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论文:2016,Vol:34,Issue(6):1101-1107 |
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引用本文： |
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孙乐园, 贾如岩, 杨枝山, 江振宇. 重型运载火箭轨迹/总体参数一体化优化方法[J]. 西北工业大学学报 |
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Sun Leyuan, Jia Ruyan, Yang Zhishan, Jiang Zhenyu. An Integrated Optimization Method of Trajectory/System Parameters for Heavy Launch Vehicles[J]. Northwestern polytechnical university |
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| 重型运载火箭轨迹/总体参数一体化优化方法 |
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| 孙乐园, 贾如岩, 杨枝山, 江振宇 |
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| 国防科学技术大学 航天科学与工程学院, 湖南 长沙 410073 |
| 摘要: |
| 研究了重型运载火箭轨迹/总体参数一体化优化问题。建立了一体化参数优化模型，设计了一种双环迭代优化算法，外环采用遗传算法进行参数优化，内环通过带自适应松弛因子的改进牛顿迭代法进行参数迭代。针对牛顿迭代法对模型本身及迭代初值敏感的问题，提出了一种模型变量筛选方法和迭代初值生成方法。基于Morris参数全局灵敏度分析法筛选出对终端等式约束影响最大的参数作为牛顿迭代变量，以历史迭代收敛值作为当前迭代初值。并通过迭代误差监控，保证了算法的鲁棒性。以三级液体重型运载火箭为对象，进行了一体化优化仿真。仿真结果显示起飞总质量减少了4.09%，表明设计的双环迭代优化算法能在复杂约束下完成重型运载火箭轨迹/总体参数一体化优化。 |
| 关键词:
重型运载火箭
一体化优化
改进牛顿迭代法
全局灵敏度分析
迭代初值
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| An Integrated Optimization Method of Trajectory/System Parameters for Heavy Launch Vehicles |
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| Sun Leyuan, Jia Ruyan, Yang Zhishan, Jiang Zhenyu |
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| College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China |
| Abstract: |
| The integrated optimization of trajectory/system parameters for heavy launch vehicles was investigated. A model of integrated optimization was set up. An iterative optimization algorithm with double loops was designed. The genetic algorithm was used to optimize parameters in outer loop, and the improved Newton iteration method with an adaptive relaxation factor was used to iterate parameters in inner loop. Aiming at the susceptibility of Newton iteration method to the model and initial values, a method of model variable screening and initial iteration values generation were proposed. Based on the Morris method of global sensitivity analysis, the parameters with the biggest influence on the terminal equality constraints were taken as the Newton iteration variables. And the historic convergent iteration values were set as the current initial iteration values. And the robustness of the algorithm was ensured by monitoring of the iterative error. A liquid heavy launch vehicle with 3 levels was set as an example for integrated optimization simulation. The results showed that initial mass decreases by 4.09% and demonstrate that the iterative optimization algorithm with double loops can complete the integrated optimization of trajectory/system parameters for heavy launch vehicles with complex constraints. |
| Key words:
Heavy launch vehicles
Integrated optimization
Improved Newton iteration method
Global sensitivity analysis
Initial iteration values
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| 收稿日期: 2016-04-14
修回日期:
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| DOI: |
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| 作者简介: 孙乐园(1991-),国防科学技术大学硕士研究生,主要从事飞行器总体设计与系统仿真研究。
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