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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Design optimization of a thrust chamber using a mass-based model to improve the geometrical and performance parameters of low-thrust space propulsion systems
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Design optimization of a thrust chamber using a mass-based model to improve the geometrical and performance parameters of low-thrust space propulsion systems

机译：使用基于质量的模型对推力室进行设计优化，以改善低推力空间推进系统的几何和性能参数

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摘要

A large portion of the wet and dry mass budget in any space system is assigned to the propulsion system. Each of these depends on the engine system design values. Any effort to decrease the mass of space systems demands an additional effort to reduce the propulsion system mass, which in turn requires a complete review of the engine design. Thus, proposing a computational model derived from the engine design and based on minimum system mass is necessary. The present computational research developed a propulsion system design strategy for liquid propulsion systems to optimize take-off mass and satisfy the thrust required under performance and structural constraints. Improvement of the geometric and performance variables and component mass using a mass-based model for optimization process is investigated. The method uses a hybrid genetic algorithm sequential quadratic programming as an optimizer. The mass-based formulation problem is solved using a hybrid optimization algorithm with a genetic algorithm as the global optimizer and sequential quadratic programming as the local optimizer starting from the solution given by the genetic algorithm. The convergence of the optimization algorithm is improved by introducing an initial solution based on genetic algorithm. Comparison of the proposed design optimization model with a real space propulsion system indicates that the performance of the proposed algorithm significantly improved the final results. While propellant mass, engine consumption rate and engine geometric dimensions decreased, specific impulse increased. All of these decreased the total mass of the space propulsion system.
机译：在任何空间系统中，大部分干湿预算都分配给了推进系统。这些都取决于发动机系统的设计值。减少空间系统质量的任何努力都要求减少推进系统质量的额外努力，这又需要对发动机设计进行全面审查。因此，有必要提出一种基于发动机设计并基于最小系统质量的计算模型。当前的计算研究为液体推进系统开发了一种推进系统设计策略，以优化起飞质量并满足性能和结构约束下所需的推力。使用基于质量的模型进行优化过程，研究了几何和性能变量以及零件质量的改进。该方法使用混合遗传算法顺序二次规划作为优化程序。使用基于遗传算法给出的解的遗传算法作为全局优化器和顺序二次规划作为局部优化器的混合优化算法解决了基于质量的配方问题。通过引入基于遗传算法的初始解，提高了优化算法的收敛性。所提出的设计优化模型与实际空间推进系统的比较表明，所提出的算法的性能显着改善了最终结果。当推进剂质量，发动机消耗率和发动机几何尺寸减小时，比冲增加。所有这些减少了空间推进系统的总质量。

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