Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach
For a small country with limited research budget and lack of advanced space technology, it is imperative to find new approaches for the development of low-cost launch vehicles (LV), which is, among all possibilities, an interesting option for rapid access to space, focused on integration of acquired...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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Instituto de Aeronáutica e Espaço (IAE)
2014-09-01
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| Series: | Journal of Aerospace Technology and Management |
| Subjects: | |
| Online Access: | https://www.jatm.com.br/jatm/article/view/333 |
| _version_ | 1818192722621628416 |
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| author | Fredy Marcell Villanueva Lee Linshu Xu Dajun |
| author_facet | Fredy Marcell Villanueva Lee Linshu Xu Dajun |
| author_sort | Fredy Marcell Villanueva |
| collection | DOAJ |
| description | For a small country with limited research budget and lack of advanced space technology, it is imperative to find new approaches for the development of low-cost launch vehicles (LV), which is, among all possibilities, an interesting option for rapid access to space, focused on integration of acquired components complemented with indigenously developed subsystems. This approach requires the cooperation of developed countries with huge experience and knowledge in LV development and operations. The main objective is to develop a small three stage solid propellant LV capable of delivering a payload of 100 kg to a circular low earth orbit of 600 km altitude, with the first and second stage solid rocket motors (SRM) hypothetically acquired from different countries and the third one designed and produced domestically in accordance with the production and technological capability. This approach provides main advantages such as: reduction in total time to access the space and to master the basic knowledge of launch operations. For this purpose, an integer continuous genetic algorithm global optimization method was selected and implemented, the SRM characteristics of the first and second stage were considered as integer variables, whereas the design variables of the third stage SRM and the trajectory variable were considered as continuous. A multi discipline feasible (MDF) framework was implemented along with the propulsion, aerodynamic, mass and trajectory models. Despite their particular characteristics and constraints, the results show highly acceptable values, and the approach proved to be reliable for conceptual design level. |
| first_indexed | 2024-12-12T00:35:01Z |
| format | Article |
| id | doaj.art-059b80fca8e544c383a26830ced3ac66 |
| institution | Directory Open Access Journal |
| issn | 2175-9146 |
| language | English |
| last_indexed | 2024-12-12T00:35:01Z |
| publishDate | 2014-09-01 |
| publisher | Instituto de Aeronáutica e Espaço (IAE) |
| record_format | Article |
| series | Journal of Aerospace Technology and Management |
| spelling | doaj.art-059b80fca8e544c383a26830ced3ac662022-12-22T00:44:23ZengInstituto de Aeronáutica e Espaço (IAE)Journal of Aerospace Technology and Management2175-91462014-09-0163Small Solid Propellant Launch Vehicle Mixed Design Optimization ApproachFredy Marcell Villanueva0Lee LinshuXu DajunBeihang UniversityFor a small country with limited research budget and lack of advanced space technology, it is imperative to find new approaches for the development of low-cost launch vehicles (LV), which is, among all possibilities, an interesting option for rapid access to space, focused on integration of acquired components complemented with indigenously developed subsystems. This approach requires the cooperation of developed countries with huge experience and knowledge in LV development and operations. The main objective is to develop a small three stage solid propellant LV capable of delivering a payload of 100 kg to a circular low earth orbit of 600 km altitude, with the first and second stage solid rocket motors (SRM) hypothetically acquired from different countries and the third one designed and produced domestically in accordance with the production and technological capability. This approach provides main advantages such as: reduction in total time to access the space and to master the basic knowledge of launch operations. For this purpose, an integer continuous genetic algorithm global optimization method was selected and implemented, the SRM characteristics of the first and second stage were considered as integer variables, whereas the design variables of the third stage SRM and the trajectory variable were considered as continuous. A multi discipline feasible (MDF) framework was implemented along with the propulsion, aerodynamic, mass and trajectory models. Despite their particular characteristics and constraints, the results show highly acceptable values, and the approach proved to be reliable for conceptual design level.https://www.jatm.com.br/jatm/article/view/333Launch vehicleMixed design optimizationSolid propellant. |
| spellingShingle | Fredy Marcell Villanueva Lee Linshu Xu Dajun Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach Journal of Aerospace Technology and Management Launch vehicle Mixed design optimization Solid propellant. |
| title | Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach |
| title_full | Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach |
| title_fullStr | Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach |
| title_full_unstemmed | Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach |
| title_short | Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach |
| title_sort | small solid propellant launch vehicle mixed design optimization approach |
| topic | Launch vehicle Mixed design optimization Solid propellant. |
| url | https://www.jatm.com.br/jatm/article/view/333 |
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