Liquid rocket engine performance assessment in the context of small launcher optimisation

The paper presents a fast mathematical model that can be used to quickly asses the propulsive characteristics of liquid propelled rocket engines. The main propulsive parameters are computed using combustion surfaces obtained after a nonlinear data fitting analysis. This approach is much more time ef...

Full description

Saved in:
Bibliographic Details
Published in:INCAS bulletin 2019-09, Vol.11 (3), p.135-145
Main Authors: ONEL, Alexandru-Iulian, POPESCU, Oana-Iuliana, NECULAESCU, Ana-Maria, AFILIPOAE, Tudorel-Petronel, CHELARU, Teodor-Viorel
Format: Article
Language:English
Subjects:
Aeronautics
Algorithms
Altitude
Atmospheric pressure
Engines
Fuel combustion
Kerosene
mathematical model
Mathematical models
Mathematical programming
Molecular weight
multidisciplinary optimisation
Nonlinear analysis
nonlinear surface fitting
Optimization
Performance assessment
Rocket engines
rocket propulsion
Rockets
small launchers
specific impulse
Citations: Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:The paper presents a fast mathematical model that can be used to quickly asses the propulsive characteristics of liquid propelled rocket engines. The main propulsive parameters are computed using combustion surfaces obtained after a nonlinear data fitting analysis. This approach is much more time efficient than using standard codes which rely on frequent calls of the Fuel Combustion Charts and interpolating their data. The tool developed based on the proposed mathematical model can be used separately or it can be integrated in a multidisciplinary optimisation algorithm for a preliminary microlauncher design.
ISSN:2066-8201
2247-4528
DOI:10.13111/2066-8201.2019.11.3.12