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| 直升机/发动机系统变旋翼转速串行优化方案 | |
| 引用本文： | 张海波,姚文荣,王日先,田迪.直升机/发动机系统变旋翼转速串行优化方案[J].航空动力学报,2010,25(10):2363-2371. |
| 作者姓名： | 张海波 姚文荣 王日先 田迪 |
| 作者单位： | 1. 南京航空航天大学,能源与动力学院,南京,210016;中国航空工业集团公司,中航工业航空动力控制系统研究所,无锡,214016 2. 中国航空工业集团公司,中航工业航空动力控制系统研究所,无锡,214016 3. 南京航空航天大学,能源与动力学院,南京,210016 |
| 基金项目： | 航空支撑科技基金，南京航空航天大学基本科研业务费专项科研项目 |
| 摘 要： | 提出了一种用于直升机/涡轴发动机综合控制的变旋翼转速串行优化方案.首先基于Levenberg-Marquarat(L-M)算法/一维最优搜索算法,在保证直升机飞行状态不变的情况下,寻优得到旋翼所需最小功率,再通过优化发动机操纵量,在保证发动机约束成立的条件下得到当前发动机运行最优工作点,即达到直升机巡航时油耗最小或者涡轮前温度最低.最后,在UH-60直升机/涡轴发动机综合控制仿真平台上进行了最小油耗控制模式的仿真,数字仿真结果表明了该串行优化方案的可行性. |
| 关 键 词： | 涡轴发动机 直升机 综合控制 串行优化 Levenberg-Marquarat(L-M)算法 |
| 收稿时间： | 2009/9/22 0:00:00 |
| 修稿时间： | 2010/3/18 0:00:00 |
Rotor speed changeable cascaded optimization method for helicopter/engine system |
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| ZHANG Hai-bo,YAO Wen-rong,WANG Ri-xian and TIAN Di.Rotor speed changeable cascaded optimization method for helicopter/engine system[J].Journal of Aerospace Power,2010,25(10):2363-2371. | |
| Authors: | ZHANG Hai-bo YAO Wen-rong WANG Ri-xian and TIAN Di |
| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaChina Aviation Motor Control System Institute, Aviation Industry Corporation of China, Wuxi 214016, China;China Aviation Motor Control System Institute, Aviation Industry Corporation of China, Wuxi 214016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| Abstract: | A cascaded optimization scheme by which the main rotor speed can be changed was proposed to solve helicopter/turbo-shaft engine hybrid control problem.Firstly,the minimal power demand of main rotor was found by Levenberg-Marquarat(L-M)algorithm and one-dimensional search optimization algorithm under the helicopter's stable flying state.And secondly,the engine's optimum operating point,i.e.:least fuel consumption state or lowest inlet turbine temperature state,was calculated by optimizing engine's manipulate variables,provided that the engine's constraints were not violated.At last,specific fuel consumption mode control was simulated based on UH-60 helicopter/turbo-shaft engine hybrid control platform;the simulation results show that the cascade optimization scheme is feasible and valid. |
| Keywords: | turbo-shaft engine helicopter hybrid control cascade optimization Levenberg-Marquarat(L-M) algorithm |
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