Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers
Hybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines. In this work, the design of a three-stage hybrid launch...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-12-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/12/807 |
| _version_ | 1797461946221461504 |
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| author | Lorenzo Casalino Andrea Ferrero Filippo Masseni Dario Pastrone |
| author_facet | Lorenzo Casalino Andrea Ferrero Filippo Masseni Dario Pastrone |
| author_sort | Lorenzo Casalino |
| collection | DOAJ |
| description | Hybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines. In this work, the design of a three-stage hybrid launcher is optimized by means of a coupled procedure: an evolutionary algorithm optimizes the engine design, whereas an indirect optimization method optimizes the corresponding ascent trajectory. The trajectory integration also provides the vertical emission profiles required for the evaluation of the environmental impact of the launch. The propellants are a paraffin-based wax and liquid oxygen. The vehicle is launched from the ground and uses an electric turbo pump feed system. The initial mass is given (5000 kg) and the insertion of the payload into a 600-km circular, and polar orbit is considered as a reference mission. Clusters of similar hybrid rocket engines, with only few differences, are employed in all stages to reduce the development and operational costs of the launcher. Optimization is carried out with the aim of maximizing the payload mass and then minimizing the overall environmental impact of the launch. The results show that satisfactory performance is achievable also considering rocket polluting emissions: the carbon footprint of the launch can be reduced by one fourth at the cost of a 5-kg payload mass reduction. |
| first_indexed | 2024-03-09T17:26:35Z |
| format | Article |
| id | doaj.art-0aa864df779c4e59921752b07addc8cf |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T17:26:35Z |
| publishDate | 2022-12-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-0aa864df779c4e59921752b07addc8cf2023-11-24T12:38:21ZengMDPI AGAerospace2226-43102022-12-0191280710.3390/aerospace9120807Emission-Driven Hybrid Rocket Engine Optimization for Small LaunchersLorenzo Casalino0Andrea Ferrero1Filippo Masseni2Dario Pastrone3Dipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyHybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines. In this work, the design of a three-stage hybrid launcher is optimized by means of a coupled procedure: an evolutionary algorithm optimizes the engine design, whereas an indirect optimization method optimizes the corresponding ascent trajectory. The trajectory integration also provides the vertical emission profiles required for the evaluation of the environmental impact of the launch. The propellants are a paraffin-based wax and liquid oxygen. The vehicle is launched from the ground and uses an electric turbo pump feed system. The initial mass is given (5000 kg) and the insertion of the payload into a 600-km circular, and polar orbit is considered as a reference mission. Clusters of similar hybrid rocket engines, with only few differences, are employed in all stages to reduce the development and operational costs of the launcher. Optimization is carried out with the aim of maximizing the payload mass and then minimizing the overall environmental impact of the launch. The results show that satisfactory performance is achievable also considering rocket polluting emissions: the carbon footprint of the launch can be reduced by one fourth at the cost of a 5-kg payload mass reduction.https://www.mdpi.com/2226-4310/9/12/807hybrid rocket enginesmultidisciplinary optimizationgreen propulsion |
| spellingShingle | Lorenzo Casalino Andrea Ferrero Filippo Masseni Dario Pastrone Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers Aerospace hybrid rocket engines multidisciplinary optimization green propulsion |
| title | Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers |
| title_full | Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers |
| title_fullStr | Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers |
| title_full_unstemmed | Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers |
| title_short | Emission-Driven Hybrid Rocket Engine Optimization for Small Launchers |
| title_sort | emission driven hybrid rocket engine optimization for small launchers |
| topic | hybrid rocket engines multidisciplinary optimization green propulsion |
| url | https://www.mdpi.com/2226-4310/9/12/807 |
| work_keys_str_mv | AT lorenzocasalino emissiondrivenhybridrocketengineoptimizationforsmalllaunchers AT andreaferrero emissiondrivenhybridrocketengineoptimizationforsmalllaunchers AT filippomasseni emissiondrivenhybridrocketengineoptimizationforsmalllaunchers AT dariopastrone emissiondrivenhybridrocketengineoptimizationforsmalllaunchers |