| Autor: |
Yun-tao Zheng, Jun Chen, Jue Wang, Xiao-yan Tong, Jie Fang, Guobiao Cai |
| Rok vydání: |
2005 |
| Předmět: |
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| Zdroj: |
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. |
| DOI: |
10.2514/6.2005-3743 |
| Popis: |
Generic simulation and optimization software of system parameters for the engine with gas generator cycle was developed to design and optimize rocket engines of different structural forms. For this paper, the engine with gas generator cycle was decomposed into several principal components, such as the thruster chamber, turbopumps, and gas generators. Numerical simulation codes were developed for each component and the system. According to different relationships between the components, these modular codes could be integrated arbitrarily. Chemical equilibrium analysis for the bipropellants types in the system had been built into the simulation model. A generic optimization procedure of system parameters for the engine with gas generator cycle was developed to maximize the engine specific impulse and the thrust to weight ratio. The Multidisciplinary Design Optimization (MDO) approaches such as Multidisciplinary Feasible (MDF) method and Collaborative Optimization (CO) method were employed during the optimization process. Several methods of multi-objective processing were also investigated for the design of a particular hydrogen- oxygen rocket engine to obtain the Pareto frontier as well as the relative optimal solutions. In addition, uncertainties in the engine operation were considered. Results of reliability - based optimization presented illustrate the tradeoff between the engine performance and the design reliability. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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