers are obtained using a multidisciplinary design optimisation (MDO) algorithm, where the lowest mass configuration capable of accurately inserting the payload into the target orbit is considered to be optimal.
Publisher
INCAS - National Institute for Aerospace Research Elie Carafoli
Subject
Aerospace Engineering,Control and Systems Engineering
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